高压涡轮导向器扇形叶栅试验研究  

Experimental Investigation on the Sector Cascade of High Pressure Turbine Guide

作　　者：姜正礼[1] 凌代军[1] 王晖[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2006年第1期17-20,53,共5页Gas Turbine Experiment and Research

摘　　要：本文介绍了国内首次在平面叶栅风洞上进行的涡轮导向器扇形叶栅的试验方法和试验结果。扇形段由五个真实的高压涡轮导向叶片组成。试验中通过调整扇形段出口凸块的高度,可以获得满足要求的径向压力梯度。试验结果表明:该涡轮导向器扇形段叶栅在M2h≤1．05时,叶中截面处在带冷气和不带冷气时出口气流参数周向分布较均匀,周期性较好;在设计状态下,带冷气和不带冷气时靠近叶中的几个截面的出口气流参数沿径向的分布变化很小。This paper presents the experimental methods and experimental results of the sector cascade of HP turbine guide. It was first test by a domestic plane cascade wind tunnel. The sector cascade consists of five vanes operating at HP turbine guide. The experimental results shows： the desired radial pressure gradient can be obtained by means of adjusting height of convex block at cascade outlet and at M2h≤1.05, the sector cascade outlet aerodynamic parameter was uniform and its periodicity was good too on the middle section of blade. At design condition and with cooled air injection, outlet aerodynamic parameter changed a little along radial among middle sections of blade.

关 键 词：高压涡轮 扇形叶栅试验 试验方法 试验结果 

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]