寺島 洋史(テラシマ ヒロシ) |

工学研究院 機械・宇宙航空工学部門 宇宙航空システム |

准教授 |

Last Updated :2020/08/07

- 20415235

- 情報通信 / 計算科学
- 情報通信 / 計算科学
- フロンティア（航空・船舶） / 航空宇宙工学
- ものづくり技術（機械・電気電子・化学工学） / 熱工学
- 社会基盤（土木・建築・防災） / 安全工学
- 社会基盤（土木・建築・防災） / 社会システム工学

- 2015年12月 - 現在 北海道大学 工学研究院 准教授
- 2013年04月 - 2015年11月 東京大学 工学系研究科 特任准教授
- 2011年04月 - 2013年03月 東京大学 工学系研究科 特任助教
- 2009年04月 - 2011年03月 宇宙航空研究開発機構 宇宙航空プロジェクト研究員
- 2007年04月 - 2009年03月 Worcester Polytechnic Institute Mechanical Engineering Department Research Scientist
- 2005年04月 - 2007年03月 理化学研究所 研究員（2006年11月より客員研究員）
- 2004年04月 - 2005年03月 東京大学 IML 機関研究員

- 2000年04月 - 2004年03月 東京大学 航空宇宙工学専攻 博士課程
- 1998年04月 - 2000年03月 東北大学 航空宇宙工学専攻 博士課程前期
- 1994年04月 - 1998年03月 東北大学 工学部 機械航空工学科

- Terashima, Hiroshi, Matsugi, Akira, Koshi, MitsuoCOMBUSTION AND FLAME 203 204 - 216 2019年05月 [査読有り][通常論文]

The present study addresses effects of pressure wave disturbance on end-gas autoignition behavior and subsequent pressure wave development, which are of particular interest for understanding a fundamental process of knocking combustion in spark-assisted ignition engines. Such pressure wave disturbance is initiated by a compression wave generated from spark-like ignition and continuously exists in a combustion chamber. The investigation is conducted through a direct numerical simulation with a 1-D constant volume reactor, where the compressible Navier-Stokes equations are solved with detailed reaction mechanisms of n-C7H16 and n-C4H10/air mixtures. The width of an ignition kernel parametrically changes in order to control the strength of an initial compression wave and thus pressure wave disturbance. The result showed that stronger compression waves with larger kernel widths enhance the progress of the autoignition process at the wall through the transient increase in pressure and temperature due to the wave reflection. Consequently, stronger pressure waves such as a developing detonation are generated with the enhanced inhomogeneous end-gas autoignition starting from the wall. In contrast, weak pressure wave disturbance produces no strong pressure waves due to the lower inhomogeneity of autoignition timing in an end-gas region. An analysis with temperature variation in an end-gas region indicates that cool flame generation helps maintain the superiority of the wall for earlier autoignition through the heat release at an earlier stage. Therefore, a stronger pressure wave associated with inhomogeneous end-gas autoignition is likely generated around 650 K in the case of an n-C7H16/air mixture, which corresponds to a distinct peak generation of knocking intensity in the negative temperature coefficient regime. For lower temperature conditions such as 500 K, the end-gas autoignition first takes place in a region away from the wall. This is because the initially induced temperature inhomogeneity in the end-gas region is considerably weakened due to wave interactions and dissipation effects during longer ignition delay times. Thus, multiple end-gas points including the wall can become a preferred point for earlier end-gas autoignition, resulting in a variation of end-gas autoignition locations. The result for an n-C4H10 air mixture is finally shown and the difference from that for the n-C7H16/air mixture is highlighted. (C) 2019 The Combustion Institute. Published by Elsevier Inc. All rights reserved. - Daiki Muto, Hiroshi Terashima, Nobuyuki TsuboiTransactions of the Japan Society for Aeronautical and Space Sciences 62 203 - 212 2019年01月 [査読有り][通常論文]

© 2019 The Japan Society for Aeronautical and Space Sciences. The effects of a recess on co-flowing planar jets under supercritical pressure are numerically studied. Two-dimensional hybrid LES/RANS simulations are performed in a wide range of recess lengths and injection momentum flux ratios, which are important design parameters for liquid rocket engine injectors. The present study showed that confinement effects of the near-injector flowfield by applying a recess, suppress outer jet spreading and thus enhances the penetration of the outer jet flow into the inner jet. The enhanced penetration of the outer jet flow results in the appearance of flapping motions in the inner jet. Low-frequency oscillations corresponding to the flapping motions clearly appear in the case of recessed injectors. Moreover, the confinement effects promote interactions between vortex structures resulting in vortex breakdown. Consequently, the inner-jet length is shortened, indicating an improvement in mixing when a recess is applied. The present results also show that the inner-jet length deceases as the recess length increases, and the effects of a recess remarkably appear at higher momentum flux ratios. This is explained by the vortices generated behind the post lip that is strengthened as the result of increased velocity ratio. - A. Razmi, M. Taeibi-Rahni, H. R. Massah, H. Terashima, H. MoezziJournal of Applied Fluid Mechanics 12 631 - 645 2019年01月 [査読有り][通常論文]

© 2019 Isfahan University of Technology. A front tracking/ghost fluid method was used to simulate fluid interfaces in a shock-bubble interaction problem. The method captures fluid interfaces, using explicit front-tracking and defines interface conditions, using the ghost-fluid method. In order to demonstrate the accuracy and the capability tracking of the approach used, an air-helium and anair-R22 shock-bubble interaction cases were simulated. The computational results were compared with reliable experimental and computational studies, showing close agreements. - D Deb, MA Uddin, H Terashima, N OshimaJournal of Scientific Research 10 2 117 - 131 2018年 [査読有り][通常論文]
- Hiroumi Tani, Hiroshi Terashima, Yu Daimon, Mitsuo Koshi, Ryoichi KuroseCOMBUSTION SCIENCE AND TECHNOLOGY 190 3 515 - 533 2018年 [査読有り][通常論文]

Unsteady simulations of hydrazine (N2H4) sprays in nitrogen tetroxide (NTO, NO2-N2O4) streams were conducted to explore the hypergolic combustion in bipropellant thrusters. The Navier-Stokes equations were solved using a detailed chemical kinetics mechanism and dispersed droplets were modeled through direct numerical simulations. Auto-ignition occurred when the sum of the heat transfer from the ambient gas and the heat release from hydrogen abstraction reactions exceeded the latent heat of the droplets. Although the evaporation of the droplets was enhanced as the droplet size decreased, the ignition delay time increased due to the lower temperatures of the mixtures of the N2H4 vapor and nitrogen tetroxide. After the flames reached a steady state, a double flame structure appeared, comprised of outer diffusion and inner decomposition flames. The inner decomposition flame and N2H4 vapor flow exhibited a sinusoidal behavior at a certain droplet size. This behavior was initiated by the locally expanded decomposition gases and developed by the supply of N2H4 droplets to the decomposition gases at relatively high temperatures. In cases of larger and smaller droplet sizes, the sinusoidal behavior was not significant due to less evaporation of the N2H4 droplets and a lower temperature of the N2H4 vapor, respectively. The sinusoidal behavior of the decomposition flames enhanced the mixing and reactions of the fuel components (i.e., N2H4, NH3, and H-2). The present study demonstrated a large impact of droplet size on flame dynamics, suggesting that a fine spray is not always better for hypergolic propellant combustion to consume the fuel components quickly. - Ohashi Tatsushi, Takahashi Yusuke, Terashima Hiroshi, Oshima NobuyukiJOURNAL OF FLUID SCIENCE AND TECHNOLOGY 13 3 2018年 [査読有り][通常論文]
- Terashima, Hiroshi, Matsugi, Akira, Koshi, MitsuoCOMBUSTION AND FLAME 184 324 - 334 2017年10月 [査読有り][通常論文]

The present study deals with the mechanisms for the hot-spot formation and pressure wave development associated with end-gas autoignition during knocking combustion of n-heptane/air mixture. The discussion is based on a one-dimensional (1-D) direct numerical simulation, where the compressible Navier-Stokes equations are solved with a detailed chemical kinetic mechanism of n-heptane, involving 373 species and 1071 reactions. The result demonstrates that the first trigger for a hot-spot formation is a compression wave generated by forced autoignition of a hot kernel and its reflection at a wall. The wall reflection of the propagating compression wave periodically produces an instantaneous temperature increase, which leads to the production of a larger amount of chemical species compared to that of other end-gas points. This non-uniform progress of chemical reaction process continues to exist at the wall, although the temperature increase is transient, resulting in faster autoignition and pressure wave generation at the wall. Thus, an important aspect of observing chemistry behaviors rather than temperature is demonstrated on the mechanism of hot-spot formation. The present study further addresses the reactivity of hot-spots on the relevance to pressure wave developments, wherein a zero-dimensional (0-D) ignition problem with pulsed compression waves is introduced. The higher reactivity of n-heptane/air mixture against pulse waves is observed with the faster ignition delay times in lower and higher initial temperature conditions. Conversely, the result at initial temperatures of 750-800 K indicates the lower reactivity with no significant effects of pulse waves on the ignition delay times. This is connected with the fuel characteristics of a negative temperature coefficient. Thus, in the 1-D simulations, a hot-spot with the high reactivity enhances spatial temperature difference in the end-gas region, leading to strong pressure wave generations. In contrast, a hot-spot with the low reactivity suppresses the pressure wave development with little spatial variation in temperature. The result demonstrates a significant aspect of hot-spot formation and reactivity on pressure wave development during knocking combustion. (C) 2017 The Combustion Institute. Published by Elsevier Inc. All rights reserved. - Akira Matsugi, Hiroshi Terashima, Hiroshi TerashimaCombustion and Flame 179 238 - 241 2017年05月 [査読有り][通常論文]

© 2017 The Combustion Institute The diffusive-thermal effect plays an important role in the intrinsic instability of premixed flames. A two-dimensional direct numerical simulation of the propagation of premixed hydrogen–air flames was performed using a detailed chemical kinetics model. The cellular behavior of a lean hydrogen–air flame was analyzed on the basis of its chemical structure. The primary consequence of the diffusive-thermal effect was found to be a change in the buildup process of reactive intermediates by the chain reaction mechanism at the preheat zone. The resultant chemical structure at the main reaction zone can be explained by the local composition change of the gas flowing into the reaction zone from the preheat zone. - Youhi Morii, Hiroshi Terashima, Mitsuo Koshi, Taro Shimizu, Eiji ShimaJOURNAL OF COMPUTATIONAL PHYSICS 322 547 - 558 2016年10月 [査読有り][通常論文]

