研究者詳細 - 河内　俊憲

講演・口頭発表等 - 河内　俊憲

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Side-Wall Effects on the Global Stability of Swept and Unswept Supercritical Wings at Buffet Conditions

SANSICA Andrea, 橋本敦, 小池俊輔, 河内俊憲, SANSICA Andrea, HASHIMOTO Atsushi, KOIKE Shunsuke, KOCHI Toshinori

宇宙航空研究開発機構特別資料: 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2020オンライン論文集 = JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online 2021年2月8日宇宙航空研究開発機構(JAXA)

凝集ナノ粒子を用いた超音速流れの可視化とPIVに関する研究

福田征弥, 柳瀬眞一郎, 河内俊憲, 永田靖典, 宮井祥真

中国四国支部総会・講演会講演論文集 2019年一般社団法人日本機械学会

後退角ありと後退角なしの2次元CRM翼における衝撃波はく離とその振動

小池俊輔, 松本葉, 河内俊憲

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) 2019年

RANSを用いた低レイノルズ数域における翼型NACA0012の二次元解析

井上佑希, 永田靖典, 河内俊憲, 柳瀬眞一郎

中国四国支部総会・講演会講演論文集 2019年一般社団法人日本機械学会

超音速電磁流体制御におけるアークジェット気流サイズの影響に関する実験的研究

市川恒士, 永田靖典, 河内俊憲, 柳瀬眞一郎

中国四国支部総会・講演会講演論文集 2019年一般社団法人日本機械学会

修正 force-coupling method を用いた二気泡間の相互作用に関する数値解析

上西雅信, 関超, 柳瀬眞一郎, 河内俊憲, 永田靖典

中国四国支部総会・講演会講演論文集 2018年一般社団法人日本機械学会

フラクタル格子乱流の熱線風速計と PIV による計測

平尾将孝, 柳瀬眞一郎, 河内俊憲, 永田靖典, 宮里健志

中国四国支部総会・講演会講演論文集 2018年一般社団法人日本機械学会

OpenFOAMによる半導体洗浄装置内流れの数値解析

柳瀬眞一郎, 青山翼, 河内俊憲, 永田靖典, 三好勇輝

流体工学部門講演会講演論文集 2018年一般社団法人日本機械学会

開催年月日： 2018年

記述言語：日本語

<p>In semiconductor production, efficiency and precision of the cleaning process are very important. In this study, we handle "Single Wafer Cleaner" that is one of the washing methods in the way of blowing air to a wafer with a turning disk at a high speed. However, the flow in the device becomes turbulent, which causes the problem that water drops and dusts re-attach to the wafer surface. Therefore, it is necessary to understand the flow in the device exactly to solve this problem. In previous studies, we experimented to establish the method of understanding the flow in the semiconductor wafer cleaner without a covering cup that is used for liquid splash preventing. In this study, numerical calculations were performed to observe the flow in the device to study influence of covering cup and find a suitable turbulence model to simulate the experiment.</p>

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ポンプ水槽内の渦構造の数値解析

柳瀬眞一郎, 山崎諒, 河内俊憲, 永田靖典, 細田駿介

流体工学部門講演会講演論文集 2018年一般社団法人日本機械学会

開催年月日： 2018年

記述言語：日本語

<p>We conducted numerical simulations of the benchmark experiments of the pump sump conducted by Matsui et al. (2006 & 2015) and compared the simulation with the experimental data to investigate the effects of turbulence model, grid density and detection method of the vortices. We determined a threshold of the gas-liquid fraction function of VOF method (α) and the second invariant of velocity gradient tensor (Q2) to detect the air-entraining and submerged vortices by using vorticity, respectively. This method well detected the vortices and well reproduced the experiments for the RANS simulation using SST k-ω model. Large eddy simulation using Smagorinsky model, however, was sensitive to the grid system and difficult to reproduce the experimental vortex structures even for the finest grid system having 3.7 mil-lion cells.</p>

