• Title/Summary/Keyword: 연소영역

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Turbulent Combustion Characteristics of a Swirl Injector in a Gas Turbine Annular Combustor Using LES and Level-set Flamelet (LES와 Level-set Flamelet 기법을 이용한 가스터빈 환형 연소기용 스월 분사기의 난류 연소 특성)

  • Kim, Lina;Hong, Ji-Seok;Jeong, Won Cheol;Yoo, Kwang-Hee;Kim, Jong-Chan;Sung, Hong-Gye
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.2
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    • pp.1-9
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    • 2014
  • To investigate the flame dynamics in an annular combustor with single swirl injector, a 3D large-eddy simulation (LES) and a level-set flamelet turbulent combustion model have been implemented. The LM6000 developed by GEAE has been used as the combustor of concern and boundary conditions are based on experimental data. The strong central toroidal recirculation zone induced by the volume expansion of the combustion gas and the vortex breakdown continuously occurred through the procession of the vortex with decreasing strength, are observed.

Surface Combustion Characteristics of LPG and Coke Oven Gas Using Metallic Fiber Burner (액화석유가스와 코크스로가스의 표면연소 특성)

  • 한건우;조길원;박오현;이용국
    • Proceedings of the Korea Society for Energy Engineering kosee Conference
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    • 1997.10a
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    • pp.70-77
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    • 1997
  • 표면연소버너의 모재 중 최근 많은 관심을 끌고 있는 금속섬유를 이용한 LPG 및 COG의 연소특성을 파악하였다. 연소모드, 매트 표면온도분포, 공해물질 배출량, 버너 전후단 압력 손실을 측정한 결과, COG 연소시가 더 넓은 범위의 적열영역을 얻을 수 있었고, 매트의 평균 표면온도도 높았다. NOx 발생량은 100ppm 이하였고, 연소부하 50kcal/$ extrm{cm}^2$hr에서의 매트 전후단의 압력손실은 30mmH2O로 압력손실은 거의 없었다. 적열범위나 표면온도분포 등이 가스별로 약간의 차이를 보였으나, 매트의 종류에 크게 상관없이 안정연소를 달성할 수 있어 가스 특성이 상이한 각종 가스의 연소에 표면연소기술의 적용이 가능할 것이다.

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Study on the Stability Test of Impinging(FOOF) Injector on $GN_2$ Purge Cold Flow Test (질소분사 음향시험을 통한 충돌형(FOOF) 분사기의 안정성 평가에 관한 연구)

  • Yoo Doc-Koon;Lee Kwang-Jin;Seo Seong-Hyeon;Han Young-Min;Choi Hwan-Seok;Seol Woo-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2006.05a
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    • pp.135-140
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    • 2006
  • In the experimental study of $N_2$ purge cold flow test of impinging(FOOF) injector for determining of instability region, the whistling sound which has a specific frequency is generated. The frequency of whistling is proportional to the gas flow velocity in part of the oxidizer orifice and due to the coupling of the vibrating gas column and the natural frequency of pipe-orifice shape, the discontinuous jumping phenomena arises. The whistling phenomena have no effect on the combustion instability. Compared the damping factor of 1T1L mode with the hot fire test, the instability region of $N_2$ purge cold flow test is very much like that. It means that flow instability by impinging or mixing of jet is the main reason of combustion instability of impinging injector(FOOF) in the hot firing test.

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A Study on Lean Combustion Characteristics with Hydrogen Addition in a Heavy Duty Natural Gas Engine (대형 천연가스엔진에서의 수소 첨가에 의한 희박연소특성 연구)

  • Park, Cheol-Woong;Kim, Chang-Gi;Choi, Young;Won, Sang-Yeon
    • Journal of the Korean Institute of Gas
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    • v.14 no.4
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    • pp.12-17
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    • 2010
  • Natural gas is one of the most promising alternatives to gasoline and diesel fuels because of its high thermal efficiency and lower harmful emissions, including $CO_2$. However, the possibility of partial burn and misfire makes the benefits of natural gas fueled engine worse under lean burn operation condition, Hydrogen addition can promote the combustion characteristics while reduces emissions extremely. In this study, the effect of hydrogen addition on an engine performance was investigated. The results showed that thermal efficiency was increased due to the expansion of lean operation range under stable operation. NOx emission can be significantly reduced with the small increase in HC or CO emissions.