We herein propose a fast and robust Jacobian-free time integration method named as the extended robustness-enhanced numerical algorithm (ERENA) to treat the stiff ordinary differential equations (ODEs) of chemical kinetics. The formulation of ERENA is based on an exact solution of a quasi-steady-state approximation that is optimized to preserve the mass conservation law through use of a Lagrange multiplier method. ERENA exhibits higher accuracy and faster performance in homogeneous ignition simulations compared to existing popular explicit and implicit methods for stiff ODEs such as VODE, MTS, and CHEMEQ2. We investigate the effects of user-specified threshold values in ERENA, to provide trade-off information between the accuracy and the computational cost. (C) 2016 Elsevier Inc. All rights reserved. - Soshi Kawai, Hiroshi Terashima, Hideyo NegishiJOURNAL OF COMPUTATIONAL PHYSICS 300 116 - 135 2015年11月 [査読有り][通常論文]

This paper addresses issues in high-fidelity numerical simulations of transcritical turbulent flows at supercritical pressure. The proposed strategy builds on a tabulated look-up table method based on REFPROP database for an accurate estimation of non-linear behaviors of thermodynamic and fluid transport properties at the transcritical conditions. Based on the look-up table method we propose a numerical method that satisfies high-order spatial accuracy, spurious-oscillation-free property, and capability of capturing the abrupt variation in thermodynamic properties across the transcritical contact surface. The method introduces artificial mass diffusivity to the continuity and momentum equations in a physically-consistent manner in order to capture the steep transcritical thermodynamic variations robustly while maintaining spurious-oscillation-free property in the velocity field. The pressure evolution equation is derived from the full compressible Navier-Stokes equations and solved instead of solving the total energy equation to achieve the spurious pressure oscillation free property with an arbitrary equation of state including the present look-up table method. Flow problems with and without physical diffusion are employed for the numerical tests to validate the robustness, accuracy, and consistency of the proposed approach. (C) 2015 Elsevier Inc. All rights reserved. - Nozomu Kanno, Hiroumi Tani, Yu Daimon, Hiroshi Terashima, Norihiko Yoshikawa, Mitsuo KoshiJOURNAL OF PHYSICAL CHEMISTRY A 119 28 7659 - 7667 2015年07月 [査読有り][通常論文]

The reactions of NO2 with cis-/trans-CH3NHNH, CH3NNH2 and CH2NHNH2 have been studied theoretically by quantum chemical calculations and steady-state unimolecular master equation analysis based on RRKM theory. The barrier heights for the roaming transition states between nitro (RNO2) and nitrite (RONO) isomerization reactions and those for the concerted HONO and HNO2 elimination reactions from RNO2 and RONO, affect the pressure dependences of the product-specific rate coefficients. At ambient temperature and pressure, the dominant product of the reactions of NO2 with cis-/trans-CH3NHNH and CH2NHNH2 would be expected to be HONO with trans-CH3NNH and CH2NNH2, respectively, whereas it is CH3N(NH2)NO2 for CH3NNH2 + NO2. The product-specific rate coefficients for the titled and related reactions on the same potential energy surfaces were proposed for kinetics modeling. - Hiroshi Terashima, Mitsuo KoshiCOMBUSTION AND FLAME 162 5 1944 - 1956 2015年05月 [査読有り][通常論文]

A knocking combustion modeled using a one-dimensional constant volume reactor is simulated in a manner of direct numerical simulations, in which large detailed chemical kinetic mechanisms for two pre-mixed gases, n-butane (113 species) and n-heptane (373 species), are directly and efficiently introduced. Detailed mechanisms of strong pressure wave generation during end-gas autoignition are clarified. Comparison of n-butane and n-heptane shows that the presence of the negative temperature coefficient (NTC) region significantly influences not only the timing of knocking occurrence but also the amplitude of pressure oscillations. In the case of n-heptane with the condition of an adiabatic wall, there is one large peak produced in the strength of knocking intensity for initial temperature between 450 and 1000 K, whereas there is no peak produced in the case of n-butane. The peak generated around 650 K is attributed to a pressure wave intensified through propagation in the end-gas, which is locally generated near the wall with the influence of the NTC region. It is also found that there is a transition of the autoignition position in the end-gas region from the wall for higher initial temperatures to the region ahead of the flame front for lower initial temperatures, leading to different mechanisms of knocking intensity generation. In the case of the isothermal wall condition, the peak around 650 K is reduced due to the lack of a local temperature increase at the wall, demonstrating the influence of wall temperature conditions on the strength of knocking intensity. (C) 2014 The Combustion Institute. Published by Elsevier Inc. All rights reserved. - Youhi Morii, Hiroshi Terashima, Mitsuo Koshi, Taro ShimizuJOURNAL OF LOSS PREVENTION IN THE PROCESS INDUSTRIES 34 92 - 99 2015年03月 [査読有り][通常論文]

A numerical simulation of the spontaneous ignition of high-pressure hydrogen in a duct with two obstacles on the walls is conducted to explore the spontaneous ignition mechanisms. Two-dimensional rectangular ducts are adopted, and the Navier Stokes equations with a detailed chemical kinetic mechanism are solved by using direct numerical simulations. In this study, we focus on the effects of the initial pressure of hydrogen and the position of the obstacles on the ignition mechanisms. Our results demonstrate that the presence of obstacles significantly changes the spontaneous ignition mechanisms producing three distinct ignition mechanisms. In addition, the position of the obstacles drastically changes the interaction of shock waves with the contact surface, and spontaneous ignition may take place at a relatively low pressure in some obstacle positions, which is attributed to the propagation direction and interaction timing of two reflected shock waves. (C) 2015 Elsevier Ltd. All rights reserved. - Hiroshi Terashima, Mitsuo KoshiJournal of Computational Physics 283 2015年01月01日 [査読無し][通常論文]
- Hiroumi Tani, Hiroshi Terashima, Yu Daimon, Mitsuo KoshiInternational Journal of Energetic Materials and Chemical Propulsion 14 71 - 84 2015年01月 [査読有り][通常論文]

© 2015 by Begell House, Inc. Hydrazine (N<inf>2</inf>H<inf>4</inf>)/nitrogen tetroxide (NTO) co-flowing jets were simulated to explore the hypergolic ignition processes in N<inf>2</inf>H<inf>4</inf>/NTO bipropellant thrusters. The Navier–Stokes equations with a detailed chemical kinetics mechanism were solved by direct numerical simulation to reveal the influence of the distinct chemical reaction; i.e., hydrogen abstraction by nitrogen dioxide (NO<inf>2</inf>). In the ignition processes, the hydrogen abstraction sequence, especially the reaction of N<inf>2</inf>H<inf>3</inf> and NO<inf>2</inf>, played a significant role in preheating the mixture gases and it was significant in the NTO-rich conditions rather than in the specifically stoichiometric conditions. Thus, in the N<inf>2</inf>H<inf>4</inf>/NTO co-flowing jets, the preheated regions correspond to the regions where the NTO-rich flows existed and contacted the N<inf>2</inf>H<inf>4</inf> jet. The ignition eventually occurred in the region where NTO has sufficient concentration. Hence, it was found that the ignition timing and position strongly depend on whether the unsteady behavior of the NTO jet provides appropriate environments for the hydrogen abstraction reactions. - Hiroumi Tani, Hiroshi Terashima, Mitsuo Koshi, Yu DaimonPROCEEDINGS OF THE COMBUSTION INSTITUTE 35 2199 - 2206 2015年 [査読有り][通常論文]

Hydrazine (N2H4)/nitrogen tetroxide (NTO) co-flowing plane jets were simulated to explore the hypergolic ignition processes and flame structures in N2H4/NTO bipropellant thrusters. The Navier-Stokes equations with a detailed chemical kinetics mechanism were solved in a manner of direct numerical simulation to reveal the influence of the distinct chemical reaction, i.e., hydrogen abstraction by nitrogen dioxide (NO2) and the thermal decomposition of N2H4. In the ignition processes, the hydrogen abstraction sequence played a significant role in preheating the mixture gases. Further, the ignition eventually occurred in the region where both N2H4 and NTO were sufficiently supplied for preheating. Hence, the ignition position and delay strongly depended on the fluid-mixing conditions. After the flames reached a steady state, the combustion flames uniquely comprised two types of flames, the outer diffusion flame and the inner decomposition flame. The outer diffusion flame came from the oxidization by NTO. The inner decomposition flame was caused and maintained by the heat transfer from the outer diffusion flame and a high rate of heat release from the thermal decomposition of N2H4. Because of the decomposition flame, the decomposition products such as NH3 and H-2 were the major constituents of the downstream combustion gases. (C) 2014 The Combustion Institute. Published by Elsevier Inc. All rights reserved. - Hiroshi Terashima, Youhi Morii, Mitsuo KoshiInternational Journal of Energetic Materials and Chemical Propulsion 14 177 - 196 2015年01月 [査読有り][通常論文]

© 2015 by Begell House, Inc. A robust explicit time integration method for stiff chemical reaction equations is proposed and applied to zero-dimensional ignition and one-dimensional combustion flow problems. The proposed method based on a multi-time scale method significantly improves the robustness of the original method by introducing two new strategies: automatic adjustment of time step size for each characteristic group using a quasi-steady-state assumption and automatic reset of base time step size using two appropriate criteria. The results for several zero-dimensional ignition problems demonstrate the robustness and accuracy of the proposed method compared to existing explicit and implicit integration methods. The present study also provides a computational cost estimation of various terms in the governing equations using a one-dimensional combustion problem (knocking simulation), where the Navier– Stokes equations are coupled with the chemical reaction equations. As well as the zero-dimensional problems, the robustness and capability of the proposed method are demonstrated. While the proposed method alleviates the occupancy of chemical reaction part in the total computational cost compared to an implicit time integration method, it is found that the transport properties calculations relatively increase with considerable amounts, suggesting efficient modeling of transport properties calculations for multi-dimensional combustion problems. - Akira Kikusato, Kazuya Kogo, Beini Zhou, Kusaka Jin, Yasuhiro Daisho, Kiyotaka Sato, Hidefumi Fujimoto, Hiroshi Terashima, Youhi MoriiSAE Technical Papers 2014-October 2014年10月13日 [査読有り][通常論文]