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衝撃波上流域の速度変化がバフェットに及ぼす影響

山下雄輝, 河内俊憲, 小池俊輔, 柳瀬眞一郎

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

気中衝突水噴流の数値解析と実験による検証

徳善一仁, 高崎玲爾, 柳瀬眞一郎, 河内俊憲, 永田靖典

中国四国支部総会・講演会講演論文集 2017年一般社団法人日本機械学会

非定常シュリーレン計測結果に基づいたLeeの遷音速バフェットモデルの修正

河内俊憲, 山口真伍, 小池俊輔, 柳瀬眞一郎

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) 2016年

スーパークリティカル翼における衝撃波自励振動のモデル

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 2016年

Wavelet analysis of unsteady shock-wave motion on two-dimensional airfoil with vortex generators

Toshinori Kouchi, Shingo Yamaguchi, Shinichiro Yanase, Shunsuke Koike, Tsutomu Nakajima, Mamoru Sato, Hiroshi Kanda

54th AIAA Aerospace Sciences Meeting 2016年

開催年月日： 2016年

記述言語：英語

© 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved. We visualized the shock wave-boundary layer interaction on a two-dimensional transonic airfoil with and without vortex generators (VGs) by using a fast-framing focusing schlieren imaging. Image processing extracted a time-space trajectory of the shock wave motion from a time-series of the schlieren images. The shock trajectories were analyzed by using the Morlet wavelet. The shock motions in the cases without VGs were quite periodic. The Fourier analysis well extracted the characteristics of the shock motion such as frequency etc. However, the shock motions in the cases with VGs were not periodic. Therefore, the Fourier analysis is not applicable for this case. The wavelet analysis with the statistical significance test gave quantitative measure of change in the shock oscillation around the buffet frequency due to installation of VGs, such as amplitude and intermittency. The wavelet spectrograms revealed that the installation of VGs did not prevent from generating the buffet but just reduced the amplitude of the buffet oscillation.

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1215 流量一定条件を課した曲がり管内流の数値計算(流体工学IV)

益田卓哉, 永田靖典, 河内俊憲, 早水庸隆, 柳瀬眞一郎

講演論文集 2015年2月27日一般社団法人日本機械学会

遷音速二次元翼バフェットにおける衝撃波と同期する音波の解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

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) 2015年

二次元遷音速バフェットの可視化によるVortex Generatorの効果の解明

笠木信哉, 山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 2015年

二次元遷音速バフェットのウェーブレット解析-ボルテックス・ジェネレータの効果に関して-

河内俊憲, 山口真伍, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

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) 2015年

S0530102 半導体洗浄機モデル内の渦構造の時間変化([S053]内部流れ)

清水義也, 柳瀬眞一郎, 河内俊憲, 森洋平, 福田修也, 中野裕介

年次大会 : Mechanical Engineering Congress, Japan 2014年9月7日一般社団法人日本機械学会

開催年月日： 2014年9月7日

記述言語：日本語

In a single wafer spin cleaner, the wafer is rotated at high speed to spin off ultrapure water and clean air is blown perpendicular onto the surface to dry the wafer. Interaction between the rotating wafer and blown air generates vortices and the recirculation flow due to the vortices may cause reattachment of contaminants on the wafer surface. Therefore, we experimentally studied vortical structures and the conditions of their formation in a modeled cleaner by using particle image velocimetry (PIV). The model was a 330 mm diameter rotating disk in a 520 mm diameter cylindrical stationary housing, and laminar blown air came from the housing inlet onto the rotating disk. The angular speed of the rotating disk was changed up to 500 rpm and the blown air rate was 0.5 m3/min. Our PIV data show that turbulent kinetic energy near the housing wall with a vortex is as large as that around the rotating disk around at SOOrpm. This vortex may cause reattachment of particles onto the wafer. The vortices generated in the experimental apparatus have three-dimensional structures regardless of their size.

