高温升燃烧室与双燃烧室发动机性能对比分析

毛艳辉; 杨金虎; 刘存喜; 穆勇; 刘富强; 徐纲

高温升燃烧室与双燃烧室发动机性能对比分析

中国科学院工程热物理研究所,北京 100190

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出版历程
- 收稿日期: 2012-04-12
- 刊出日期: 2013-03-28

Performance comparison and analysis of high temperature rise combustor engine and two-combustor engine

Institute of Engineering Thermophysics, Chinese Academy of Sciences, 100190 Beijing, China

摘要

摘要: 采用一维定常计算方法,考虑各种部件效率的影响,在双燃烧室发动机总增压比为32,涡轮前总温为1900K时,与高温升燃烧室涡轮前总温为2400K时进行了总体性能对比,并指出了双燃烧室结构发动机2个燃烧室的热量分配方法.结果表明:温升同为1463K时,高温升燃烧室发动机比双燃烧室发动机单位推力高2.7%,耗油率低3.8%.双燃烧室结构发动机更有利克服超声速下的冲压损失, Ma大于1.5之后,增力比大于高温升燃烧室发动机.
- 航空发动机 /
- 总体性能 /
- 热力循环 /
- 级间燃烧室 /
- 高温升燃烧室
Abstract: One-dimensional steady method was used to calculate the high temperature rise combustor engine and two-combustor engine's overall performance in consideration of the component efficiency. The overall performance was compared at total pressure ratio 32 and turbine inlet temperature 1900K for two-combustor engine and turbine inlet temperature 2400K for high temperature rise combustor engine. The way of temperature rise distribution between combustors of two-combustor engine was also analyzed. Results show that the specific thrust of high temperature rise combustor engine is 2.7 percent higher than that of two-combustor engine, while the specific thrust fuel consumption is 3.8 percent lower. The two-combustor engine is helpful to decrease the total pressure loss under supersonic condition, and its specific thrust increase ratio is higher than high temperature rise combustor engine when Mach number is more than 1.5.
- aero engine /
- overall performance /
- thermo cycle /
- inter-stage turbine burner /
- high temperature rise combustor

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参考文献(19)

[1]	Bahr D W.Technology for the design of high temperature rise combustor[R].AIAA 85-1292,1985.
[2]	林宇震,许全宏,刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社,2006.
[3]	许全宏,林宇震,刘高恩,等.航空发动机高温升燃烧室贫油熄火及冒烟性能研究[J].航空动力学报,2005,20(4):636-640. XU Quanhong,LIN Yuzhen,LIU Gaoen,et al.Research on the high temperature rise combustor lean blow-out and smoke emission characteristics[J].Journal of Aerospace Power,2005,20(4):636-640.(in Chinese)
[4]	黎明,吴二平,唐明.高温升蒸发型双腔燃烧室的设计[J].推进技术,2010,31(4):418-422. LI Ming,WU Erping,TANG Ming.Design of vaporing combustor with double chambers and high temperature rise[J].Journal of Propulsion Technology,2010,31(4):418-422.(in Chinese)
[5]	彭云晖,刘旦,林宇震.高温升燃烧室主燃区流场和燃烧性能[J].燃烧科学与技术,2010,16(5):456-461. PENG Yunhui,LIU Dan,LIN Yuzhen.Primary zone flow field and combustion performance of high temperature rise combustor[J].Journal of Combustion Science and Technology,2010,16(5):456-461.(in Chinese)
[6]	Zhang R C,Fan W J.The design and performance of a high temperature rise combustor for wind tunnel[J].Journal of Thermal Science,2011,20(6):556-562.
[7]	Sirignano W A,Delplanque J P,Liu F.Selected challenges in jet and rocket engine combustion research[R].AIAA 97-2701,1997.
[8]	Lee A S,Singh R,Probert S D.Performances of a two-combustor turbofan engine under design and off-design conditions[R].AIAA-2008-4901,2008.
[9]	Liu F,Sirignano W A.Turbojet and turbofan engine performance increase through turbine burners[R].AIAA-2000-0741,2000.
[10]	Liew K H,Urip E,Yang S L.A parametric cycle analysis of a separate-flow turbofan with inter-stage turbine burner[R].NASA/CR-2005-213657,2005.
[11]	孙泽晖,蔡元虎.带混排涡轮级间燃烧的涡扇发动机循环参数[J].推进技术,2010,31(2):139-142. SUN Zehui,CAI Yuanhu.Parametric cycle analysis of mixed exhaust turbofan with inter stage turbine burner[J].Journal of Propulsion Technology,2010,31(2):139-142.(in Chinese)
[12]	Zelina J,Ehret J,Hancock R D.Ultra-compact combustor combustion technology using high swirl for enhanced burning rate[R].AIAA-2002-3725,2002.
[13]	Thornburg H,Sekar B,Zelina J.Geometrical parametric studies of inter-turbine burner for improved performance[R].AIAA-2007-5099,2007.
[14]	金如山,索建秦.先进加力燃烧室技术发展[R].北京:中国航空学会第七届动力年会,2010.
[15]	张宝诚.航空发动机试验和测试技术[M].北京:北京航空航天大学出版社,2005.
[16]	Chen G,Hoffman M A,Davis R L.Gas turbine performance improvement through the use of multiple turbine inter-stage burners[J].Journal of Propulsion and Power,2004,20(5):828-834.
[17]	廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005.
[18]	毛艳辉,刘存喜,刘富强,等.级间燃烧室在航空发动机上应用分析[J].航空动力学报,2012,27(3):578-587. MAO Yanhui,LIU Cunxi,LIU Fuqiang,et al.Application analysis of inter stage turbine burner of aero engine[J].Journal of Aerospace Power,2012,27(3):578-587.(in Chinese)
[19]	彭泽琰,刘刚,桂幸民,等.航空燃气轮机原理[M].北京:国防工业出版社,2008.