微型单叶轮涡扇发动机若干总体问题

单鹏; 兰可

微型单叶轮涡扇发动机若干总体问题

单鹏,
兰可

北京航空航天大学能源与动力工程学院, 北京 100083

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出版历程
- 收稿日期: 2006-04-14
- 修回日期: 2006-09-19
- 刊出日期: 2007-05-28

Overall design study of micro-turbofan engine using single blisk of fan and compressor rotor

SHAN Peng,
LAN Ke

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 对低增压比微型涡扇的总体气动热力学有效性进行了基础性的研究.结果表明, 该类发动机仍可有效地降低耗油率, 因而有发展的必要.进一步, 为解决微型涡扇发动机的结构复杂性困难, 提出了一种微型高矮叶片单叶轮风扇压气机的压缩系统气动布局和结构设计方案.借助一个具体例子的设计研究和流场检验的结果, 陈述了该方案的转子、静子的气动设计和结构设计特点.最后拟出了相应的发动机主体结构.
- 航空、航天推进系统 /
- 推进系统特性 /
- 微型发动机 /
- 涡轮风扇发动机 /
- 斜流压气机 /
- 高矮叶片单叶轮风扇压气机
Abstract: The presented overall aero-thermodynamic cycle analysis and engine flight altitude-velocity performance simulation revealed that with a group of well compromised parameters,the micro-turbofan engines with today commonly used low pressure ratio is still efficient for a lower specific fuel consumption(SFC) than that of turbojet.Furthermore,to resolve the difficulties of complex structure in micro-turbofan engines,a newly conceived integral fan-compressor component with both high-low blades and splitter blades is claimed.The features of the aerodynamic design and structural design of the new type fan-compressor component are introduced briefly.Finally one of the principia overall structure design of this kind of turbofan engine was worked out.
- aerospace propulsion system /
- performance of propulsion system /
- micro-engine /
- turbofan engine /
- mixed flow type compressor /
- high-low blades single rotor fan and compressor

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参考文献(3)

[1]	美Oates G C 主编.燃气涡轮发动机气动热力学理论及其应用(上册)[M].张逸民,李燕生,译.吴大观,沈炳正,校.北京:国防工业出版社,1988.
[2]	McKinney J S.Simulation of turbofan engine.Part I.Description of method and balancing technique[R].AFAPL-TR-67-125-pt.-1,Air Force Aero Propulsion Lab.AD-825197,1967.
[3]	单鹏.多变量推进系统数学模型中的矢量空间及其分解[J].航空学报,1997,18(1):78-82.Shan Peng.Vector space and its resolution in propulsion system's mathematical model[J].Acta Aeronautica et Astronautica Sinica,1997,18(1):78-82.