Copyright © 2014 SAE International. The objective of the present study is to analyze soot formation in diesel engine combustion by using multi-dimensional combustion simulations with a parallelized explicit ODE solver. Parallelized CHEMEQ2 was used to perform detailed chemical kinetics in KIVA-4 code. CHEMEQ2 is an explicit stiff ODE solver developed by Mott et al. which is known to be faster than traditional implicit ODE solvers, e.g., DVODE. In the present study, about eight times faster computation was achieved with CHEMEQ2 compared to DVODE when using a single thread. Further, by parallelizing CHEMEQ2 using OpenMP, the simulations could be run not only on calculation servers but also on desktop machines. The computation time decreases with the number of threads used. The parallelized CHEMEQ2 enabled combustion and emission characteristics, including detailed soot formation processes, to be predicted using KIVA-4 code with detailed chemical kinetics without the need for reducing the reaction mechanism. After validating the code, diesel engine combustion was simulated to investigate combustion and emission characteristics, focusing on soot formation, growth and oxidation at different EGR ratios. To predict soot formation, a gas-phase polycyclic aromatic hydrocarbons (PAH) precursor formation model was coupled with a detailed phenomenological particle formation model, which included soot nucleation from precursors, surface growth/oxidation and particle coagulation. The results indicate that increased soot emission at high EGR ratios is mainly caused by decreased oxidation by oxygen and OH radicals because mixing fuel and gases (including oxygen and OH) has significant effects on reducing the mass of soot. - Nozomu Kanno, Hiroshi Terashima, Yu Daimon, Norihiko Yoshikawa, Mitsuo KoshiINTERNATIONAL JOURNAL OF CHEMICAL KINETICS 46 8 489 - 499 2014年08月 [査読有り][通常論文]

The kinetics and mechanisms of H atom abstraction reactions from CH3NHNH2 by NO2 (R1) and related reactions have been investigated theoretically by using B97X-D and CCSD(T)-F12 quantum chemical calculations and the steady-state unimolecular master equation analysis based on Rice-Ramsperger-Kassel-Marcus (RRKM) theory. For reaction (R1), both dissociation and isomerization steps between intermediate complexes were found to be important for the distribution of the dissociated bimolecular products. The dominant products of (R1) were found to be cis-CH3NHNH and HONO at lower temperature. The branching ratios for CH3NNH2 formation paths increased with increasing temperature. On the same reaction potential energy surface, six reactions including isomerization reactions between CH3NNH2 and cis-/trans-CH3NHNH catalyzed by HONO were suggested to compete with the reverse reaction of (R1). The temperature- and pressure-dependent rate expressions are proposed for kinetic modeling. - Yu Daimon, Hiroshi Terashima, Mitsuo KoshiJOURNAL OF PROPULSION AND POWER 30 3 707 - 716 2014年05月 [査読有り][通常論文]

A detailed chemical kinetic mechanism for hypergolic ignition of N2H4 in a N2O4-NO2 gas mixture has been constructed. In this mechanism, the hypergolic ignition is mainly caused by the sequential reactions of H atom abstraction from N2Hm by NO2: N2Hm + NO2 = N2Hm-1 HONO/HNO2 (m = 4 similar to 1). Although the first step of the H atom abstraction (m = 4) is endothermic, consecutive abstraction reactions for m = 3, 2, and I are exothermic, and especially heat release by the reaction of N2H + NO2 = N-2 + HONO(m =1) is large because of N-2 production. Temperature rise caused by the heat release accelerates the endothermic initiation reaction (m = 4). This thermal feedback is responsible for the hypergolic ignition at low temperatures. Because no experimental and theoretical information is available on these reactions, rate coefficients were evaluated on the basis of transition state theory, unimolecular rate theory, and master equation analysis with quantum chemical calculations of potential energy curves. In addition, reactions of N2H4 with N2O4 isomers were also examined. The present kinetic mechanism can explain gas-phase hypergolic ignition of N2H4/NTO mixtures at temperatures down to 200 K. - Hiroshi Terashima, Mitsuo Koshi, Chika Miwada, Toshio Mogi, Ritsu DobashiINTERNATIONAL JOURNAL OF HYDROGEN ENERGY 39 11 6013 - 6023 2014年04月 [査読有り][通常論文]

A two-dimensional (2-D) simulation of spontaneous ignition of high-pressure hydrogen in a length of duct is conducted to explore ignition mechanisms. The present study adopts a 2-D rectangular duct and focuses on effects of the initial diaphragm shape on spontaneous ignition. The Navier-Stokes equations with a detailed chemical kinetics mechanism are solved in a manner of direct numerical simulation. The detailed mechanisms of spontaneous ignitions are discussed for each initial diaphragm shape. For a straight diaphragm, ignition only occurs near the wall owing to the adiabatic wall condition, while three ignition events are identified for a greatly deformed diaphragm: ignition due to reflection of leading shock wave at the wall, hydrogen penetration into shock-heated air near the wall, and deep penetration of hydrogen into shock-heated air behind the leading shock wave. Copyright (C) 2014, Hydrogen Energy Publications, LLC. Published by Elsevier Ltd. All rights reserved. - Youhi Morii, Hiroshi Terashima, Mitsuo Koshi, Taro Shimizu, Eiji Shima50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 2014年 [査読有り][通常論文]

© 2014 by authors. Published by the American Institute of Aeronautics and Astronautics, Inc. A simple yet robust and fast time integration method is proposed for efficiently solving stiff chemical kinetic ordinary differential equations. The proposed method is based on a general formula which preserves the conservation laws for any integration operators con- structed using the Lagrange multiplier method. A quasi-steady-state approxixmation is used as the integrator. The time step size is automatically controlled by using a Lagrange multiplier so that the error, which is caused by the Lagrange multiplier method, is small. The results of several ignition problems demonstrate the robustness and accuracy of the proposed method in comparison with other integration methods such as a implicit inte- gration method (VODE), a multi time-scalse method (MTS), and a modified CHEMEQ2. The proposed method, named ERENA, provides the fastest performance for the most of conditions used in this study. **Numerical Study of Real Gas Effects on Shock Tube Problems**Daiki Muto, Hiroshi Terashima, Nobuyuki TsuboiTRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 ists29 Po_2_39-Po_2_44 2014年 [査読無し][通常論文]- Hiroshi Terashima, Soshi Kawai, Mitsuo KoshiComputers and Fluids 88 484 - 495 2013年12月 [査読有り][通常論文]

An interface-capturing method using a high-order central difference scheme is presented for simulations of compressible multicomponent flows. The present method adds consistent numerical diffusion terms to robustly capture interface discontinuities, while maintaining the velocity, pressure, and temperature equilibriums at interfaces. Analysis of the numerical errors generated at the interfaces leads to a proposal of new consistent numerical diffusion terms. The method solves a fully conservative form of the total mass, momentum, total energy, and species-mass, and an additional advection form of the specific heats ratio to preserve the pressure oscillation-free property at the interfaces. Several one- and two-dimensional problems are used to verify the proposed method. © 2013 Elsevier Ltd. - 寺島洋史, 越光男日本燃焼学会誌 55 174 411 - 421 2013年11月 [査読有り][通常論文]
- Hiroshi Terashima, Mitsuo KoshiJournal of Propulsion and Power 29 1328 - 1336 2013年11月 [査読有り][通常論文]

Two-dimensional planar and three-dimensional round nitrogen jets under supercritical pressures are simulated with a wide range of conditions to explore their unique characteristics. A high-order method using a sixth-order compact scheme is applied. The present study parametrically covers two supercritical pressures of 4 and 8 MPa and three jet injection temperatures between a cryogenic jet of 82Kand a warmer jet of 133 K. Unique characteristics are found in both the mean temperature and temperature fluctuation profiles on the centerline (i.e., slower increase of jet temperature and relatively weak temperature fluctuation), only in the case of a near-critical pressure of 4 MPa and a cryogenic jet of 82 K. For the condition, the temperature profile on the centerline uniquely consists of four characteristic regions. The other conditions show no distinct features. The present study suggests that the distributions of the specific heat capacity at constant pressure help to explain the generation of the unique temperature characteristics. Copyright © 2013 by the von Karman Institute for Fluid. - Chihiro Inoue, Mitsuo Koshi, Hiroshi Terashima, Takehiro Himeno, Toshinori WatanabeScience and Technology of Energetic Materials 74 106 - 111 2013年11月 [査読有り][通常論文]

The physics behind the beauty of sparkling fireworks has not been clarified yet due to a lack of detailed visualization results. In the present study, atomization process in sparkling fireworks is elucidated by using a high-speed video camera. In the first-half sequence of the fireworks, the fireball repeatedly expands, bursts, and shrinks due to the high pressure gas inside the fireball. In contrast, in the last-half sequence, the bubbly fireball slightly deforms, and small bubbles burst on the fireball. A scenario of droplets generation is as follows : a liquid thread extends from the bottom of the bursting fireball, and fragments into droplets. Thus the droplets originate from inside the fireball rather than from its surface. - Hiroshi Terashima, Mitsuo KoshiComputers and Fluids 85 39 - 46 2013年10月 [査読有り][通常論文]

This study presents a strategy for simulations of cryogenic single-species jets under supercritical pressure conditions. In this strategy, a pressure evolution equation is introduced and numerical diffusion terms are consistently constructed in order to maintain the pressure and velocity equilibriums at fluid interfaces. By taking the idea of the equilibrium, the interfaces with high density and temperature ratio are robustly captured without the generation of spurious oscillations, while a high-order central differencing scheme resolves the flow fields. The present method preserves the mass and momentum conservation properties, while the poor energy conservation property is recognized. The one-dimensional interface advection and two-dimensional cryogenic jet mixing problems demonstrate the superiority and robustness of the present method over a conventional fully conservative approach. © 2012 Elsevier Ltd. - 井上 智博, 越 光男, 寺島 洋史, 姫野 武洋, 渡辺 紀徳Science and Technology of Energetic Materials : journal of the Japan Explosive Society 74 3 106 - 111 火薬学会 2013年08月 [査読有り][通常論文]
- Yu Daimon, Hiroshi Terashima, Mitsuo KoshiScience and Technology of Energetic Materials 74 17 - 22 2013年07月 [査読有り][通常論文]

