非对称端壁造型对离心压气机性能的影响  

Effects of Non-Axisymmetric Profiled End Wall Treatments on Performance of a Centrifugal Compressor

作　　者：郎进花 楚武利[1,2] 张皓光 安光耀[1] 马姗 LANG Jin-hua;CHU Wu-li;ZHANG Hao-guang;AN Guang-yao;MA Shan(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China;Collaborative Innovation Center of Advanced Aero-Engine,Beijing 100191,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]先进航空发动机协同创新中心,北京100191

出　　处：《推进技术》2020年第6期1286-1295,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(51576162);国家科技重大专项(2017-II-0005-0018)。

摘　　要：非对称端壁造型应用在轴流压气机和涡轮中具有较好的提高效率的作用。为了探究非对称端壁造型对离心压气机性能的影响,借鉴非对称端壁造型在轴流压气机中的设计经验,借助Autoblade和CFX商用软件,设计了四种非对称端壁造型结构,并对带叶片式扩压器的离心压气机展开数值计算研究。研究发现,与原型压气机相比,采用压力面附近为凸曲率形状、吸力面附近为凹曲率形状的非对称端壁造型结构PEW110%(profiled end wall 110%)可以在保证全工况效率不降低的情况下,使离心压气机的性能曲线向小流量和大流量均有拓展,稳定工作范围扩大11.8%。通过分析流场发现,在近喘振工况,非对称端壁造型PEW110%使扩压器通道内流量重新分配,吸力面附近径向速度增大,低能流体减少,改善了扩压器通道的流动状况,进而推迟喘振的发生。The application of non-axisymmetric endwall profiling on both axial compressors or turbines has been determined to be an effective way to increase the efficiency.In order to investigate the effects of non-axisymmetric end wall profiling on the performance of centrifugal compressors,four endwall contouring schemes according to the design experience of non-axisymmetric endwall profiling in axial compressors were performed on a vaned diffuser centrifugal compressor with the help of Autoblade and CFX software.Numerical investigations were conducted on a radial compressor with vane diffuser.The results showed that non-axisymmetric profiled endwall PEW1_10%which was convex near the pressure side and concave near the suction side extended the compressor characteristic performance curve to smaller and higher mass flow rate points which gave a 11.8%improvement of the operating range with no reduction of the efficiency compared with the original compressor.Analysis of the flow field showed that PEW1_10%caused a redistribution of the flux in the diffuser passage at the near surge condition,which further led to an increase of the radial velocity near the suction side and a decrease of the low-energy fluid.As a result,the flow condition in the diffuser passage was improved,and the surge was delayed.

关 键 词：离心压气机 非对称端壁造型 叶片式扩压器 回流区 扩稳 

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]