跨声速多级轴流压气机非设计性能预测

杜文海; 吴虎; 黄健

跨声速多级轴流压气机非设计性能预测

西北工业大学动力与能源学院, 西安 710072

计量
- 文章访问数: 1918
- HTML浏览量: 375
- PDF量: 478
- 被引次数: 0
出版历程
- 收稿日期: 2006-08-24
- 修回日期: 2006-12-29
- 刊出日期: 2007-09-28

Off-design performance prediction of multi-stage transonic axial compressor

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

摘要

摘要: 基于公开发表的研究成果, 发展了一种适用于跨声速轴流压气机的新型损失和落后角模型, 并进行了3-D的修正, 运用改进的流线曲率法对某两级跨声速轴流压气机进行了数值模拟, 得到了设计点和非设计点的特性曲线.通过计算结果与实验值的比较, 验证了本模型和方法在设计点和非设计点均具较高的精度, 可用于工程计算.
- 航空、航天推进系统 /
- 流线曲率法 /
- 跨声速 /
- 轴流压气机 /
- 非设计 /
- 损失落后角模型
Abstract: A new loss and deviation model suitable for multi-stage transonic axial compressor was developed according to the research findings publicly available.Along with 3-D modification,numerical simulation was performed for two-stage transonic axial compressor using an improved streamline curvature method,thus obtaining the characteristic curve of design point and off-design point.By combining the calculated results with experimental value,this model and method are suitable for engineering calculation with higher accuracy of design point and off-design point.
- aerospace propulsion system /
- streamline curvature /
- transonic /
- axial compressor /
- off-design /
- loss and deviation model

HTML

参考文献(12)

[1]	Denton J D.Computational fluid dynamics for turbomachinery design[J].J.Mech.Eng.Sci,1999,213(c2).
[2]	Boyer K M.An improved streamline curvature approach for off-design analysis of transonic compression systems[D].Blacksburg,VA:Ph.D.Dissertation,Mechanical Engineering Dept.Virginia Polytechnic Institute and State University,April,2001.
[3]	Joseph E.Identification and evaluation of loss and deviation models for use in transonic compressor stage performance prediction[D].Blacksburg,VA:MS Thesis,Mechanical Engineering Dept.Virginia Polytechnic Institute and State University,September,1997.
[4]	Cetin M,Ucer A S,Hirsch CH,et al.Application of modified loss and deviation correlations to transonic axial compressors[R].AGARD-R-745,1987.
[5]	Bloch G S,Copenhavor W W,O' Brien W F.A shock loss model for supersonic compressor cascades[J].Transactions of the ASME,Journal of Turbomachinery,January,1999,121:28-35.
[6]	秦鹏译.轴流压气机气动设计[M].北京:国防工业出版社1975.
[7]	White N M,Tourlidakis A,Elder R L.Axial compressor performance modelling with a quasi-one-dimensional approach[J].Proc Instn Mech Engrs,Part A:J Power and Energy,2002,216.
[8]	Creveling H F,Carmody R H.Axial-flow compressor computer program for calculating off-design performance[R].NASA-CR-72472,1968.
[9]	Klepper J.Technique to predict stage-by-stage,pre-stall compressor performance characteristic using a streamline curvature code with loss and deviation correlations[D].Knoxville,TN:MS Thesis,University of Tennessee,August.1998.
[10]	Koch C C,Smith L H Jr.Loss sources and magnitudes in axial-flow compressors[J].Transactions of the ASME,Journal of Engineering for Power,July,1976:411-424.
[11]	Miller G R,Lewis G W Jr,Hartmann M J.Shock losses in transonic compressor blade rows[J].Transactions of the ASME,Journal of Engineering for Power,July 1961:235-242.
[12]	Urasek D C,Gorrell W T,Cunnan W S.Performance of two-stage fan having low-aspect-ratio,first-stage rotor blading[R].NASA TP-1493,1979.