Hydrazine (N2H4) has a unique characteristic inducing hypergolic ignition even at very low temperatures with nitrogen dioxide (NO2). In order to understand the chemical kinetic origin of this hypergolic nature, thermochemical data (heat of formation, specific heat capacity, and entropy) for chemical species relevant to N2H 4/NO2 combustion are firstly evaluated on the basis of quantum chemical calculation at the CBS-QB3 level of theory. Then, a preliminary detailed chemical kinetic mechanism for gas-phase combustion of N 2H4/NO2 mixtures has been constructed. Kinetic simulations indicated that sequential reactions of N2H m+NO2 (m=4,3,2,l), that is, N2H 4+NO2=N2H3+HONO (1), N 2H3H-NO2=N2H3NO 2= N2H2H-HONO (2), N2H 2+NO2=NNH+HONO (3), and NNH+NO2=N 2+HONO (4), are responsible for the hypergolic ignition at low temperatures. Rate constants of these reactions were estimated based on the transition state theory and unimolecular rate theory. The proposed mechanism can predict low temperature ignition of N2H4/NO 2mixtures. The origin of the low temperature ignition is the reaction sequence of hydrogen abstraction by NO2 from N2H 4, N2H4=>N2H3= >N2H2=>NNH=>N2, Large amount of heat is released during this reaction sequence, especially by the reaction (4) which produces N2, and the resulting temperature rise accelerates the reaction (1), which has a small activation barrier. - Hiroshi Terashima, Mitsuo KoshiJOURNAL OF COMPUTATIONAL PHYSICS 231 20 6907 - 6923 2012年08月 [査読有り][通常論文]

This study proposes an approach for simulations of cryogenic fluid mixing under supercritical pressures using high-order schemes. In this approach, we introduce a pressure evolution equation and consistently construct numerical diffusion terms to maintain the velocity and pressure equilibriums at fluid interfaces. The interfaces with high density and temperature ratio are successfully captured without the generation of spurious oscillations, while a high-order central differencing scheme resolves the flow fields. The present method preserves the mass and momentum conservation properties, while the poor energy conservation property is recognized. The one-dimensional single and multi-species interface advection and two-dimensional cryogenic jet mixing problems demonstrate the superiority and robustness of the present method over a conventional fully conservative method. (C) 2012 Elsevier Inc. All rights reserved. - Taku Nonomura, Seiichiro Morizawa, Hiroshi Terashima, Shigeru Obayashi, Kozo FujiiJOURNAL OF COMPUTATIONAL PHYSICS 231 8 3181 - 3210 2012年04月 [査読有り][通常論文]

A weighted compact nonlinear scheme (WCNS) is applied to numerical simulations of compressible multicomponent flows, and four different implementations (fully or quasi-conservative forms and conservative or primitive variables interpolations) are examined in order to investigate numerical oscillation generated in each implementation. The results show that the different types of numerical oscillation in pressure field are generated when fully conservative form or interpolation of conservative variables is selected, while quasi-conservative form generally has poor mass conservation property. The WCNS implementation with quasi-conservative form and interpolation of primitive variables can suppress these oscillations similar to previous finite volume WENO scheme, despite the present scheme is finite difference formulation and computationally cheaper for multi-dimensional problems. Series of analysis conducted in this study show that the numerical oscillation due to fully conservative form is generated only in initial flow fields, while the numerical oscillation due to interpolation of conservative variables exists during the computations, which leads to significant spurious numerical oscillations near interfaces of different component of fluids. The error due to fully conservative form can be greatly reduced by smoothing interface, while the numerical oscillation due to interpolation of conservative variables cannot be significantly reduced. The primitive variable interpolation is, therefore, considered to be better choice for compressible multicomponent flows in the framework of WCNS. Meanwhile better choice of fully or quasi-conservative form depends on a situation because the error due to fully conservative form can be suppressed by smoothed interface and because quasi-conservative form eliminates all the numerical oscillation but has poor mass conservation. (C) 2012 Elsevier Inc. All rights reserved. **APPROACH TO PREVENT SPURIOUS OSCILLATIONS IN COMPRESSIBLE MULTICOMPONENT FLOWS USING HIGH-ORDER METHODS**Hiroshi Terashima, Soshi Kawai, Mitsuo KoshiPROCEEDINGS OF THE ASME FLUIDS ENGINEERING DIVISION SUMMER MEETING, 2012, VOL 1, PTS A AND B, SYMPOSIA 635 - 643 2012年 [査読有り][通常論文]

We present an interface-capturing method for fluid interfaces in compressible multicomponent flows using high-order central-difference-based schemes. Numerical diffusion terms are consistently designed so that the velocity, pressure, and temperature equilibriums are maintained at the fluid interfaces, while serving as an efficient interface-capturing. Advection problems of a contact discontinuity and a material interface shows that 1) the present method maintains the velocity, pressure, and temperature equilibriums at the fluid interfaces (oscillation-free property) and 2) the numerical diffusion terms effectively works for suppressing spurious wiggles of the density or temperature. Comparisons with a conventional fully-conservative approach demonstrates the superiority of the present method in avoiding spurious oscillations. A shock tube problem of two-component gases shows the capability for capturing the shock wave while the velocity and pressure equilibriums are successfully maintained at the contact discontinuity.- Hiroshi Terashima, Soshi Kawai, Nobuhiro YamanishiAIAA JOURNAL 49 12 2658 - 2672 2011年12月 [査読有り][通常論文]

A high-resolution methodology using a high-order compact differencing scheme with localized artificial diffusivity is introduced with the aim of simulating jet mixing under supercritical pressure environments. The nonlinear localized artificial diffusivity provides the stability to capture different types of discontinuity, such as shock wave, contact surface, and material interface, whereas the high-order compact difference scheme resolves broadband scales in the rest of the domain. The present method is tested on several one-dimensional discontinuity-related problems under super/transcritical conditions and a comparatively more illustrative two-dimensional low-temperature planar jet problem under a supercritical pressure condition. The localized artificial diffusivity, especially artificial thermal conductivity for temperature gradients, effectively suppresses numerical wiggles near the interfaces. The effects of the artificial thermal conductivity on numerical stability and accuracy are examined. Comparisons between the present method and a conventional low-order scheme demonstrate the superior performance of the present method for resolving a wide range of flow scales while successfully capturing large density/temperature variations at interfaces. - Soshi Kawai, Hiroshi TerashimaINTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS 66 10 1207 - 1225 2011年08月 [査読有り][通常論文]

A simple methodology for a high-resolution scheme to be applied to compressible multicomponent flows with shock waves is investigated. The method is intended for use with direct numerical simulation or large eddy simulation of compressible multicomponent flows. The method dynamically adds non-linear artificial diffusivity locally in space to capture different types of discontinuities such as a shock wave, contact surface or material interface while a high-order compact differencing scheme resolves a broad range of scales in flows. The method is successfully applied to several one-dimensional and two-dimensional compressible multicomponent flow problems with shock waves. The results are in good agreement with experiments and earlier computations qualitatively and quantitatively. The method captures unsteady shock and material discontinuities without significant spurious oscillations if initial start-up errors are properly avoided. Comparisons between the present numerical scheme and high-order weighted essentially non-oscillatory (WENO) schemes illustrate the advantage of the present method for resolving a broad range of scales of turbulence while capturing shock waves and material interfaces. Also the present method is expected to require less computational cost than popular high-order upwind-biased schemes such as WENO schemes. The mass conservation for each species is satisfied due to the strong conservation form of governing equations employed in the method. Copyright (C) 2010 John Wiley & Sons, Ltd. - Hiroshi Terashima, Gretar TryggvasonCOMPUTERS & FLUIDS 39 10 1804 - 1814 2010年12月 [査読有り][通常論文]

A front-tracking method for compressible multi-fluid flows is presented, where marker points are used both for tracking fluid interfaces and also for constructing the Riemann problem on the interfaces. The Riemann problem between the two fluid phases (defined in the interface normal direction) is solved using the exact Riemann solver on the marker points. The solutions are projected onto fixed grid points and then extrapolated into the corresponding ghost-fluid regions, to be used as boundary conditions. Each fluid phase is solved separately as in the ghost-fluid method. The proposed procedures, especially the projection of the exact Riemann solutions onto the fluid grids, are designed to be simple and consistent in any spatial dimensions. Several multi-fluid problems, including the breakup of a water cylinder induced by the passage of a shock wave were computed in order to demonstrate the capability of the proposed method. (C) 2010 Elsevier Ltd. All rights reserved. - Hiroshi Terashima, Gretar TryggvasonJOURNAL OF COMPUTATIONAL PHYSICS 228 11 4012 - 4037 2009年06月 [査読有り][通常論文]

A front-tracking/ghost-fluid method is introduced for simulations of fluid interfaces in compressible flows. The new method captures fluid interfaces using explicit front-tracking and defines interface conditions with the ghost-fluid method. Several examples of multi-phase flow simulations, including a shock-bubble interaction. the Richtmyer-Meshkov instability, the Rayleigh-Taylor instability, the collapse of an air bubble in water and the breakup of a water drop in air, using the Euler or the Navier-Stokes equations, are performed in order to demonstrate the accuracy and capability of the new method. The computational results are compared with experiments and earlier computational studies. The results show that the new method can simulate interface dynamics accurately, including the effect of surface tension. Results for compressible gas-water systems show that the new method can be used for simulations of fluid interface with large density differences. (C) 2009 Elsevier Inc. All rights reserved. - Hiroshi Terashima, Kozo FujiiAIAA JOURNAL 45 1 237 - 246 2007年01月 [査読有り][通常論文]

Transonic and supersonic flutter characteristics of a delta wing configuration with external stores were computationally simulated, and the aerodynamic influence of the stores on the flutter characteristics was investigated. Delta wings with one and two external stores were considered. Unsteady aerodynamics of the wing with external stores were evaluated using Navier-Stokes equations, and equations of motion based on a modal approach were applied to the structural dynamics. These equations were,coupled using a subiteration approach. The computational results showed that the flutter dynamic pressures were reduced for a wide range of Mach numbers when the external stores were attached. The flutter dynamic pressures also decreased as the number of external stores increased. In the case of one external store, the aerodynamic influence of the store could be divided into two regions according to the Mach number. It was found that neglecting the aerodynamic influence of the store led to an overestimation of the flutter dynamic pressures in the supersonic flow region. In the case of two external stores, the aerodynamic influence of the stores on the flutter boundary appeared only at one supersonic Mach number, unlike the case of one external store. Additional flutter analysis using a different store size and unsteady aerodynamic analysis with forced oscillations indicated that the interference position of the shock wave generated ahead of the external store on the lower surface was a key factor in determining the flutter boundary, and the shock wave oscillation may have acted as a negative damping on the wing motion. - 寺島 洋史, 藤井 孝藏日本機械学會論文集. B編 = Transactions of the Japan Society of Mechanical Engineers. B 71 712 2856 - 2863 一般社団法人日本機械学会 2005年12月 [査読有り][通常論文]

