研究者詳細 - 河内　俊憲

論文 - 河内　俊憲

分割表示 113 件中 81 - 100 件目／全件表示 >>

Effect of fuel injection location on a plasma jet assisted combustion with a backward-facing step 査読

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

Proceedings of the Combustion Institute 33 ( 2 ) 2375 - 2382 2011年1月

Large-eddy simulations of hydrogen and ethylene injections into a supersonic crossflow

Junya Watanabe, Toshinori Kouchi, Kenichi Takita, Goro Masuya

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 ( 2011-5764 ) 2011年

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：American Institute of Aeronautics and Astronautics

Turbulent structure and mixing state of hydrogen and ethylene jets transversely injected into Mach 1.9 supersonic crossflow was numerically investigated using large-eddy simulation. The feature of windward large-scale structure was largely different between the hydrogen and ethylene jets. The ethylene jet had a highly intermittent feature with intensive geometric change of jet plume. The hydrogen jet had much larger velocity difference between the jet and the crossflow in the near-field, thus much higher turbulent intensity was obtained than in the ethylene jet. In addition, the scale of energetic eddy of hydrogen jet was larger in the windward mixing layer. These probably result in the better mixing in the hydrogen jet than in the ethylene jet. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

DOI： 10.2514/6.2011-5764

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Effect of fuel injection locations with a hyper mixer in supersonic combustion

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

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 ( 2011-5830 ) 2011年

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：American Institute of Aeronautics and Astronautics

A reacting-experiment was conducted to understand the relation between a wallmounted alternating-ramp-wedge type hyper mixer and various injection locations in unheated supersonic flow. The hydrogen gas and a plasma jet torch were used as the fuel and the igniter, respectively. The parallel injection method shows the maximum combustion efficiency for the forced ignition. This is because the fuel-air mixture can be ignited in the heat source (plasma jet) and providing the fuel-air mixture to the plasma jet, i.e., the parallel injection, is very effective to enhance the combustion efficiency. In the cold main flow, the combustion region is restrained and affected by the location of the plasma jet. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

DOI： 10.2514/6.2011-5830

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Flowfield characteristics on a vent slot mixer in supersonic flow 査読

Kim, C., Sung, K., Jeung, I. -S., Choi, B., Kouchi, T., Masuya, G.

Shock Waves 20 ( 6 ) 559 - 569 2010年12月

Effect of a Vent Slot Mixer with a Plasma Jet Torch in Unheated Supersonic Flow

Chae-hyoung Kim, In-seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010年7月

Penetration Characteristics of Pulsed Injection into Supersonic Crossflow

Toshinori Kouchi, Keita Sasaya, Junya Watanabe, Hiroharu Shibayama, Goro Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010年7月

Scalar spatial correlations in a supersonic mixing flowfield 査読

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

AIAA Journal 48 ( 2 ) 443 - 452 2010年2月

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：AMER INST AERONAUT ASTRONAUT

Single-time two-point spatial correlations of injectant concentrations 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 data. Side-view and end-view contour maps were obtained in several planes to characterize the turbulent structure and three-dimensionality of the mixing flowfield. The correlation maps indicated an organized large-scale structure in the upper region of the jet. The 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. The end-view correlation maps showed that the instantaneous jet plume appeared by turns either in the top or in the lower sides of the time-averaged injectant plume in each cross section. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

DOI： 10.2514/1.44684

Web of Science

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

Chae-hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009年10月

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10月

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1月

Aerodynamic Experiments of Small Scale Combined Cycle Engine in Various Mach Numbers 査読

TANI Kouichiro, KOUCHI Toshinori, KATO Kanenori, SAKURANAKA Noboru, WATANABE Syuuichi

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7 ( ists26 ) Pa_59 - Pa_64 2009年

記述言語：英語掲載種別：研究論文（学術雑誌）出版者・発行元：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

