研究者詳細 - 河内　俊憲

講演・口頭発表等 - 河内　俊憲

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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

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