Experimental Study of Effects of One Kind of Tangentially Non-uniform Tip Clearance on the Flow Field at an Exit of a Compressor Cascade Passage  

作　　者：Hongwei MA Jinghui ZHANG Jun ZHANG 

机构地区：[1]School of Jet Propulsion, Beihang University, Beijing, 100191, China [2]National Key Laboratory of Science and Technology on Aero-Engines, Beijing, 100191, China

出　　处：《Journal of Thermal Science》2010年第1期7-13,共7页热科学学报（英文版）

基　　金：funded by the National Natural Science Foundation of China, Grant No 50776004;supported by the 111 Project, No B07009;973 Project, No 2007CB210103

摘　　要：This paper presents an experimental investigation of effects of one kind of tangentially non-uniform tip clearance on the flow field at an exit of a compressor cascade passage.The tests were performed in a low-speed large-scale cascade with the uniform tip clearance and the non-uniform clearance.The three-dimensional flow field was measured at the exit at three incidence angles of 0°,5°,and 8° using a mini five-hole pressure probe.The measurement results show that the non-uniform tip clearance can moderate the leakage flow and blow down more low-energy fluids at the tip corner and decrease the accumulation of low-energy fluids which cause the flow blockage in the blade passage.In the meantime,the non-uniform clearance can weaken the tangential migration of the low-energy fluids in the endwall boundary layer and reduce the secondary loss and the flow blockage in the tip region.This paper presents an experimental investigation of effects of one kind of tangentially non-uniform tip clearance on the flow field at an exit of a compressor cascade passage. The tests were performed in a low-speed large-scale cascade with the uniform tip clearance and the non-uniform clearance. The three-dimensional flow field was measured at the exit at three incidence angles of 0~, 5~, and 8~ using a mini five-hole pressure probe. The meas- urement results show that the non-uniform tip clearance can moderate the leakage flow and blow down more low-energy fluids at the tip corner and decrease the accumulation of low-energy fluids which cause the flow blockage in the blade passage. In the meantime, the non-uniform clearance can weaken the tangential migration of the low-energy fluids in the endwall boundary layer and reduce the secondary loss and the flow blockage in the tip region.

关 键 词：compressor cascade CLEARANCE leakage flow secondary flow vortex 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] TK123[动力工程及工程热物理—工程热物理]