• Title/Summary/Keyword: 초음속 흡입구

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Internal Flow Aerodynamic Test of a Mach 5 Scramjet Engine (마하 5 스크램젯 엔진의 내부 유동 공력 시험)

  • Yang, In-Young;Lee, Yang-Ji;Kim, Young-Moon;Lee, Kyung-Jae;Kang, Sang-Hoon;Yang, Soo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.584-587
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    • 2011
  • An internal flow aerodynamic test was performed for a Mach 5 scramjet engine. The test was done without fuel injection, as a preliminary test for the combustion test. Test engine is an engineering model with intake cross-section of $70mm{\times}200mm$ and total length of 1.7m. Test facility is a blowdown-type, high enthalpy, hypersonic facility. 19 pressures were measured through the holes on the model surface along the engine internal flow passage. It was found that the facility start is possible, and also supersonic flow is maintained inside the engine.

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Mixing Characteristics of Various Cavity Shapes in SCRamjet Engine (스크램제트 엔진 내부 Cavity 형상 변화에 따른 혼합 성능 특성)

  • Oh, Ju-Young;Seo, Hyung-Seok;Byun, Yung-Hwan;Lee, Jae-Woo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.1
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    • pp.57-63
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    • 2008
  • In combustor of SCRamjet of air-breathing engine type, the flow duration time is very short because of the supersonic air flow. In this short duration, the whole process of combustion should be done, so it is very important to study supersonic combustion technologies. In this study, we focus fuel-air mixing enhancement method using cavity and conducted 3-dimensional Navier-Stokes computational analysis. Cavity height is fixed by 10mm, length is changed from 0 to 40mm. There is a supersonic jet injection downstream of the cavity and the hole size is 1mm. As a result, the higher ratio of cavity length/height is, the higher value of vorticity gets. The increased area of vorticity expands to upper and sidewise combustor. However, the stagnation pressure loss which generates thrust loss becomes higher when the vorticity is higher. Considering these result, we can conclude that optimized design which considers the highest mixing performance and the least stagnation pressure loss is needed.

Numerical Flow Analysis of a Supersonic Impulse Turbine with Nozzles and Rotor Blades (노즐과 로터가 장착된 초음속 충동형 터빈의 전산유동해석)

  • Park, Pyun-Goo;Lee, Eun-Seok;Jeong, Eun-Hwan;Kim, Jin-Han
    • The KSFM Journal of Fluid Machinery
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    • v.10 no.1 s.40
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    • pp.26-33
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    • 2007
  • Four design candidates for a partial admission turbine have been chosen from a preliminary design process. Their performance were estimated through the 3-D numerical analyses using a frozen rotor method. In order to select the optimum design, each flow analysis result was compared with others. Flow characteristics in the passages and some types of losses induced by shocks and wakes were found from calculation results. Based on these calculations, a new rotor blade was redesigned and compared with previous one through flow analysis.

Numerical Flow Analysis of a Supersonic Impulse Turbine with Nozzles and Rotor blades (노즐과 로터가 장착된 초음속 충동형 터빈의 전산유동해석)

  • Park, Pyun Goo;Lee, En Seok;Jeong, Eun Hwan;Kim, Jinhan
    • 유체기계공업학회:학술대회논문집
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    • 2004.12a
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    • pp.445-451
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    • 2004
  • Four design candidates for a 1.4MW class partial admission turbine have been chosen from a Preliminary design process. Their performance were estimated through the 3-D numerical analyses using a frozen rotor method. In order to select the optimum design, each flow analysis result was compared with others. Flow characteristics in the passages and some types of losses induced by shocks and wakes were found from calculation results. Based on these calculations, a new rotor blade was redesigned and compared with previous one through flow analysis.

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Mixing Characteristics in Supersonic Combustor with a Cavity (Cavity를 이용한 초음속 연소기 내의 혼합특성)

  • Oh Juyoung;Bae Young-Woo;Kim Ki-Su;Jeon Young-Jin;Lee Jae-Woo;Byun Yung-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.359-363
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    • 2005
  • In SCRamjet engine, combustion occurs in supersonic flow with airbreathing. SCRamjet is characterized by very short combustion time in combustor, so it is very important to be mixing the air and fuel in short duration. Several methods are suggested for mixing enhancement. Among these, cavity is selected to study for enhancement of mixing. The numerical simulation is performed in the case of freestream Mach number of 2.5 and cavity located in front of fuel jet injection. CFD-Fastran, commercial code with three-dimensional Navier-Stokes equation with the Menter SST turbulence model were used. The results are obtained validate experiment results for same condition. Therefore, the numerical results show the mixing enhancement characteristics with a cavity.

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Starting Transients in Dual-Mode Scramjet Engine (이중 모드 스트램제트 엔진의 시동 천이 과정)

  • Choi, Jeong-Yeol;Noh, Jin-Hyun;Byun, Jong-Ryul;Lim, Jin-Shik
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.981-984
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    • 2011
  • A high-resolution numerical study is carried out to investigate the transient process of the combustion and the shock-train developments in an ethylene-fueled direct-connect dual-mode scramjet combustor. Following the fuel injection, air-throttling is applied at the expansion part of the combustor to provide mass addition to block the flow to subsonic speed. The ignition occurs several ms later when the fuel and air are mixed sufficiently. The pressure build up by the combustion leads to the shock train formation in the isolator section that advances to the exit of the intake nozzle. Then, the air-throttling is deactivated and the exhaust process begins and the situation before the air-throttling is restored. Present simulation shows the detailed processes in the dual-mode scramjet combustor for better understanding of the operation regimes and characteristics.

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A Study on the Blade Load Measurement of Partial-admission Turbine Cascade (충동형 터빈 캐스케이드의 깃 하중 측정에 관한 연구)

  • Lim, Dong-Hwa;Jang, Jin-Man;Lee, Eun-Seok;Kim, Jin-Han;Choi, Jong-Soo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.2
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    • pp.143-148
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    • 2007
  • An impulse turbine, which is a main component of a liquid rocket engine, needs to be a small size with light weight and generate large power. Since the impulse turbine is being operated under complicated supersonic conditions, flow analysis and performance prediction largely depend on CFD technique. In order to increase the reliability of the prediction code, however, it often requires an experimental data to compare. In this research a rotating turbine rotor with multiple blades is simulated with a two-dimensional stationary cascade to check the effect of major flow parameters. Mach number is measured at nozzle exit by using a pitot tube and the blade thrust was also measured with a load cell. The measured thrust coefficient and the power are compared well with the designed conditions, which proves the design procedures are properly taken.