One criterion that determines time stepping size in the implicit time integration method is given for accurate and effective transonic flutter simulations. Transonic flows over two-dimensional forced oscillating air foils with several reduced frequencies are first investigated for constructing a criterion for selecting the time stepping size, and then two and three-dimensional transonic flutter simulations are performed for evaluating the criterion. Results for the forced oscillating airfoil indicate that unsteady aerodynamic forces converge in a constant value as the time stepping size decreases and the time stepping size required the convergence of unsteady aerodynamic force depends on the reduced frequency. From these results, it turns out that 4000 integration steps during one cycle of airfoil oscillations are enough for the estimation of the unsteady aerodynamic forces at any reduced frequency. The time stepping size is automatically decided by setting 4000 integration steps during one cycle of airfoil oscillations. Results for two and three-dimensional transonic flutter simulations show that flutter boundaries can be accurately and effectively calculated based on the criterion.

- Shun Murakami, Hiroshi Terashima, Nobuyuki OshimaAIAA Scitech 2019 Forum 2019年01月© 2019 by Timothy K. Minton. Published by the American Institute of Aeronautics and Astronautics, Inc. A computational study is performed for exploring flow and flame dynamics of a high-pressure hydrogen/oxygen coflow jet with the effects of post thickness and moment flux ratio. A two-dimensional model with a splitter plate, which represents a post configuration of an injector of rocket engines, is adapted to fully resolve the combustion flow field. The compressible Navier-Stokes equations are solved with a detailed chemical kinetic mechanism in a manner of direct numerical simulation. The result shows that the post thickness largely affects the temperature distribution in a recirculation region established behind the post. The temperature distribution is determined with the amount of incoming high-temperature combustion gas and unburned hydrogen gas, which significantly changes with the post thickness. The effect of the momentum flux ratio clearly appears in the case of thicker post configuration, while in the case of thinner post configuration no major differences are identified for all the momentum flux ratio. The study shows a tendency that thicker post geometries with smaller J numbers provide lower temperature fields in the recirculation region behind the post, thus preliminarily indicating some difficulty of maintaining a flame anchoring in the recirculation region.
- 定容容器におけるエンドガス局所自着火現象の可視化 [通常講演]藤田晴彦, 伊藤祐太朗, 山田眞平, 下栗大右, 佐藤伴音, 寺島洋史, 河野通治, 本田雄哉, 植木義治, 横畑英明日本伝熱シンポジウム講演論文集(CD-ROM) 2017年
- 柔軟構造体に対する再突入ブラックアウトの数値解析 [通常講演]榎尚也, 松永学, 高橋裕介, 寺島洋史, 大島伸行流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2017年
- 大橋達志, 松永学, 高橋裕介, 寺島洋史, 大島伸行流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2017年
- Numerical simulation for effects of pressure on cryogenic coaxial jet under supercritical pressure [通常講演]Takahide Araki, Daiki Muto, Hiroshi Terashima, Nobuyuki TsuboiAIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting 2017年01月© 2017 by Rolls-Royce North America Holdings Inc. Three-dimensional numerical simulations of coaxial nitrogen jet mixing under supercritical pressures are performed with an emphasis on the effects of pressure on the mixing. The results show that the overall mixing behaviors are similar in terms of normalized density profiles between 5 and 12 MPa. However, the normalized temperature profiles are different between two conditions because non-linear change of the density to the temperature near the critical point. The peak of the constant pressure specific heat is particularly observed in the case of 5 MPa. The density and temperature fluctuations become large between the inner jet flow and the outer jet flow. Although the density fluctuation distributions are similar between two cases, the larger fluctuation region of temperature is observed in the case of 5 MPa. This is because the temperature increases are different near the critical temperature between two pressure conditions.
- ノッキング現象におけるホットスポットの源について [通常講演]寺島洋史, 松木亮燃焼シンポジウム講演論文集 2016年11月
- 佐藤伴音, 寺島洋史, 大島伸行燃焼シンポジウム講演論文集 2016年11月
- 寺島洋史, 大門優日本機械学会熱工学コンファレンス講演論文集(CD-ROM) 2016年
- 超臨界圧力下における極低温同軸噴流への噴射条件の影響 [通常講演]武藤大貴, 武藤大貴, 寺島洋史, 坪井伸幸数値流体力学シンポジウム講演論文集(CD-ROM) 2016年
- Hiroumi Tani, Yutaka Umemura, Yu Daimon, Hiroshi Terashima, Mitsuo Koshi54th AIAA Aerospace Sciences Meeting 2016年01月© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved. The vaporization and burning of the N 2 H 4 and NTO droplets were simulated with the interface-tracking method to accurately explore the auto-ignition processes and the flame structures. The N 2 H 4 vapor plume developed behind the N 2 H 4 droplet and reacted with the ambient NO 2 gas through the hydrogen abstraction reactions. Thus, the N 2 H 4 vapor and NO 2 gas mixtures behind the droplet were preheated and reached the auto-ignition at a few ms. The auto-ignition occurred in the multiple points almost at the same time. After the ignition, the premixed flame developed around the droplet. Thus, the vaporization of the liquid N 2 H 4 near the surface became significant. Then, the double flame structures which comprise the inner decomposition flame and oxidation flame appeared around the droplet. The NTO droplet was not auto-ignited in the computational time of the present study because little N 2 O4 vapor near a saturated temperature decomposed to NO 2 gas which is necessary for the hydrogen abstraction reactions. When the ignition was forced, the double flames developed. The outer decomposition flame propagated to the boundaries of the computational domain, while the inner oxidation flame appeared near the droplet. Except for the propagation of the decomposition flame, the NTO droplet combustion was similar to that of the industrial fuels.
- Daiki Muto, Hiroshi Terashima, Nobuyuki Tsuboi54th AIAA Aerospace Sciences Meeting 2016年01月© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Three-dimensional numerical simulations of cryogenic coaxial jets under supercritical pressure are performed with flushed and recessed injectors to investigate the effect of a recess on the coaxial mixing. A hybrid ILES/RANS method is applied to simulate wallbounded injectors and a recessed region. The recessed injector enhances the density decay and the temperature increase on the central axis, indicating the improvement of mixing compared with the flushed injector. However, the mixing improvement by the recess is not significant in the present conditions. The recess also induces distinct vortex rings around the outer jet. The power spectra of the velocity fluctuations also demonstrated that the low-frequency velocity fluctuations are clearly induced by the recess which frequency corresponds to the large vortex structures.
- Yu Daimon, Hiroumi Tani, Hiroshi Terashima, Mitsuo Koshi54th AIAA Aerospace Sciences Meeting 2016年01月© 2016 by the American Institute of Aeronautics, and Astronautics, Inc. All rights reserved. Hydrazine (N 2 H 4 )/nitrogen dioxide (NO 2 ) un-like doublet impinging gas jets were simulated to explore the hypergolic ignition processes in a N 2 H 4 /N 2 O4 bipropellant thruster. The three-dimensional compressible Navier-Stokes equations with a detailed chemical kinetics mechanism, in which more than 200 chemical reactions were directly taken into account, were solved to reveal the influence of the chemical reaction. The differences of three-dimensional structures of hypergolic ignition process and mechanism of flame holding between the two different inlet gas temperatures of 400 and 600 K were discussed in order to investigate the influence of the induction time of chemical reaction on the three-dimensional flowfield. The computed results clarified that the ignition time of impinging gas jets can be significantly influenced by the ignition delay of the detailed chemical kinetics mechanism. In addition, the intermittent multi-ignitions played a significant role in the mechanism of flame holding.
- H. Terashima, Y. Daimon52nd AIAA/SAE/ASEE Joint Propulsion Conference, 2016 2016年01月© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. A two-dimensional detailed numerical simulation is performed for combustion flow field of a GCH4/GOX single injector using detailed chemical kinetics with the compressible Navier-Stokes equations. A detailed mechanism of CH4, 33 chemical species and 150 re- actions, is efficiently and directly introduced. The result shows that the relatively high- temperature and CH4-rich recirculation region is established in the upper and lower corners of the combustion chamber. The result, with a at inlet profile, interestingly shows the generation of an unstable combustion mode, which is not observed with a smooth inlet pro- file. It is shown that the disappearance of non-premixed flames behind the GOX post is a trigger for the unstable combustion mode through the production of partly premixed gases and the generation of autoignition at several locations in the combustion chamber, which may be caused by the extent of the incursion of GCH4 and GOX jets in the recirculation region behind the GOX post.
- Daiki Muto, Nobuyuki Tsuboi, Hiroshi Terashima53rd AIAA Aerospace Sciences Meeting 2015年01月© 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. The effects of the injector geometries on co-flowing planar cryogenic jet mixings under a supercritical condition are numerically investigated. The present study focuses the recess of the coaxial injector which is widely applied in practical liquid rocket engines. The present numerical method applies an ILES/RANS hybrid method to simulate the jet mixing in the wall-bounded recessed region. As a validation of the present method, a mono-planar jet and a round jet simulations are carried out, and the results agree well with an experimental result. To examine the effects of the recess length on the coaxial injections, two-dimensional co-planar jet simulations at the supercritical pressure are performed in three recess lengths. The recessed cases show the strong flapping motions of the high densty jet, and as a result, the injected fluids are mixed well compared with the case without the recess. While there is a small difference on the potential core length between the cases without the recess and the shorter recess, the longer recess case largely shortens the jet core.
- Hiroumi Tani, Hiroshi Terashima, Ryoichi Kurose, Tomoaki Kitano, Mitsuo Koshi, Yu Daimon53rd AIAA Aerospace Sciences Meeting 2015年01月© 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Hydrazine (N 2 H 4 ) spray/gaseous nitrogen tetroxide (NTO) co-flowing jets were simulated to explore the hypergolic combustion flows in N 2 H 4 /NTO bipropellant thrusters. The Navier-Stokes equations with the use of a detailed chemical kinetics mechanism and dispersed droplets with evaporation models were solved in a manner of direct numerical simulations. The influence of the evaporation of N 2 H 4 droplets upon the hypergolic ignition processes and flame structures was investigated. Before the auto-ignition, the N 2 H 4 vapor and the ambient NTO gas mixtures were preheated as a result of the hydrogen abstraction reactions, whereas the evaporation of the N 2 H 4 droplets decreased the temperature of the gas mixtures. When the temperature of the NTO flows was sufficiently high, the N 2 H 4 vapor and NTO gas mixtures were preheated and could auto-ignite near the leading edge of the N 2 H 4 spray. This occurred because the heat transfer from the ambient gases to the droplets and the N 2 H 4 vapor enhanced the hydrogen abstraction reactions in the leading edge. After the auto-ignition, the double flame structure appeared, comprising the outer diffusion flames and inner decomposition flame. Interestingly, the inner decomposition flame and the N 2 H 4 vapor flow exhibited a sinusoidal behavior. This behavior was initiated by the locally expanded decomposition gases and developed by the supply of the N 2 H 4 droplets to the decomposition gases at relatively high temperatures. When the droplet size was small, the auto-ignition was not always enhanced because the temperature of the N 2 H 4 vapor and the NTO gas mixtures decreased. Furthermore, the sinusoidal behavior of the inner decomposition flame was less significant because the flame’s development depended on the temperature of the N 2 H 4 vapor and inertial mass of the droplets.
- Hiroshi Terashima, Mitsuo Koshi52nd Aerospace Sciences Meeting 2014年01月© 2014, American Institute of Aeronautics and Astronautics Inc. All rights reserved. Three-dimensional simulations for nitrogen/hydrogen mixing of a shear coaxial injector under supercritical pressures are conducted in order to investigate their mixing characteristics. A high-order numerical method based on a sixth-order compact scheme is applied. The present study parametrically covers two pressures of 4 and 8 MPa and two outer hydrogen jet conditions, while an inner nitrogen jet condition and a mixture ratio are kept to be same. The discussions on mean and fluctuation properties in addition to instantaneous flow fields are made in order to characterize mixing features for the coaxial injection. A colder outer hydrogen jet provides less mixing behavior compared to a warmer hydrogen jet, generating a longer dense-core of the inner nitrogen jet; unmixed nitrogen and hydrogen remain in downstream regions. Some unique features are found in the temperature profiles on the centerline of inner nitrogen jet as a flattened or a wave-like profile under 4 MPa, while no such unique features are not observed under 8 MPa. In the case of a warmer outer hydrogen jet, the hydrogen density show a maximum peak just after the injection because of the heat transfer to the inner nitrogen jet. The density and temperature fluctuation distributions are determined by the unique thermodynamic fluid variations around the critical temperature, and the velocity and temperature differences among two jets and chamber fluid. Finally, a clear dependence of dense-core length on the momentum flux ratio is demonstrated on comparison with experimental and computational data.
