• Title/Summary/Keyword: 화염안정기

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Influence of Flame Holder on Film Cooling Effectiveness of Ramjet Combustor (화염안정기 형상이 램제트 연소실에서의 슬롯 막냉각 특성에 미치는 영향)

  • Lee, Keon-Woo;Song, J.;Cho, Hyung-Hee;Hwang, Ki-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.315-320
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    • 2008
  • This experimental study has been conducted to investigate the effect of the flame holder on the multi-slot film cooling in the ramjet combustor. The turbulent wake which is generated by the flame holder on the entrance of the coolant flow path affects on the slot. Adiabatic film cooling effectiveness on the downstream wall of the slot exit are measured. The results show that the film cooling performance is rapidly decreased after the slot exit by shear layer and high turbulence intensity between separated flows and coolant flows.

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Influence of the Vertical Flame holder on Heat Transfer Characteristics of Ramjet Combustor (세로축 화염안정기 형상이 램제트 연소실에서의 열전달 특성에 미치는 영향)

  • Yang, Kang-Mo;Lee, Keon-Woo;Song, Ji-Woon;Cho, Hyung-Hee;Hwang, Ki-Young
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.305-309
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    • 2008
  • This experimental study has been conducted to investigate the installation of the vertical flame holder shape in ramjet combustor, which affects on the film cooling effectiveness. All slot position, the film cooling effectiveness decreases because of the shear layer and high turbulence intensity between separated flows and coolant flows. When the flame holder is installed, film cooling effectiveness decreases abruptly on the beginning of the slot exit region due to the mixing effect. As the blowing rate increases, the film cooling effectiveness is increased for all cases due to the augmented momentum of injected coolant from the slot.

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Characteristics of Jet Type Flame Holder for Ramjet Engine Combustors (램제트 엔진 연소기용 제트분사형 화염안정기의 특성분석)

  • Kang, Sang-Hun;Yang, Soo-Seok
    • Aerospace Engineering and Technology
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    • v.6 no.2
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    • pp.14-20
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    • 2007
  • In this study, characteristics of jet type flame holder for ramjet engine combustors are investigated Jet flame holder can be easily controlled by the injection angle change and jet momentum variation without any thermal protection devices. Due to the intensive turbulent mixing effect, jet flame holder shows better flame holding performance than mechanical flame holders such as cavity, step and v-shape flame holder.

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Study on Combustion Stability and Flame Structure of Injectors Through Subscale Combustion Tests (모델 연소시험을 통한 분사기 연소안정성과 화염구조에 대한 연구)

  • Song Ju-Young;Lee Kwang-Jin;Seo Seonghyeon;Han Yeoung-Min;Seol Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2004.10a
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    • pp.245-250
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    • 2004
  • The objective of the present study is to conduct model combustion tests for various injectors to identify their combustion stability characteristics. Three different double swirl coaxial injectors with variation of a recess number have been tested for the comparative study of stability characteristic and flame structure. Gaseous oxygen and mixture of gaseous methane and propane have been employed for simulating actual propellants used for a fullscale thrust chamber. Upon test results, the direct comparison between various types of injectors can be realized for the selection of the best design among prospective injectors.

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Effects of Combustor Configuration on the Stability of Supersonic Turbulent Lifted Flame in a DCR Engine (이중 연소 램제트 엔진에서 연소기 형상에 따른 초음속 난류 부상 화염의 안정성 연구)

  • Choi, Jeong-Yeol
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.595-598
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    • 2011
  • Supersonic combustion phenomena in the main combustor of a dual combustion ramjet (DCR) engine are studied numerically. Since the supersonic combustion is affected significantly by the compressibility effects parametric studies have been carried out for the constant are length and the divergence angle. Numerical studies with fixed inflow condition for different geometric configurations reveals that the supersonic combustion in DCR combustor has the characteristics of lifting flame, where the lifting flame is maintained near the injector tip for the case of long combustor length with small divergence angle, but the lifting height is significantly increase for large divergence angle resulting flame blow-out of the combustor. Therefore, it is concluded that flame stability should be considered sufficiently in the design o DCR combustor.