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901 粒子群を含む流れのカオス的挙動に関する数値的研究

新庄弘明, 柳瀬眞一郎, 河内俊憲

講演論文集 2014年一般社団法人日本機械学会

高速度フォーカシングシュリーレンによる二次元翼バフェットの可視化とその解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島務, 佐藤衛, 神田宏

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) 2014年

S055015 半導体洗浄機モデル内流れのPIV計測([S055-01]内部流れ(1))

清水義也, 柳瀬眞一郎, 河内俊憲, 森洋平, 福田修也

年次大会 : Mechanical Engineering Congress, Japan 2013年9月8日一般社団法人日本機械学会

開催年月日： 2013年9月8日

記述言語：日本語

The cleaning process of a silicon wafer is important in the manufacturing of semiconductors, which determines the quality of the final products crucially. In the so-called single wafer cleaning, a wafer washed with cleaning solution and rinse liquid is dried up by rotating at a high speed. We made an experimental apparatus which has a similar structure to the single wafer cleaning chamber, and measured the velocity field in the chamber by the particle image velocimetry(PI V) method.

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133 エジェクタジェットの二次燃焼効率改善を目指したPIVによる速度場計測(流体工学IV,一般講演)

野島清, 河内俊憲, 升谷五郎, 富岡定毅

講演論文集 2012年3月13日一般社団法人日本機械学会

A plasma jet assisted combustion with a backward- facing step by fuel injection locations

Chae-Hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Kenichi Takita, Goro Masuya

The 33rd International Symposium on Combustion 2010年

The Effect of a Vent Slot Mixer with a Plasma Jet Torch in the Supersonic Combustion

C. Kim, I. Jeung, B. Choi, T. Kouchi, G. Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010年

Development of Ignition Enhance Method by Using Non-Equilibrium Plasma in High Speed Flow

T. Yamamoto, Y. Matsubara, K. Takita, T. Kouchi

Asian Joint Conference on Propulsion and Power 2010年

Numerical Simulation of Pulsed Injection into a Supersonic Crossflow

K. Sasaya, J. Watanabe, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010年

Effects of Injectant Species on Compressible Tubulent Scalar Mixing Structure

Y. Horikoshi, H. Takahashi, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010年

Stereoscopic PIV Measurement of Supersonic Injection Flowfield and Its Error Analysis

S. Uramoto, S. Tsuru, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010年

Development of a New Supersonic Mixier for Dual- Mode Scramjet Engine Combustor

C. Kim, I. Jeung, B. Choi, Y. Matsubara, T. Kouchi, G. Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009年

Mechanism of mixing enhanced by pseudo-shock wave

Hideki Yamauchi, Byongil Choi, Toshinori Kouchi, Goro Masuya

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009年

開催年月日： 2009年

An experiment was conducted to investigate the mixing mechanism of a jet injected perpendicularly into a mainstream with a pseudo-shock wave (PSW). The velocity fields in the cross-sectional plane were obtained by particle-image velocimetry (PIV). Mixing of the injectant was observed by Mie scattering light of oil mist seeded in the injectant. The PSW thickened the boundary layer and reduced the momentum flux of the mainstream so the injectant penetrate higher from the wall. This affected the injectant mixing. The rd-scale model was applicable to estimate the injectant mixing in PSW by considering the flow condition just upstream of the injection jet. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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超音速流れ場における速度変動量のPIV測定

田村武, 津留真一郎, 小池俊輔, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2009年

Scalar spatial correlations in a supersonic mixing flowfield

Hidemi Takahashi, Hiroki Oso, Toshinori Kouchi, Goro Masuya, Mitsutomo Hirota

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009年

開催年月日： 2009年

Scalar spatial correlations in the supersonic mixing flowfield produced by a sonic transverse injection of air into a Mach 2.0 supersonic airstream were investigated using acetone planar laser-induced fluorescence (acetone PLIF) data. Side-view and end-view images were obtained in several planes to characterize the turbulent structure and three-dimensionality of the mixing flowfield. Single-time two-point spatial correlations of injectant concentration were obtained from the acetone PLIF data. Contour maps of the correlations indicated an organized large-scale structure in the upper region of the jet. Side-view correlation maps revealed that the shape of the large dominating structure was elliptic, and that its major axis turned from backward-leaning to forward-leaning as the reference point of correlation moved downstream. End-view correlation maps revealed that the instantaneous jet plume appeared by turns either in the top or in the lower sides of the timeaveraged injectant plume in each cross-section. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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Influence of Velocity Fields on Mixing in Pseudo-Shock Wave