- Akira Kikusato, Kazuya Kogo, Beini Zhou, Kusaka Jin, Yasuhiro Daisho, Kiyotaka Sato, Hidefumi Fujimoto, Hiroshi Terashima, Youhi MoriiSAE Technical Papers 2014年01月Copyright © 2014 SAE International. The objective of the present study is to analyze soot formation in diesel engine combustion by using multi-dimensional combustion simulations with a parallelized explicit ODE solver. Parallelized CHEMEQ2 was used to perform detailed chemical kinetics in KIVA-4 code. CHEMEQ2 is an explicit stiff ODE solver developed by Mott et al. which is known to be faster than traditional implicit ODE solvers, e.g., DVODE. In the present study, about eight times faster computation was achieved with CHEMEQ2 compared to DVODE when using a single thread. Further, by parallelizing CHEMEQ2 using OpenMP, the simulations could be run not only on calculation servers but also on desktop machines. The computation time decreases with the number of threads used. The parallelized CHEMEQ2 enabled combustion and emission characteristics, including detailed soot formation processes, to be predicted using KIVA-4 code with detailed chemical kinetics without the need for reducing the reaction mechanism. After validating the code, diesel engine combustion was simulated to investigate combustion and emission characteristics, focusing on soot formation, growth and oxidation at different EGR ratios. To predict soot formation, a gas-phase polycyclic aromatic hydrocarbons (PAH) precursor formation model was coupled with a detailed phenomenological particle formation model, which included soot nucleation from precursors, surface growth/oxidation and particle coagulation. The results indicate that increased soot emission at high EGR ratios is mainly caused by decreased oxidation by oxygen and OH radicals because mixing fuel and gases (including oxygen and OH) has significant effects on reducing the mass of soot.
- Youhi Morii, Hiroshi Terashima, Mitsuo Koshi, Taro Shimizu, Eiji Shima50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 2014年01月© 2014 by authors. Published by the American Institute of Aeronautics and Astronautics, Inc. A simple yet robust and fast time integration method is proposed for efficiently solving stiff chemical kinetic ordinary differential equations. The proposed method is based on a general formula which preserves the conservation laws for any integration operators con- structed using the Lagrange multiplier method. A quasi-steady-state approxixmation is used as the integrator. The time step size is automatically controlled by using a Lagrange multiplier so that the error, which is caused by the Lagrange multiplier method, is small. The results of several ignition problems demonstrate the robustness and accuracy of the proposed method in comparison with other integration methods such as a implicit inte- gration method (VODE), a multi time-scalse method (MTS), and a modified CHEMEQ2. The proposed method, named ERENA, provides the fastest performance for the most of conditions used in this study.
- Daiki Muto, Nobuyuki Tsuboi, Hiroshi Terashima52nd Aerospace Sciences Meeting 2014年01月© 2014, American Institute of Aeronautics and Astronautics Inc. All rights reserved. Effects of recess on the mixing of the cryogenic coaxial jet under supercritical conditions were numerically investigated. Recessed injectors have been applied as coaxial injectors of liquid rocket engines because it is expected to improve propellant mixing and combustion efficiency. In the present study, a numerical simulation code was developed to examine jet mixing under the supercritical pressures. For validation of the present method, a two-dimensional planner jet simulation was carried out. The present result showed good agreement with an experimental result. As a preliminary study of coaxial jets, co-planner simulations were performed in a recessed case and an unrecessed case. Large-scale vortical structures were observed in the both cases, and the recessed case showed the larger struc- tures relative to the unrecessed case. This is because of the destabilization mechanism of a recessed region. These instabilities improved entrainments of ambient uid, and as a result, the enhanced jet mixing shortens the jet-core length.
- Yu Daimon, Hiroshi Terashima, Mitsuo Koshi51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 2013年08月A detailed chemical kinetic mechanism for hypergolic ignition of N2H4/NO2 gas mixture at low temperatures has been constructed. In this mechanism, the hypergolic ignition is caused by following sequential reactions of H atom abstraction from N2Hm by NO2. N2H4+ NO2= N2H3+ HONO or HNO2(R1) N2H3+ NO2= N2H2+ HONO (R2) N2H2+ NO2= N2H + HONO (R3) N2H + NO2= N2+ HONO (R4) These reactions are exothermic, especially heat release by the reaction (R4) is large because of N2 production. Temperature rise caused by the heat release accelerates the initiation reaction (R1). This 'thermal feedback' is responsible to the hypergolic ignition at ambient temperatures. Since no experimental and theoretical information was available on these reactions, rate coefficients were evaluated on the basis of transition state theory, uni-molecular rate theory, and master equation analysis with quantum chemical calculations of potential energy curves. Results of simulations by using the present mechanism including reactions (R1)-(R4) reasonably agree with existing experimental data. © 2013 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
- Hiroshi Terashima, Mitsuo Koshi51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013 2013年08月Two-dimensional planar and three-dimensional round nitrogen jets under supercritical pressures are simulated with a wide range of conditions in order to explore its unique characteristics. A high-order method using a sixth-order compact scheme is applied. The present study parametrically covers two supercritical pressures of 4 MPa and 8 MPa and three jet injection temperatures between a cryogenic jet of 82 K and a warmer jet of 133 K. Unique characteristics are found in both the mean temperature and the temperature fluctuation profiles on the centerline, i.e., slower increase of jet temperature and relatively weak temperature fluctuation, only in case of a near-critical pressure of 4 MPa and a cryogenic jet of 82 K. The temperature profile on the centerline of the cryogenic jet of 82 K under 4 MPa uniquely consists of four characteristic regions. The other conditions show no distinct features. The present study suggests that the distributions of the specific heat capacity at constant pressure help to explain the generation of the unique characteristics on the temperature. © 2013 by the authors.
- Hiroshi Terashima, Soshi Kawai, Mitsuo KoshiAmerican Society of Mechanical Engineers, Fluids Engineering Division (Publication) FEDSM 2012年12月We present an interface-capturing method for fluid interfaces in compressible multicomponent flows using high-order central-difference-based schemes. Numerical diffusion terms are consistently designed so that the velocity, pressure, and temperature equilibriums are maintained at the fluid interfaces, while serving as an efficient interface-capturing. Advection problems of a contact discontinuity and a material interface shows that 1) the present method maintains the velocity, pressure, and temperature equilibriums at the fluid interfaces (oscillation-free property) and 2) the numerical diffusion terms effectively works for suppressing spurious wiggles of the density or temperature. Comparisons with a conventional fully-conservative approach demonstrates the superiority of the present method in avoiding spurious oscillations. A shock tube problem of two-component gases shows the capability for capturing the shock wave while the velocity and pressure equilibriums are successfully maintained at the contact discontinuity. Copyright © 2012 by ASME.
- Hiroshi Terashima, Soshi Kawai, Nobuhiro Yamanishi41st AIAA Fluid Dynamics Conference and Exhibit 2011年12月Two-dimensional planar nitrogen jets in supercritical thermodynamic conditions are simulated using a high-resolution numerical method (which consists of a sixth-order compact difference scheme and a localized artificial diffusivity method) with the aim at exploring its unique characteristics. Effects of injection temperature, chamber pressure, and the equation of state on supercritical jet behaviors are investigated. Throughout the investigations, two major unique characteristics are found under the transcritical conditions. One unique characteristic are found in the mean temperature profile, as the slower increase of jet temperature, in the case of transcritical injections. The cause for the unique feature is simply explained by the corresponding temperature-density (T-ρ) diagrams. Another unique feature of supercritical jet flows appears in the generation of different flow scales. The power spectrums and the flow fields quantitatively and qualitatively show the different features of flow scales due to the injection conditions. In the transcritical injection, the production of smaller flow scales is considerably enhanced relative to the other injection cases, due to not only its higher density ratio, but also its abrupt variations (leap) of δρ/δT in the T-ρ diagrams. This study indicates, for the present conditions used, that the unique characteristics of supercritical jet flows appear in the mean temperature distributions and the generation of different flow scales, which are simply yet effectively explained by the T-ρ diagrams. © 2011 by the authors.
- 圧縮性流体中の気液界面挙動に対するフロントトラッキング法 [通常講演]寺島 洋史, TRYGGVASON Gretar微粒化シンポジウム講演論文集 = Symposium (ILASS-Japan) on Atomization 2009年12月
- Transonic aeroelastic computations of a delta wing configuration with high fidelity equations [通常講演]Hiroshi Terashima, Kenji OnoComputational Fluid Dynamics 2006 - Proceedings of the Fourth International Conference on Computational Fluid Dynamics, ICCFD 2006 2009年01月
- Hiroshi Terashima, Kenji Ono2007 Proceedings of the 5th Joint ASME/JSME Fluids Engineering Summer Conference, FEDSM 2007 2007年12月A compressible flow solver coupled with moving/deformed geometries on Cartesian grid with Signed Distance Field (SDF) is developed and its capability is investigated through computations of several basic flow fields for future applications with certain reliability. The flow solver is designed so that SDF includes sufficient geometrical information to compute flow fields. Since information of moving/deformed geometries is recognized as a change of the SDF between time steps, the flow solver can be coupled with moving/deformed geometries naturally. The implementation of this solver is simple and easy. No modification is needed in the main part of the flow solver. Furthermore, the interpolation and the corresponding stencils searching process are not required. Several basic flow fields around fixed/moving cylinders and a fixed sphere are computed in order to validate the proposed solver, in which the computed results are compared with available numerical and experimental results. The results demonstrated the method's capability for moderate Reynolds number flows around both of fixed and moving geometries. Based on the results, some criteria and problems for obtaining reliable solution are suggested. Copyright © 2007 by ASME.
- Effects of number of stores on the transonic flutter characteristics of a delta wing configuration [通常講演]Hiroshi Terashima, Kozo Fujii34th AIAA Fluid Dynamics Conference and Exhibit 2004年12月Transonic and supersonic flutter characteristics of a delta wing configuration with external stores are simulated using the fluid/structure coupling method and the effect of the store aerodynamics is investigated. A delta wing with one and two external stores are considered in this study. The stores are located in the rearward of the wing simulating typical high speed aircraft configurations. The computational result shows that the flutter dynamic pressures over all the Mach numbers are reduced by adding external stores for both cases. In addition, the flutter dynamic pressures become much lower when the number of attached external stores is increased. In the case of the single external store, influence of the store aerodynamics can be divided into two regions according to the Mach number. It is found that neglecting the store aerodynamics leads to the overestimation of the flutter dynamic pressures in the supersonic region. In case of two external stores, the store aerodynamics influence on the flutter boundary only at M∞ = 1.22 unlike the case of the single external store. It is shown that the shock wave ahead of the external store influences on the pressure distributions on the lower surface and the location of the shock wave is important for the decision of the flutter boundary. © 2004 by the American Institute of Aeronautics and Astronautics, Inc.
- 寺島 洋史, 藤井 孝藏年次大会講演論文集 : JSME annual meeting 2002年09月Flutter phenomena for the AGARD445.6 standard aeroelastic wing in the transonic flow are simulated using the fluid/structure coupling method. The effect of time accuracy, number of the inner-iterations and comparison of a fully implicit coupling method with a loosely coupling method are examined. The sufficient number of inner-iterations in time is required for the accurate prediction of time responses when using a large time step. Improvement of the solution time accuracy for the aerodynamic equations is key for accurate aeroelastic computations and the one-step time lag generated in a loosely coupling method does not have an effect in the flutter prediction in transonic flows.
- 藤井 孝蔵, 守屋 公一郎, 寺島 洋史, 堀江 俊行流体工学部門講演会講演論文集 2001年09月CFD simulations using three-dimensional compressible Navier-Stokes equations are carried out for the establishment of the reliability of the CFD tools for the aerodynamic evaluation of space transportation systems. Simulations for Apollo-type capsule show that the simulations with typical number of grid points can give us reasonable result and CFD analysis can be a useful tool for the initial estimation of aerodynamic characteristics. Simulations for the FTB configuration show the dependency of the aerodynamic data on the order of accuracy of the simulations. The flow field near the base alters the characteristics. The example for the delta and double-delta wings which may be a candidate for the future TSTO systems shows that the success of the CFD simulations for delta wings does not necessarily justify the CFD results for similar configurations.
- Satoru Yamamoto, Hiroshi TerashimaFluids 2000 Conference and Exhibit 2000年12月Unsteady three-dimensional hypersonic shock/shock interference flows measured by Berry and Nowak1 are calculated using the shock-vortex capturing method with and without thermochemical nonequilibrium effect. This method contains the 4th-order compact MUSCL TVD scheme, the maximum 2nd-order LU-SGS scheme, and the AUSM-based scheme. Two typical 3-D flows around the forward swept fin at the angle of 0° and -15° are first calculated without reaction. The flow pattern and the shock heating on the body surface are well compared with the experiments. These 3-D flows specified by a high temperature condition are also calculated for resolving the effect of thermochemical nonequilibrium. The two-temperature model based on the Park model is employed for the chemical reaction model. The calculated results show that the increase of temperature changes the type of shock interference because of decreasing the shock standoff distance and also suggest that the shock heating might be very sensitive to the type of shock interference. Finally, unsteady flow characteristics captured both with and without thermochemical nonequilibrium effect are preliminarily expressed. © 2000 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

