摘要
目前 ,大量的可控扩散叶型 (CDA)已设计应用于多级轴流压气机中。通过亚音、跨音叶栅实验 ,证明了在可比的气动设计条件下 ,CDA叶栅可以达到更高的临界马赫数、更大的冲角范围和更高的负荷。通过单级或多级测试 ,CDA提供了更高的效率、更高的负荷、且易于进行级间匹配 ,并最终减少研发费用 ,提高喘振裕度 ;由于 CDA叶型具有增厚的前缘和尾缘 。
A series of Controlled Diffusion Airfoils (CDA) has been developed for multistage compressor application.These airfoils are designed analytically to be shock free at transonic Mach numbers and to avoid the separation of the suction surface boundary layer for a range of inlet conditions necessary for stable compressor operation.From the results in the cascade testing,it has been demonstrated that CDA has higher critical Mach number,higher incidence range,and higher loading capability than standard series airfoils designed for equivalent aerodynamic requirements.By using these airfoils in single and multistage rig testing,the high efficiency,the high loading capability and good stage matching can be obtained,the costs can be reduced and the surge margin can be improved.The CDA profile shapes tend to have thicker leading and trailing edges than the conventional standard series profiles,which lead to the improvement of compressor durability.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第1期16-22,共7页
Journal of Aerospace Power
基金
国家自然科学基金资助项目 ( 5 0 0 760 0 9)
973项目 ( G19990 2 2 30 7)
国家教育部全国优秀博士学位论文作者专项基金资助项目 ( 199932 )
