相似设计在某风扇改型设计中的应用

冀国锋; 王华青; 桂幸民; 邓少春

相似设计在某风扇改型设计中的应用

1.
中国航空工业集团公司贵州航空发动机研究所,贵阳 550081
2.
北京航空航天大学能源与动力工程学院,北京 100191

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出版历程
- 收稿日期: 2010-05-20
- 刊出日期: 2012-10-28

Application of similitude theory in modified design of a fan

1.
Guizhou Aero-engine Research Institute, Aviation Industry Corporation of China,Guiyang 550081,China
2.
School of Jet Propulsion,Beijing University of Aeronautics and Astronautics, Beijing 100191,China

摘要

摘要: 针对某涡扇发动机推力增大的动力需求,在充分分析原型风扇性能和流场的基础上,对原型风扇进行了改型设计.改型设计的方法采用“轴流/离心压气机通用叶片造型设计系统”,依据相似理论,在保证第2级风扇进口的相似准则和原型一致,即保证改型与原型第2级风扇在进口的换算流量和换算转速相等的前提下,来增大第1级风扇的流量和压比.经过三维流场计算和分析,结果表明:在风扇转速提高到1.011的情况下,流量提高到1.071,压比提高到1.074,效率提高到1.029,裕度比原型提高了0.8%,达到了性能指标的要求,改型设计结果比较理想.总体对风扇的性能和整机匹配性分析和评估表明:该风扇改型设计方案能够满足该涡扇发动机推力增大的需求.
- 风扇 /
- 相似准则 /
- 气动设计 /
- 改型设计 /
- 换算流量 /
- 换算转速
Abstract: A modified design of a fan was described, on the basis of enough performance and flow field analysis of original fan, in order to satisfy the more thrust requirement of a turbo-fan engine. The modified design method was: the design tool was “a general blading design system and its application for axial/centrifugal compressor”. According to the similitude theory, at the precondition of the equivalence of converse mass flow and converse revolution speed at the second stage inlet, the increase of the mass flow was growing with the pressure ratio. By CFD computation and analysis, all the performances met the requirement and the design result was perfect. The results show that as the speed of the fan increases 1.1 percent, the mass flow increases 7.1 percent, the pressure ratio increases 7.4 percent, the efficiency increases 2.9 percent, and the stall marge increases 0.8 percent. Analysis and valuation of the performance and matching characteristic indicate that this design can satisfy the more thrust requirement of the turbo-fan engine.
- fan /
- similitude theory /
- aerodynamic design /
- modified design /
- converse mass flow /
- converse revolution speed

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参考文献(15)

[1]	彭泽琰,刘刚.航空燃气轮机原理:上册[M].北京:国防工业出版社,2000.
[2]	舒士甄,朱力,柯玄龄.叶轮机械原理[M].北京:清华大学出版社,1991.
[3]	北京航空航天大学能源与动力工程学院流体机械系.叶轮机械原理讲义[M].北京:北京航空航天大学,2003.
[4]	北京航空航天大学能源与动力工程学院流体机械系.叶轮机械原理[M].北京:北京航空航天大学,2007.
[5]	王华青,陈懋章.高负荷高通流跨音压气机的研制和应用[J].航空动力学报,2003,18(2):175-180. WANG Huaqing,CHEN Maozhang.Development and application of a high load and high throughflow transonic compressor[J].Journal of Aerospace Power,2003,18(2):175-180.(in Chinese)
[6]	冀国锋.轴流/离心压气机通用叶片造型设计系统及应用 .北京:北京航空航天大学,2009. JI Guofeng.A general balding design system and its application for axial/centrifugal compressor .Beijing:Beijing University of Aeronautics and Astronautics,2009.(in Chinese)
[7]	桂幸民.轴流风扇/压气机可控激波跨音级模型设计研究 .北京: 北京航空航天大学,1993. GUI Xingmin.The research on the model of controllable shock wave used in the design of transonic axial fan/compressor stage .Beijing:Beijing University of Aeronautics and Astronautics,1993.(in Chinese)
[8]	冀国锋,桂幸民.轴流/离心压气机叶片通用任意中弧造型设计方法[J].航空动力学报,2009,24(1):150-156. JI Guofeng,GUI Xingmin.A blading design method for axial/centrifugal compressor airfoils using arbitrary camber lines[J].Journal of Aerospace Power,2009,24(1):150-156.(in Chinese)
[9]	Frost G R,Hearsey R M,Wennerstrom A J.A computer program for the specification of axial compressor airfoils . Ohio:Aerospace Research Laboratories,Wright-Patterson Air Force Base,ARL 72-0171,AD 756879,1972.
[10]	Crouse J E,Janetzke D C,Schwirian R E.A computer program for composing compressor blading from simulated circular-arc elements on conical surfaces .Cleveland,Ohio:Lewis Research Center,NASA TN D-5437,1969.
[11]	Frost G R,Wennerstrom A J.The design of axial compressor airfoils using arbitrary camber lines .Ohio:Arospace Research Laboratories,Wright-Patterson Air Force Base,ARL 73-0107,AD 765165,1973.
[12]	桂幸民,李晓娟.基于低雷诺数条件的风扇/增压级气动设计[J].燃气涡轮试验与研究,2007,20(3):18-22. GUI Xingmin,LI Xiaojan.Aerodynamic design of fan/compressor operated at low Reynolds number[J].Gas turbine experiment and research,2007,20(3):18-22.(in Chinese)
[13]	殷明霞,桂幸民.高速微型离心压气机的改型设计[J].燃气涡轮试验与研究,2007,20(3):57-60. YIN Mingxia,GUI Xingmin.Redesign of a high speed micro-centrifugal compressor[J].Gas turbine experiment and research,2007,20(3):57-60.(in Chinese)
[14]	冀国锋,殷明霞,桂幸民.某小型离心压气机气动设计[J].航空动力学报,2010,25(3):557-564. JI Guofng,YIN Mingxia,GUI Xingmin.Aerodynamic design of a small centrifugal compressor[J].Journal of Aerospace Power,2010,25(3):557-564.(in Chinese)
[15]	冀国锋,王伟,桂幸民.某小型离心压气机扩稳优化设计[J].航空动力学报,2010,25(3):571-576. JI Guofng,WANG Wei,GUI Xingmin.Optimization design of a small centrifugal compressor[J].Journal of Aerospace Power,2010,25(3):571-576.(in Chinese)