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Numerical Study of Flame Stability of Turbulent Combustion in a Dual Combustion Ramjet (이중연소 램제트 엔진의 난류 연소 현상과 화염 안정성)

  • Choi, Jeong-Yeol;Han, Sang-Hoon;Kim, Kyu-Hong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.371-374
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    • 2011
  • High-resolution numerical study is carried out to investigate the flame stability of the turbulent supersonic combustion in a Dual-Combustion Ramjet (DCR). The auto-ignition in a shear layer between hydrogen/carbon-monoxide syngas and air was studied at elevated enthalpy condition. Comparison of a constant area combustor and a combustor with a small divergence angle shows that the supersonic combustion has a characteristics of the lifted flame and its stability is influenced significantly by the compressibility.

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Measured Effect of Shock Wave on the Stability Limits of Supersonic Hydrogen-Air Flames (충격파가 초음속 수소-공기 화염의 안정한계에 미치는 영향)

  • Hwanil Huh
    • Journal of the Korean Society of Propulsion Engineers
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    • v.3 no.1
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    • pp.86-94
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    • 1999
  • Measured shock wave effects were investigated by changing shock strength and position with particular emphasis on the stability limits of hydrogen-air jet flames. For this purpose, a supersonic nonpremixed, jet-like flame was stabilized along the axis of a Mach 2.5 wind tunnel, and wedges were mounted on the sidewall in order to interact oblique shock waves with the flame. This experiment was the first reacting flow experiment interacting with shock waves. Schilieren visualization pictures, wall static pressures, and flame stability limits were measured and compared to corresponding flames without shock-flame interaction. Substantial improvements in the flame stability limits were achieved by properly interacting the shock waves with the flameholding recirculation zone. The reason for the significant improvement in flame stability limits is believed to be the adverse pressure gradient caused by the shock, which can elongate the recirculation zone.

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Comparison of NOx Emission Characteristics of CH$_4$ Double and Normal Jet Diffusion Flame (CH$_4$ 이중 및 정상 분류확산화염에서의 NOx 배출 특성 비교)

  • 홍승수;김종현;이창언
    • Proceedings of the Korea Society for Energy Engineering kosee Conference
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    • 2002.11a
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    • pp.155-160
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    • 2002
  • 연소시 발생하는 오염물질 중 NOx는 심각한 대기오염의 원인이 되는 것으로 알려져 있어, 각종 연소기 등에서 발생하는 NOx 저감을 위한 연구가 중요하게 대두되었다. 특히 확산화염은 예혼합화염 및 부분예혼합화염에 비해 NOx, Soot 등 오염물질이 발생할 가능성은 높으나 화염 안정성이 좋아 산업용 연소기에 많이 이용되고 있어 보다 다양한 NOx 저감 기술의 필요가 요구되고 있다.(중략)

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A Study of Flame Visualization of the APU Gas Turbine Engine Sector Combustor (APU용 가스터빈 엔진 분할연소기의 화염가시화 연구)

  • Kim, Bo-Ra-Mi;Choi, Chea-Hong;Choi, Seong-Man
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.4
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    • pp.11-17
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    • 2011
  • In order to see flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65 m/s.

A Study of Flame Visualization of the APU Gas Turbine Engine Sector Combustor (APU용 가스터빈 엔진 분할연소기의 화염가시화 연구)

  • Kim, Bo-Ra-Mi;Choi, Chea-Hong;Choi, Seong-Man
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.153-159
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    • 2010
  • In order to see the flame behavior in the annular reverse gas turbine combustor, sector combustion test was performed. Ignition test by using torch ignition system was carried out at the various combustor inlet velocity and air fuel ratio. Also, flame blow out limit was measured by changing fuel flow rate with constant air mass flow rate. In the test results, stable ignition is possible at air excess ratio of 6 and this limit is gradually increased with combustor inlet velocity. The minimum blow out limit is about 4 at 40 m/s of combustor inlet velocity. This blow out limit is also increased up to about 10 with increasing combustor inlet velocity. Test result shows that lean blow out limits are increased with air velocity. The highest blow out limit was found at the combustor inlet velocity of 65m/s.

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