重气体离心压缩机三元叶轮的设计及实验  

DESIGN AND EXPERIMENT OF CENTRIFUGAL COMPRESSOR 3-D IMPELLERS FOR HEAVY GASES

作　　者：王尚锦[1] 席光[1] 刘士学[1] 袁沿 王世池 

机构地区：[1]西安交通大学 [2]重庆通用机器厂

出　　处：《航空动力学报》1995年第2期170-172,共3页Journal of Aerospace Power

摘　　要：利用一种基于准三元流动理论Ｓ２流面的逆命题方程，研究了重气体离心压缩机三元叶轮的设计方法及提高性能的措施。对设计的两个三元叶轮模型级进行了实验测量，获得了优良的性能曲线。还研究了不同工况下叶轮出口动压分布，分析了各部件的损失特性。An inverse problem method based on s 2 flow surface theory of 3 D flow field has been developed to design centrifugal compressor impellers for heavy gases and some techniques to improve the performance of high pressure ratio impellers have been presented too.Two impellers with Mach number M u 2 =1 26,1.06 and relative width b 2/D 2=0 054,0 036 respectively have been designed by use of this method.Experiments of the impellers have been performed in a closed loop test rig with Freon gases (R11) to verify the design method.The dynamic pressures distribution from shroud to hub at the exits of impellers and the losses of vaneless diffusers and volutes have been measured and analyzed under different work points.Their good performance obtained from tests shows the design method and techniques presented in this paper is feasible and favourable.

关 键 词：离心压缩机 三元叶轮 设计及实验 

分 类 号：TH452[机械工程—机械制造及自动化]