跨音速涡轮平面叶栅风洞收缩段设计方法研究  

Wind Tunnel Contraction Design for Transonic Turbine Linear Cascade Test

作　　者：韩建涛[1,2] 王晏根 阳诚武[1] 李紫良 朱俊强[1] 

机构地区：[1]中国科学院工程热物理研究所,北京100190 [2]中国科学院大学,北京100049

出　　处：《燃气轮机技术》2017年第2期17-22,共6页Gas Turbine Technology

基　　金：工业和信息化部民用飞机专项科研项目(MJZ-D-2013-02)

摘　　要：本文基于跨音速平面叶栅试验台的搭建,对入口风洞收缩段进行设计。在收缩比确定的情况下,采用流场特性较好的五次曲线。同时从实际角度出发,重点研究收缩段的长高比(长度与入口高度比值)对出口流场的影响,综合对比不同长高比收缩段出口流场品质(压力、马赫数、边界层厚度等),获得了最优长高比,期望为跨音速平面叶栅实验风洞收缩段的优化设计提供了参考。On the base of constructing a transonic turbine linear test rig, an inlet wind tunnel contraction is designed in this paper. In the case of the convergence ratio is determined, quintic curve is applied for its good aerodynamic performance. Meanwhile, in consider-ation of the rig, this research focuses on the contraction length-height ratio^ effect to the flow field, especially the outlet of the contrac-tion. The flow field quality of different length-height ratio contraction is compared in details （ pressure, mach number, thickness of boundary layer etc. ） and the best length-height ratio is obtained, hoping to provide a reference for the optimal design of windtunnel contration in transonic linear cascade test.

关 键 词：跨音速涡轮 平面叶栅 风洞 收缩段长高比 流场品质 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]