- Takahide Araki, Daiki Muto, Hiroshi Terashima, Nobuyuki Tsuboi AIAA SciTech Forum - 55th AIAA Aerospace Sciences Meeting 2017年01月01日 [査読無し][通常論文]

© 2017 by Rolls-Royce North America Holdings Inc. Three-dimensional numerical simulations of coaxial nitrogen jet mixing under supercritical pressures are performed with an emphasis on the effects of pressure on the mixing. The results show that the overall mixing behaviors are similar in terms of normalized density profiles between 5 and 12 MPa. However, the normalized temperature profiles are different between two conditions because non-linear change of the density to the temperature near the critical point. The peak of the constant pressure specific heat is particularly observed in the case of 5 MPa. The density and temperature fluctuations become large between the inner jet flow and the outer jet flow. Although the density fluctuation distributions are similar between two cases, the larger fluctuation region of temperature is observed in the case of 5 MPa. This is because the temperature increases are different near the critical temperature between two pressure conditions. - 越光男, 寺島洋史, 谷洋海, 大門優 衝撃波シンポジウム講演論文集(CD-ROM) 2016 ROMBUNNO.TOKUベTSUKOEN II 2017年 [査読無し][通常論文]
- KANNO Nozomu, KANNO Nozomu, KANIE Yuto, TANI Hiroumi, DAIMON Yu, TERASHIMA Hiroshi, KOSHI Mitsuo 航空原動機・宇宙推進講演会講演論文集(CD-ROM) 56th ROMBUNNO.AJCPP2016‐055 2016年 [査読無し][通常論文]
- TANI Hiroumi, UMEMURA Yutaka, DAIMON Yu, TERASHIMA Hiroshi, KOSHI Mitsuo 航空原動機・宇宙推進講演会講演論文集(CD-ROM) 56th ROMBUNNO.AJCPP2016‐134 2016年 [査読無し][通常論文]
- 大門優, 谷洋海, 寺島洋史, 菅野望, 越光男, 根岸秀世 シミュレーション 34 (3) 180 -185 2015年09月15日 [査読無し][通常論文]
- 森井 雄飛, 寺島 洋史, 越 光男, 清水 太郎, 嶋 英志 ながれ : 日本流体力学会誌 34 (2) 131 -135 2015年04月25日 [査読無し][通常論文]
- 谷洋海, 寺島洋史, 越光男, 大門優 宇宙航空研究開発機構特別資料 JAXA-SP- (14-010) 75 -80 2015年03月25日 [査読無し][通常論文]
- Hiroshi Terashima, Mitsuo Koshi JOURNAL OF COMPUTATIONAL PHYSICS 283 609 -610 2015年02月 [査読無し][通常論文]
- Daiki Muto, Nobuyuki Tsuboi, Hiroshi Terashima 53rd AIAA Aerospace Sciences Meeting 2015年01月01日 [査読無し][通常論文]

© 2015 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. The effects of the injector geometries on co-flowing planar cryogenic jet mixings under a supercritical condition are numerically investigated. The present study focuses the recess of the coaxial injector which is widely applied in practical liquid rocket engines. The present numerical method applies an ILES/RANS hybrid method to simulate the jet mixing in the wall-bounded recessed region. As a validation of the present method, a mono-planar jet and a round jet simulations are carried out, and the results agree well with an experimental result. To examine the effects of the recess length on the coaxial injections, two-dimensional co-planar jet simulations at the supercritical pressure are performed in three recess lengths. The recessed cases show the strong flapping motions of the high densty jet, and as a result, the injected fluids are mixed well compared with the case without the recess. While there is a small difference on the potential core length between the cases without the recess and the shorter recess, the longer recess case largely shortens the jet core. - Daiki Muto, Nobuyuki Tsuboi, Hiroshi Terashima 52nd Aerospace Sciences Meeting 2014年01月01日 [査読無し][通常論文]

