导风轮轮罩引气对离心式压气机性能影响的数值研究  

Numeric Simulation of Inducer Shroud Bleeding Effect on Centrifugal Compressor Performance

作　　者：戴四敏[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2005年第1期125-129,共5页Journal of Aerospace Power

摘　　要：为了研究扩大离心压气机喘振裕度的实用技术 ,以解决某工程设计中的问题 ,用三维粘性计算流体力学 ( CFD)计算软件对离心压气机导风轮轮罩引气措施进行了数值模拟。该项技术在应用中所涉及的设计参数经过了初步的数值试验。从数值模拟的结果中 。In order to investigate the applied techniques that can be used to enlarge the centrifugal compressor surge-margin and to solve the problem in certain engineering design,3D viscous Computation Fluid Dynamics (CFD) code was used to simulate the inducer shroud bleeding effect on centrifugal compressor performance.Numerical experiments have been carried out to test certain design parameters involved in the application of this technique.The results show that inducer shroud bleeding has a remarkable effect on the centrifugal compressor performance improvement.

关 键 词：航空、航天推进系统 计算流体力学(CFD) 数值模拟 离心压气机 叶轮罩 引气 

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] TK474.8[动力工程及工程热物理—动力机械及工程]