Goro Masuya, Byongil Choi, Hideki Yamauchi, Toshinori Kouchi

19th ISABE conference 2009年

Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices

Sadatake Tomioka, Toshinori Kouchi, Ryo Masumoto, Muneo Izumikawa, Akiko Matsuo

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2009年

Scalar Spatial Correlations in a Supersonic Mixing Flowfield

Hidemi Takahashi, Hiroki Oso, Toshinori Kouchi, Goro Masuya

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace 2009年

Time-space trajectory of unsteady jet into supersonic crossflow using high-speed framing schlieren images

Toshinori Kouchi, Takahisa Hoshino, Keita Sasaya, Goro Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009年

開催年月日： 2009年

Supersonic transverse jet flow-field has an important role for supersonic combustor in scramjet engines. Supersonic speed induces the difficulty in unsteady measurements, because characteristics time is very short in the flow. Lacks of time-series data make the combustor difficult to develop. To investigate the jet unsteady motion, high-speed framing camera captured 100 successive schlieren images of the supersonic transverse jet flow-field with 250 kHz sampling rate. The mainstream Mach number was 2.0 and the injectant was helium gas, simulating fuel hydrogen. This work revealed the effects of density-weighted jetto-crossflow velocity ratio (blowing ratio: r) and the injector diameter (D) on the motion of the jet boundary. Newly suggested image processing, based on the Sobel spatial filter, efficiently tracked the jet boundary from the time-series schlieren images. 2700 sample data gave the probability density function (PDF) of the jet boundary. The PDF distributions indicated the jet penetration was insensitive to both r and D in rD space. The jet spreading, however, was sensitive to both r and D even in rD space. This was due the compressibility effect generated at the near field of injector. Remapping the time-series jet boundary as the time-space jet trajectory indicated the convective velocity of the large eddies in the jet was insensitive to r and D. It was constant of 460 m/s. The map gave us another important information on the jet motion: cycle of high-penetrated eddy formation in the jet. Spectrum analysis of the time-space jet trajectory investigated the shedding frequencies of highpenetrated eddy in the transverse jet. As the results, we find out that the high-penetrated eddy occurred at comparatively various frequencies. The specific amplified frequency of the jet instability probably did not exist at the far field of supersonic transverse injection. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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Combustion performance of supersonic combustor with stinger-shaped fuel injector

T. Kouchi, K. Hirano, A. Matsuo, K. Kobayashi, S. Tomioka, M. Izumikawa

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2008年

開催年月日： 2008年

Supersonic combustor with single "stinger-shaped" injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 % higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

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Matched Pressure Injections into a Supersonic Crossflow through Diamond-Shaped Orifices

Sadatake, T, Kouchi, T, Izumikawa, M, Koike, S, Masuya., G, Hirano, K, Matsuo, A

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2007年

New Injector Geometry for Penetration Enhancement of Perpendicular Jet into Supersonic Flow

K. Hirano, A. Matsuo, T. Kouchi, S. Tomioka, M. Izumikawa

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2007年

Pulsed transverse injection applied to a supersonic flow

Toshinori Kouchi, Noboru Sakuranaka, Muneo Izumikawa, Sadatake Tomioka

Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2007年

開催年月日： 2007年

An experimental investigation was conducted to reveal jet penetration and mixing performance of pulsed injection in a Mach 2.5 crossflow. Helium and nitrogen gas were injected perpendicularly through flush-mounted circular sonic orifice. Probing techniques including species composition sampling and high speed framing schlieren were employed to determine the penetration and mixing performance at several downstream locations. Our investigation consisted essentially of two parts. The first part was an investigation of the continuous jet. The performance of the continuous jet was mainly controlled by effective velocity ratio (r) as the square root of the momentum-flux ratio and the orifice diameter (d). The centerline trajectories of the jets and the maximum concentration decay were collapsed by the rd scale and the ratio of oncoming boundary-layer thickness to the injector diameter. The second part was an comparison of the performance between the pulse and continuous jets. The penetration of the pulse jet was adjustable by changing the pulse duty cycle at a condition of fixed injectant mass flow rate. Even at a condition of fixed injection pressure, the pulsed injection showed better mixing performance and the higher penetration, due to the fluctuation of the large-scale eddies in the jet associated with the fluctuation of the bow shock in front of the jet.