© 2014, American Institute of Aeronautics and Astronautics Inc. All rights reserved. Effects of recess on the mixing of the cryogenic coaxial jet under supercritical conditions were numerically investigated. Recessed injectors have been applied as coaxial injectors of liquid rocket engines because it is expected to improve propellant mixing and combustion efficiency. In the present study, a numerical simulation code was developed to examine jet mixing under the supercritical pressures. For validation of the present method, a two-dimensional planner jet simulation was carried out. The present result showed good agreement with an experimental result. As a preliminary study of coaxial jets, co-planner simulations were performed in a recessed case and an unrecessed case. Large-scale vortical structures were observed in the both cases, and the recessed case showed the larger struc- tures relative to the unrecessed case. This is because of the destabilization mechanism of a recessed region. These instabilities improved entrainments of ambient uid, and as a result, the enhanced jet mixing shortens the jet-core length. - 寺島洋史, 越光男, 森井雄飛 宇宙航空研究開発機構特別資料 JAXA-SP- (12-010) 49 -54 2013年03月29日 [査読無し][通常論文]
- 寺島洋史, 越光男 宇宙航空研究開発機構特別資料 JAXA-SP- (12-010) 207 -212 2013年03月29日 [査読無し][通常論文]
- 寺島洋史, 越光男 ながれ：日本流体力学誌 31 (6) 483 -486 2012年12月 [査読無し][通常論文]
**界面平衡を考慮した超臨界圧極低温流体の高精度数値解法：多成分系への展開(<特集>注目研究in 年会2012)** - 寺島 洋史, 河合 宗司, 越 光男 ながれ : 日本流体力学会誌 31 (2) 131 -139 2012年04月25日 [査読無し][通常論文]
- 武藤 大貴, 瀬戸口 彬, 坪井 伸幸, 寺島 洋史, 越 光男 日本機械学会九州支部講演論文集 2012 (65) 271 -272 2012年03月16日 [査読無し][通常論文]
- 井上 智博, 寺島 洋史, 根岸 秀世 日本航空宇宙学会誌 58 (677) 185 -191 2010年06月 [査読無し][通常論文]
- Ku Katharine, 寺島 洋史 計算工学 = Journal of The Japan Society for Computational Engineering and Science (JSCES) 9 (2) 900 -902 2004年04月30日 [査読無し][通常論文]

- 文部科学省：科学研究費補助金(基盤研究(A))研究期間 : 2011年 -2014年代表者 : 土橋 律, 越 光男, 桑名 一徳, 茂木 俊夫①爆発の発生限界(爆発限界)の予測手法の確立昨年度までに開発したN2H4/NTO混合気体の自己着火性を記述できる詳細化学反応機構に基いて，層流燃焼速度および着火遅れ時間の温度，圧力依存性に関するシミュレーションを実施した．得られた結果を用いて，N2H4/NTO混合気体の爆発限界予測を行った．②爆発被害の影響度評価手法の確立(a)火炎の不安定性解析: 爆発シミュレーションの精度を向上するために，不安定性による火炎の加速を再現できる総括反応モデルを構築した．具体的な手法としては，まず，火炎伸長が存在する場での一次元的な火炎構造を詳細反応モデルを用いた数値シミュレーションにより求め，燃焼速度の火炎伸長に対する応答性を調べた．そして，この応答性を再現できるように総括反応モデルの速度パラメータを決定した．本研究で提案する総括反応モデルを用いれば，火炎の不安定性による伝播速度の上昇を精度よく再現でき，ガス爆発事故の被害予測の精度向上につながると期待される．(b)爆発実験: 昨年度取得したデータの再現性の確認および実験データの精度向上を目的として，3m立法(27m3)のガス爆発実験を実施した．得られた火炎伝ぱに関するデータを下に流体学的不安定性の影響について調べた．火炎伝ぱの加速指数はPeclet 数が大きくなるに従って増加し，ある限界値に至る．つまり，火炎の不安定性による火炎伝ぱの加速現象は大スケールでは自己相似的に発達することが明らかになった．
- 文部科学省：科学研究費補助金(基盤研究(B))研究期間 : 2011年 -2013年代表者 : 越 光男自動車エンジンのノッキングやガスタービンの振動燃焼の解析には化学反応方程式と流体力学方程式を同時に解く事が必要であるが、燃焼反応には数百もの化学種が関与するためにこのようなシミュレーションは不可能であった。これを可能とするために、燃焼反応の特性を損なわずに解析に必要な変数の数を大幅に減少させる方法を開発した。また反応法的式の超高速積分法も開発した。これにより、化学反応と流体現象がカップリングする現象の解析が初めて可能となった。
- 文部科学省：科学研究費補助金(基盤研究(B))研究期間 : 2011年 -2013年代表者 : 坪井 伸幸, 寺本 進, 越 光男, 林 光一, 徳増 崇, 津田 伸一, 清水 和弥, 清水 太郎, 谷 洋海, 朝原 誠, 森井 雄飛高圧条件下での超臨界燃焼流体に対する熱力学的特性・流体力学的特性を明らかにするために，(1)RANS解析(2)LES解析(3)実験 を実施した．RANS解析では，単軸の極低温超臨界窒素噴流の密度分布について実験結果と比較し，妥当な結果が得られることを確認した．さらに，多化学種の質量保存式を含む流体対応の前処理法を開発し，非定常な低速酸水素剪断流における剪断層の不安定現象を捉えることに成功した．LES解析については，遷臨界混合層において擬臨界温度が乱流渦構造に与える影響は小さかった．実験については，極低温遷臨界窒素噴流における中心軸上の温度勾配は，擬臨界温度付近で緩やかになる傾向が見られた．
- 文部科学省：科学研究費補助金(若手研究(B))研究期間 : 2011年 -2012年代表者 : 寺島 洋史本研究では,高速流中の推進剤混合過程解明を目指し,衝撃波を含む圧縮性高速流中の流体界面挙動に対するマルチスケールシミュレーション手法の開発とその流体不安定メカニズム解明に関する研究を行った.高速流中で生じる衝撃波,それと干渉する流体界面挙動をシミュレーションするため,圧縮性流体方程式を用い,界面追跡にフロントトラッキング法を,界面境界条件にゴーストフルイド法を採用した解析法を構築した.これまでの手法に対して,界面において厳密リーマン解を求めるよう大幅な修正を施し,界面マーカー点における物理量を背景格子点に埋め込む一般的な変換手法を構築した.また,液滴崩壊により追跡できなくなったマーカー点を粒子の運動方程式へつながるフレームを検討した.密度比1000倍となる気液界面問題に適用し,実験や過去の数値解析結果との比較から精度良い結果が得られることを示した.衝撃波と液滴の干渉問題では,従来捕えることが難しいとされた液滴のストリッピングを含めた液滴崩壊現象を比較的少ない格子点で捕えることに成功した.
- 文部科学省：科学研究費補助金(若手研究(B))研究期間 : 2006年 -2008年代表者 : 寺島 洋史本研究は,AirbagやParachuteといった流体と干渉する薄膜展開構造物のダイナミクスシミュレーションを行う数値手法の開発と設計への応用を目的とする.流体解析には,大変形薄膜物体を容易かつロバストに扱うため直交格子を用い,構造解析には幾何学的非線形性を考慮した有限要素法を採用した.今年度は,直交格子を用いた流体解析手法の開発と,流体と移動剛体が連成した流体剛体連成解析手法を開発し,その信頼性を評価した.本手法は以下の特長を持つ:1)距離関数場(Signed Distance Filed : SDF)を使用2)プログラムの修正は境界条件部分のみで,オリジナルソルバーからの修正が非常に容易3)鏡面境界条件で見られる境界付近の物理量内挿処理とそれに伴う点探索処理が無い4)SDF情報の変化がダイレクトに物体移動の情報を表し,流体構造連成問題を合理的に扱える特に3)は移動変形物体を扱う際に有利な点である.直交格子の解析でしばしば問題となるのが計算結果の信頼性である.信頼性を検証するため,基本的な流れ場(円柱,球,振動円柱)のシミュレーションを行い,実験や他の計算と比較を行った.固定円柱と球の計算結果から,レイノルズ数500までではあるが,他の結果と良い一致を得た.また,格子解像度の影響を調べ,予想される境界層厚さに10点程度の格子点を配置することにより,信頼性ある解が得られることを示した.これは今後の解析における格子解像度選択の指標となる.振動円柱の解析では,SDFの変化をベースとした本手法が移動物体のシミュレーションに対して有効であることを示し,また,固定円柱の流れ場に比べ,力の振幅や位相を正確に求める上で格子解像度が重要であることを明らかにした.また,粗い格子を用いると,力の時間履歴に虚偽振動が発生することがわかった.この原因は今後の課題である.

- Advanced Fluid Engineering（流体工学E）開講年度 : 2018年課程区分 : 修士課程開講学部 : 工学院
- 流体工学特論開講年度 : 2018年課程区分 : 修士課程開講学部 : 工学院
- Introduction to Flight Dynamics(飛翔体工学E)開講年度 : 2018年課程区分 : 修士課程開講学部 : 工学院
- 飛翔体工学特論開講年度 : 2018年課程区分 : 修士課程開講学部 : 工学院
- Advanced Fluid Engineering（流体工学E）開講年度 : 2018年課程区分 : 博士後期課程開講学部 : 工学院
- 流体工学特論開講年度 : 2018年課程区分 : 博士後期課程開講学部 : 工学院
- Introduction to Flight Dynamics(飛翔体工学E)開講年度 : 2018年課程区分 : 博士後期課程開講学部 : 工学院
- 飛翔体工学特論開講年度 : 2018年課程区分 : 博士後期課程開講学部 : 工学院
- 国際交流Ⅱ開講年度 : 2018年課程区分 : 学士課程開講学部 : 国際本部
- 工業英語演習開講年度 : 2018年課程区分 : 学士課程開講学部 : 工学部キーワード : 工業英語、英文読解、英作文、英会話、プレゼンテーション、討論
- 計測工学実験開講年度 : 2018年課程区分 : 学士課程開講学部 : 工学部キーワード : 計測、温度、流速、圧力、抗力、変形、放射線、真空、統計学、データ解析
- 熱流体力学演習Ⅱ開講年度 : 2018年課程区分 : 学士課程開講学部 : 工学部キーワード : 蒸気、湿り空気、ガスサイクル、蒸気サイクル ナビエ・ストークス方程式、レイノルズ数、粘性摩擦抵抗、境界層、乱流、運動量・角運動量理論
- 流体工学開講年度 : 2018年課程区分 : 学士課程開講学部 : 工学部キーワード : 圧縮性流れ，音波，衝撃波，完全流体の力学，物体に働く力，翼理論，層流，乱流，境界層，航空機，空力，遷音速流