Combustion Stability Rating Test under Low Pressure Condition of a 75-$ton_f$ LRE Thrust Chamber (75톤급 액체로켓엔진 연소기의 저압 조건에서 수행된 연소안정성 시험)

  • Lee, Kwang-Jin;Kang, Dong-Hyuk;Lim, Mun-Ki;Ahn, Kyu-Bok;Han, Yeoung-Min;Choi, Hwan-Seok
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.231-238
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    • 2010
  • Combustion stability rating tests under condition low pressure of a 75-$ton_f$ liquid rocket engine(LRE) thrust chamber were carried out. Mixing head with decreased number of injectors than that of the other but with the same mass flow rate to the combustion chamber showed self-oscillation instability in chamber pressure of 30 bar. The other combustion chamber with increased number of injectors showed that high frequency combustion stability was maintained under condition of same pressure, but self-oscillation instability was generated in chamber pressure of 20 bar which can be considered as stability boundary region of this mixing head.

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Analysis of Pintle Tip Thermal Damage in the Combustion Hot Firing Test with a 1.5-tonf Class Liquid-Liquid Pintle Injector (1.5톤급 액체-액체 핀틀 분사기 연소시험에서의 핀틀 팁 열손상 원인 분석)

  • Kang, Donghyuk;Hwang, Dokeun;Ryu, Chulsung;Ko, Youngsung
    • Journal of the Korean Society of Propulsion Engineers
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    • v.24 no.6
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    • pp.1-9
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    • 2020
  • Using kerosene and liquid oxygen, 1.5-tonf class liquid-liquid pintle injector with rectangular two-row orifice was designed and manufactured. The combustion test of the pintle injector was carried out to verify the combustion performance and combustion stability under a supercritical condition which is the actual operation condition of the liquid rocket engine. The combustion test result showed that the pintle tip was damaged by the high temperature combustion gas in the high-mixed ratio recirculation zone of the combustion chamber. To solve this problem, the insert nozzle was installed in the pintle injector to increase cooling performance at the pintle tip. As a result of the hot firing test, installation of the insert nozzle, AR and BF had a great effect on pintle tip cooling performance.

PIV를 이용한 액체 램재트 엔진 연소실의 유동 계측

  • 양근수;조동우;김규남;손창현;이충원
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.11a
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    • pp.15-15
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    • 2000
  • 두 개의 사각형 유입구가 $90^{\cire}$의 각도를 이루고 있는 액체 램제트 엔진의 연소실 형상을 최적화하기 위해서 수조를 이용한 연소실 유동 계측 실험을 수행하였다. 공기 유입구의 연소실 유입 각도는 $30^{\cire}$, $45^{\cire}$$60^{\cire}$인 세 가지 형상의 연소실 모형을 제작하였으며, 각각의 유입 각도에 대하여 연소실 재순환 영역의 크기를 5가지로 변화시킬 수 있도록 모형을 제작하였다. 그리고 연소실의 배면은 돔의 형태로 하여 재순환이 잘 이루어지도록 모형을 제작하였으며, 유입구에서 연소실로 들어가는 유동의 안정화를 위해 안내깃을 세 개 설치하여 실험하였다.(중략)

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Dynamic study on the Interaction between Terminal Shock train and Flame Fluctuation of Supersonic Propulsion System (초음속 엔진의 흡입구 종말충격파와 연소실 화염의 상호간섭 동적연구)

  • Yeom, Hyo-Won;Kim, Sun-Kyeong;Kim, Seong-Jin;Sung, Hong-Gye;Gil, Hyun-Yong;Yoon, Hyun-Gull
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.05a
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    • pp.79-82
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    • 2009
  • Unsteady numerical analysis of an entire supersonic propulsion system from intake to nozzle was performed to study dynamic interaction between terminal shock in the intake and flame in the combustor. Both acceleration and cruise flight-modes were considered. Acoustic mode of the entire engine for both flight-modes were investigated by detail analysis of pressure fluctuation at each location of engine.

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LES of Supercritical Combustion of Shear-coaxial Injector of a Methane-LOx Liquid Rocket Engine (액체로켓(메탄-LOx) 동축인젝터의 초임계 연소 LES 연구)

  • Heo, Jun-Young;Kim, Kuk-Jin;Sung, Hong-Gye;Yang, Vigor
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.190-193
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    • 2010
  • The turbulent mixing and combustion of a shear coaxial injector under supercritical pressures have been theoretically/numerically investigated. Turbulent numerical model is based on large eddy simulation with real-fluid transport and thermodynamics over the entire pressure; Soave modification of Redlich-Kwong equation of state, Chung's model for viscosity/conductivity, and Fuller's theorem for diffusivity to take account Takahashi's compressible effect. The results are compared with previous researcher's. The large-scale vortices shedding from the outer rim into the recirculation region to react with gaseous oxygen was investigated.

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