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超音速燃焼器における燃料噴射孔形状が貫通に及ぼす影響の検討(空気力学・高エンタルピー流(2),一般講演)

平野昂志, 河内俊憲, 小池俊輔, 泉川宗男, 松尾亜紀子, 富岡定毅, 升谷五郎

日本流体力学会年会講演論文集 2007年日本流体力学会

開催年月日： 2007年

記述言語：日本語

Both the wind tunnel experiments and the numerical analyses on helium injections with various injector geometry configurations were performed in order to achieve high penetration and effective mixing between supersonic crossflow and injectant. The stinger shaped injector showed the best penetration performance among all injectors. There was a difference between the experiment and the numerical analysis in evaluation of the injectant concentration. However, the penetration height resulted from the numerical analysis showed good agreement with that from the experiment. It is believed that the reduction of the disturbance of the plume to the crossflow leads to the increment in the penetration.

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超音速流中への直列4孔噴射の貫通特性

小池俊輔, 河内俊憲, 泉川宗男, 富岡定毅, 升谷五郎

燃焼シンポジウム講演論文集 2007年

超音速燃焼器における燃料噴射孔形状が貫通に及ぼす影響の検討

平野昂志, 河内俊憲, 小池俊輔, 泉川宗男, 松尾亜紀子, 富岡定毅, 升谷五郎

日本流体力学会年会講演アブストラクト集 2007年

Evaluation of heat-flux on scramjet engine wall in Mach 6 flight condition

Shuichi Ueda, Masao Takegoshi, Toshinori Kouchi, Fumiei Ono, Toshihito Saito, Muneo Izumikawa

AIAA 57th International Astronautical Congress, IAC 2006 2006年

開催年月日： 2006年

Space transportation system uses the liquid hydrogen of the fuel as a coolant of the engine. Therefore, it is necessary to predict the heat flux to the engine wall in high accuracy for efficient cooling with a minimum coolant. However, the prediction of the heat flux to the scramjet engine combustor walls, is quite difficult due to complex interaction of flow and combustion. In this study, a sidewall-compression-type scramjet engine was tested under Mach 6 flight conditions using Ramjet Engine Test Facility. The heat flux was measured using water-cooled heat-flux meters installed on the sidewall within the combustor sections. The experimental results were compared with CFD analysis of the whole engine to predict heat flux distribution on the engine wall. The numerical results of wall pressure distribution showed good agreement with the experimental data. However, the experimental results of heat flux were extremely higher than the numerical results due to the radiation heating which was not considered in the CFD analysis. Based on the results, the average heat flux of the sub-scale scramjet engine with 300 K isothermal walls was 1 MW/m2 in the stoichiometric fuel rate at Mach 6 flight conditions.

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Heat Flux Prediction for Scramjet Engines

T. Kouchi, T. Mitani, T. Hiraiwa, M. Kodera, G. Masuya

Proceedings of 1st International Conference of Flow Dynamics 2004年11月

Scramjet performance achieved in engine tests from M4 to M8 flight conditions

Tohru Mitani, Sadatake Tomioka, Takeshi Kanda, Nobuo Chinzei, Toshinori Kouchi

12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003年

開催年月日： 2003年

Thrust performances of scramjet engines were compared with theoretical values to quantify the progress in engine performances (defined as "achievement factors", or "factors") from Mach (termed as "M") 4 to M8 flight conditions. An engine with a ramp produced a net thrust of 215 N under the M8 tests and a comparison of a theoretical thrust yielded a thrust achievement factor of 51%. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92% and a net thrust factor of 45%. The thrusts were limited by flow separation caused by engine combustion (termed as "engine unstart"). The starting characteristics was improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1620 N to 2460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60% at the stoichiometric H2 condition. Under M4 tests, the net thrust was tripled by the bleed and a two-staged injection of H2. As results, the thrust factor was raised from 53% to 70%, the net thrust factor was increased from 32% to 55%. Studies required for improving the net performance was addressed. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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ステレオPIVを用いた超音速流れ場の境界層速度計測