最小喉道面积比对多级轴流压气机性能影响  

Effects of Minimum Throat Area Ratio on Multistage Axial-Flow Compressor Performance

作　　者：邓熙[1] 刘波[1] 李俊[1] 

机构地区：[1]西北工业大学动力与能源学院/翼型叶栅国防科技重点实验室,陕西西安710072

出　　处：《推进技术》2015年第1期47-53,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金重点项目(51236006)

摘　　要：为了研究最小喉道面积比对多级轴流压气机性能的影响,开发了一套基元叶栅最小喉道面积比的计算程序。通过对基元叶栅进行最小喉道面积比计算,得到压气机叶片沿展向的最小喉道面积比分布,同时分析了转子和静子的最小喉道面积比分布规律。最后采用修改基元叶型的前段弯度比与最大厚度来改变基元叶栅的最小喉道面积比分布,分析了不同最小喉道面积比分布对多级轴流压气机性能的影响。结果表明,压气机的阻塞流量与最小喉道面积比成正相关,并且存在最佳前段弯度比使压气机设计点效率与压比达到最大,最大厚度变小能改善压气机整体性能。A set of process for calculating primitive cascades minimum throat area ratio was built,in order to study the effects of minimum throat area ratio on multistage axial-flow compressor performance. The span-wise distribution of minimum throat area ratio was obtained through calculating primitive cascade , and the minimum throat ratio distribution rule of rotor and stator are analyzed. Then the front camber ratio and maximum thickness of primitive blade was modified to study the different distribution of minimum throat area ratio impacting on multi-stage axial-flow compressor performance. The result shows that block mass-flow and minimum throat area ratio have a linear relationship. Having a best front camber ratio makes the compressor total pressure ratio and efficien-cy to achieve the maximum at design point. And reducing thickness is able to improve compressor performance.

关 键 词：喉道面积比 多级压气机 阻塞流量 基元叶型 弯度比 最大厚度 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]