• 제목/요약/키워드: Supersonic Combustion

검색결과 152건 처리시간 0.032초

초음속연소유동의 수치해석연구 (Numerical Simulation of Supersonic Combustion Flows)

  • 정인석;최정열
    • 한국연소학회:학술대회논문집
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    • 한국연소학회 2005년도 제31회 KOSCO SYMPOSIUM 논문집
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    • pp.32-39
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    • 2005
  • Recently, renewed interest on the scramjet engine has been demonstrated through the many international activities along the several Asia-Pacific countries. Here, a short review of current activities on supersonic combustion in a scramjet engine will be addressed followed by the discussions on the review of numerical simulation on supersonic combustion phenomena related with scramjet engine combustors and ram accelerator. Emphasis was put on the grid refinement, scheme, unsteadiness and phenomenological differences.

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초음속 유입 유동 조건에 따른 공동을 포함한 덕트 내 초음속 연소 현상에 관한 실험적 연구 (Experimental Study on Supersonic Combustion Phenomena in the Cavity Duct by the Supersonic Inflow Conditions)

  • 정은주;정인석
    • 한국연소학회:학술대회논문집
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    • 한국연소학회 2006년도 제33회 KOSCO SYMPOSIUM 논문집
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    • pp.209-219
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    • 2006
  • The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

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공동 상류 경사 분사를 이용한 초음속 연소기의 실험적 연구, Part 2 : 압력 측정 (Experimental Study on Supersonic Combustor using Inclined Fuel Injection with the Cavity, Part 2 : Pressure Measurement)

  • 정은주;정인석
    • 한국연소학회지
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    • 제12권1호
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    • pp.21-27
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    • 2007
  • The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Different shock tube fill pressures have various inflow conditions. $15^{\circ}$ inclined hydrogen fuel injection is located before the cavity. Oblique shock is generated at the trailing edge of the cavity and reflects off the top and bottom wall. For non-reacting flow, static pressures in low equivalence ratio are similar to those in no fuel injection. As equivalence ratio is increased, static pressures are increased in the duct. In the similar equivalence ratio, static pressures are increased when total enthalpy is decreased. For reacting flow, the flame is occurred near the cavity. The combustion is weak locally in the middle of the duct. The up and down pressure distribution in the duct means that the supersonic combustion is generated.

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이중연소 램제트엔진의 성능해석 기법 (Performance Analysis Method for Dual Combustion Ramjet Engines)

  • 서봉균;염효원;성홍계;길현용;윤현걸
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2011년도 제36회 춘계학술대회논문집
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    • pp.326-330
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    • 2011
  • 이중연소 램제트엔진의 아음속 연소기의 연소가스와 스크램제트 모드로 흡입되는 흡입공기의 혼합 및 초음속 연소를 고려한 이중연소램제트 성능해석 기법을 개발하고 검증하였다. 극초음속 흡입구의 유동특성을 고려하기 위하여 Taylor-Maccoll 방정식을 사용하였으며 초음속 연소기 해석을 위해 준 1차원 연소모델 및 CEA를 이용한 화학 평형 모델을 적용하였다. 개발된 모델을 통하여 계산된 흡입구와 연소기에서의 열역학 데이터를 수치해석 결과와 비교하였다.

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공동주위 분사위치에 따른 초음속 연소 유동해석 (Numerical Analysis of Supersonic Combustion Flows according to Fuel Injection Positions near the Cavity)

  • 정은주;정인석
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2005년도 제24회 춘계학술대회논문집
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    • pp.368-373
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    • 2005
  • 효과적인 초음속 연소를 수행하기 위해 연료와 공기의 빠른 혼합을 이룰 수 있는 연료 분사 기술이 요구된다. 본 수치적 연구의 목적은 초음속 유동장내에서 공동 주위 연료분사 위치에 따른 연료/공기 혼합 및 연소 현상을 살펴보고자 한다. 연료 분사 위치는 연소기내에서 영향을 미치는 공동의 길이-깊이비를 변화시킨다. 따라서 같은 형상의 공동이라 하더라도 공동 주위 유동 특성이 달라지므로 연소기 내부의 연료/공기 혼합과 연소 현상에 영향을 끼치게 된다.