A small model aerodynamic tests of the combined cycle engine were carried out to evaluate its performance in subsonic and supersonic conditions. In this regime of the flow speed, the combined cycle engine operates as an ejector-jet or ramjet. The nitrogen gas was exhausted as the substitution for the actual rocket gas. In a subsonic condition, there appeared local pressure rise at the kink point of the ramp, increasing the pressure drag. Both wall pressure and the pitot pressure distribution at the exit of the model suggested that the flow structure is "two-layered" ; one is subsonic induced air flow, and the other is the supersonic rocket exhaust. A slit was carved on the topwall inside the isolator section, expecting a better suction performance in the ejector-jet mode. The modification actually had an effect to enhance the lower limit of the rocket pressure at which the choking of the induced air is achieved.

DOI： 10.2322/tstj.7.pa_59

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Supersonic combustion with supersonic injection through diamond-shaped orifices 査読

S. Tomioka, T. Kohchi, R. Masumoto, M. Izumikawa, A. Matsuo

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 27 ( 6 ) 1196 - 1203 2009年

記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）出版者・発行元：American Institute of Aeronautics and Astronautics

Supersonic injections through diamond-shaped injectors were applied to a supersonic combustor with a diverging section, with a Mach 2.4 incoming vitiated airflow at a total temperature of 2000 K, and combustion characteristics were experimentally investigated and compared to those with sonic injection through circular injectors. Without any flame-holding devices installed, scramjet-mode combustion was attained in wide range of fuel flow rate, in which the supersonic injections resulted in a higher pressure-rise in far-field than the sonic injections. Regardless of the injection scheme (i.e, orifice shape, orifice number, and injection conditions), transition to dual-mode combustion enhanced the thrust production, and the supersonic injection through the diamond-shaped orifice had lesser ability to cause the transition than the sonic injection through the circular orifice. The ability was enhanced by installation of a recess and introduction of recess fueling, and resulting combustor performance was slightly better than that with the sonic injection, in the case with single orifice. Both the number of the orifice and the injection pressure (by changing the total orifice throat area) were varied for the supersonic injection through the diamond-shaped orifice for fixed fuel flow rates, and the change in combustion characteristics were also reported. © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

DOI： 10.2514/1.B34164

Web of Science

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Performance of a scramjet engine model in Mach 6 flight condition 査読

S. Ueda, T. Kouchi, M. Takegoshi, S. Tomioka, K. Tani

Shock Waves 1129 - 1134 2009年

Design and Experimental Verification of Two Dimensional Asymmetric Supersonic Nozzle 査読

김채형, Masuya, Goro, 성근민, 최병일, Kouchi, Toshinori

Journal of the Korean Society for Aeronautical and Space Sciences 37 ( 9 ) 2009年

Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

Toshinori Kouchi, Kohshi Hirano, Kan Kobayashi, Sadatake Tomioka, Muneo Izumikawa, Akiko Matsuo

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2008年7月

Matched pressure injections into a supersonic crossflow through diamond-shaped orifices 査読

Tomioka, Sadatake, Izumikawa, Muneo, Kouchi, Toshinori, Masuya, Goro, Hirano, Kohshi, Matsuo, Akiko

Journal of Propulsion and Power 24 ( 3 ) 471 - 478 2008年5月

複合エンジンの静止大気中における吸い込み性能（第2報：エジェクタ二層流解析と吸い込み性能改善）査読

河内俊憲, 富岡定毅, 苅田丈士

日本航空宇宙学会論文集 56 ( 651 ) 163 - 168 2008年

複合エンジンの静止大気中における吸い込み性能（第1報数：値計算による吸い込み性能予測）査読

河内俊憲, 富岡定毅, 苅田丈士

日本航空宇宙学会論文集 56 ( 650 ) 110 - 115 2008年

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

Kohshi Hirano, Akiko Matsuo, Toshinori Kouchi, Muneo Izumikawa, Sadatake Tomioka

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2007年7月

Pulsed Transverse Injection Applied to a Supersonic Flow

Toshinori Kouchi, Noboru Sakuranaka, Muneo Izumikawa, Sadatake Tomioka

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2007年7月

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