间冷回热循环航空发动机参数匹配研究

龚昊; 王占学; 刘增文

间冷回热循环航空发动机参数匹配研究

西北工业大学动力与能源学院,西安 710072

基金项目: 国家自然科学基金(51176156); 教育部博士点基金(20106102110025)

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出版历程
- 收稿日期: 2011-09-22
- 刊出日期: 2012-08-28

Study on thermodynamic cycle parameter matching for intercooled recuperated aero-engine

School of Power and Energy, Northwestern Polytechnical University,Xi'an 710072,China

摘要

摘要: 在常规大涵道比涡扇发动机热力循环基础上增加间冷过程和回热过程,发展了间冷回热循环航空发动机(IRA)的计算模型和相应的性能仿真程序.分析了采用间冷回热技术的分排大涵道比涡扇发动机的热力循环参数选择与匹配.结果表明:间冷度、回热度、外涵道间冷用气量、增压级和高压压气机压比分配、总增压比、涵道比等热力循环参数对IRA的性能有很大影响;合理应用间冷回热技术,并优化发动机热力循环参数匹配可以显著改善发动机的性能.
- 间冷 /
- 回热 /
- 航空发动机 /
- 热力循环参数 /
- 匹配
Abstract: The intercooled and recuperated processes were incorporated into the conventional high bypass turbofan engine thermodynamic cycle.Consequently,the intercooled recuperated aero-engine (IRA) simulation model was built and an overall performance simulation program was developed.Then,analysis on choosing and matching the thermodynamic cycle parameters of IRA was conducted.The result indicates that there are some thermodynamic cycle parameters such as intercooler effectiveness,recuperator effectiveness,bypass intercooling split,pressure ratio assignment between booster and high pressure compressor,overall pressure ratio and bypass ratio,which have significant influence on IRA performance.The turbofan engine performance can be improved with the proper use of intercooling, recuperation and the optimized matching of the thermodynamic cycle parameters.
- intercooled /
- recuperated /
- aero-engine /
- thermodynamic cycle parameter /
- matching

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参考文献(13)

[1]	Krammer P,Rued K,Truebenbach J.Technology preparation for green aero engines .AIAA-2003-2790,2003.
[2]	McCarthy L S,Scott M L.The WR-21 intercooled recuperated gas turbine engine-operation and integration into royal navy type 45 destroyer power system .ASME Paper GT-2002-30266, 2002.
[3]	Wilfert G,Sieber J,Rolt A,et al.New environmental friendly aero engine core concepts .ISABE-2007-1120,2007.
[4]	Rolt A M,Kyprianidis K G.Assessment of new aeroengine core concepts and technologies in the EU framework 6 NEWAC programme .ICAS-2010-408,2010.
[5]	Boggia S,Rud K.Intercooled recuperated aero engine .München,Germany:MTU Aero Engines,2004.
[6]	Gmelin T C,Hüttig G,Lehmann O.Summarized description of aircraft efficiency potentials taking account of current engine technology and foreseeable medium-term developments .Berlin,Germany:German Federal Ministry for the Environment,Nature Conservation and Nuclear Safety,FKZ UM 07 06 602/01,2008.
[7]	余建祖.换热器原理与设计[M].北京:北京航空航天大学出版社,2006.
[8]	吴丁毅,马明明,马峰,等.舰用燃气轮机间冷回热改造计算研究[J].机械设计与制造,2007(11):47-49. WU Dingyi,MA Mingming,MA Feng,et al.Calculation study of intercooled recuperated alteration of gas turbine for naval ships[J].Machinery Design & Manufacture,2007(11):47-49.(in Chinese)
[9]	廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2008.
[10]	Sellers J F,Daniele C J.Dyngen:a program for calculating steady-state and transient performance of turbojet and turbofan engines .NASA TND-7901,1975.
[11]	Marx M.Investigation and optimisation of intercooling in an intercooled recuperated aero engine .UK:School of Engineering,Cranfield University,2007.
[12]	McDonald C F,Rodgers C.Heat exchanged propulsion gas turbines:a candidate for future lower sfc and reduced emission military and civil aeroengines .ASME Paper GT-2009-59156,2009.
[13]	曹梦源,唐海龙,陈敏.中冷回热航空涡扇发动机热力循环初步分析[J].航空动力学报,2009,24(11):65-70. CAO Mengyuan,TANG Hailong,CHEN Min.Preliminary analysis of thermodynamic cycle of an intercooled recuperated turbofan engine[J].Journal of Aerospace Power,2009,24(11):65-70.(in Chinese)