中心进气转静盘腔的流量分配特性试验  

Experimental study of flow distribution characteristics for a rotor-stator system

作　　者：罗翔[1] 徐国强[1] 蔡毅[2] 陶智[1] 丁水汀[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力重点实验室,北京100083 [2]西安航空发动机(集团)有限公司,西安710021

出　　处：《航空动力学报》2007年第6期873-876,共4页Journal of Aerospace Power

摘　　要：采用实验方法,对具有中心进气、两个出口的盘腔系统的流动特性进行了研究.获得了静盘与转盘间隙以及转盘外缘小孔的冷气流量.结果表明:盘面出流孔的流量随总流量或转速的增加而增加,该流量与总流量的流量比随总流量的增加而降低,随着转速增加而增加.盘面出流孔数量为原出流孔数量的一半时,流出流量也近似是原流出流量的一半.The flow characteristics of rotor-stator cavity system with blade-cooling flow and disk-cooling flow was experimentally studied. And, the cooling flow rate of the clearance between stator and rotor as well as the hole of rotor flange was obtained. The experimental results show that：the blade-cooling flow rate will increase with the total flow rate and rotating speed;the ratio of the blade-cooling flow rate to the total flow rate will increase with decline of the total flow rate, and increases with the rotating speed. The blade air flow is almost half of original flow when the numbers of holes become half of original holes.

关 键 词：航空 航天推进系统 燃气轮机 涡轮转子 涡轮静子 流量测量 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]