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극초음속 추진기관의 특성 및 초음속 연소 풍동 기초 설계 (Characteristics of Hypersonic Airbreathing Propulsion System and Preliminary Design of Supersonic Combustion Tunnel)

  • 김정용;허환일
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2001년도 제16회 학술발표회 논문초록집
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    • pp.35-38
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    • 2001
  • 차세대 추진 기관으로 연구되고 있는 스크램제트 엔진의 열역학적 특성들을 검토하였다. 유동이 엔진을 통과하면서 연소에 의해 전압력이 손실되고 노즐 출구 마하수가 감소하지만, 고온 연소 가스가 배출되기 때문에 실질적인 속도는 증가하게 되고 추력이 발생한다. 초음속 연소를 모사하기 위해 blowdown 형태의 초음속 연소 풍동 설계를 위한 개념 설계가 이루어졌다. 초음속 풍동 시험부에서 마하 2.5의 속도를 유지하기 위한 작동 압력과 질유량이 계산되었다.

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A Study of Supersonic Combustion using Various Liquid Hydrocarbon Fuels

  • Hashimoto, Susumu;Hiramoto, Ayumu;Tsue, Mitsuhiro;Kono, Michikata;Ishikawa, Yuta;Suzuki, Shunsuke;Ujiie, Yasushige
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2008년 영문 학술대회
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    • pp.340-345
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    • 2008
  • Liquid hydrocarbon fuels are gathering increasing attention as candidates for a scramjet engine fuel. Experimental researches on supersonic combustion of kerosene have been conducted in model scramjet combustors. Through these works, understanding of combustion characteristics of kerosene have been revealed on some level, and so we decided to work on other kinds of liquid hydrocarbon fuels in order to explore effects of fuel properties on supersonic combustion performances, especially self-ignition and flame-holding. In addition, comparing the results of new fuels with kerosene, the relationship between fuel properties and supersonic combustion characteristics was discussed.

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이중 연소기의 초음속 연소 실험 (Supersonic Combustion Experiments of Dual Combustors)

  • 변종렬;이상연;문관호;황기영;임진식
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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    • pp.386-387
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    • 2012
  • 본 연구는 이중연소 램제트 엔진의 연소기에 대한 초음속 연소 실험에 대한 것이다. 이중연소 램제트 엔진의 기본 성능해석을 통해 도출된 이중 연소기 형상을 설계/제작하여 연소 실험을 수행하였다.

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초음속 코히어런트 제트에 관한 수치해석적 연구 (A Computational Study of the Supersonic Coherent Jet)

  • 정미선;;김희동
    • 대한기계학회:학술대회논문집
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    • 대한기계학회 2003년도 추계학술대회
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    • pp.490-495
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    • 2003
  • In steel-making process of iron and steel industry, the purity and quality of steel can be dependent on the amount of CO contained in the molten metal. Recently, the supersonic oxygen jet is being applied to the molten metal in the electric furnace and thus reduces the CO amount through the chemical reactions between the oxygen jet and molten metal, leading to a better quality of steel. In this application, the supersonic oxygen jet is limited in the distance over which the supersonic velocity is maintained. In order to get longer supersonic jet propagation into the molten metal, a supersonic coherent jet is suggested as one of the alternatives which are applicable to the electric furnace system. It has a flame around the conventional supersonic jet and thus the entrainment effect of the surrounding gas into the supersonic jet is reduced, leading to a longer propagation of the supersonic jet. In this regard, gasdynamics mechanism about why the combustion phenomenon surrounding the supersonic jet causes the jet core length to be longer is not yet clarified. The present study investigates the major characteristics of the supersonic coherent jet, compared with the conventional supersonic jet. A computational study is carried out to solve the compressible, axisymmetric Navier-Stokes equations. The computational results of the supersonic coherent jet are compared with the conventional supersonic jets.

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공동 내부로의 평행분사방법을 이용한 초음속 연소의 실험적 연구 (Experimental Study on Supersonic Combustion with Parallel Fuel Injection Method in the Cavity)

  • 정은주;정인석
    • 한국연소학회지
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    • 제12권2호
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    • pp.20-25
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    • 2007
  • The supersonic combustion experiments are carried out using T3 free-piston shock tunnel. Hydrogen Fuel is injected in the cavity parallel with air(or nitrogen) flow. The equivalence ratios in this study are 0.132 and 0.447. Experimental measurements use OH-PLIF near the cavity and pressures in the combustor. For parallel fuel injection case, direct fuel add into cavity leads to increase of cavity pressure. And Flame exists just near the bottom wall for low equivalent ratio. There is no flame in the cavity because of no mixing in it. Compared to the inclined fuel injection, ignition delay length is longer for low equivalence ratio in both case. OH distribution is not a single line but a repeatable fluctuation flame structure by turbulence. Pressure distributions have nothing to do with the fuel injection position.

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