弱化激波涡轮叶栅研究  

Study on Optimal Transonic Turbine Cascade of Weakening Shock

作　　者：余佳[1] 马伟涛[1] 季路成[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《工程热物理学报》2015年第12期2584-2588,共5页Journal of Engineering Thermophysics

基　　金：自然科学基金(No.51376023;No.51176012)

摘　　要：激波问题严重影响超/跨音涡轮气动性能、冷却特性和结构完整性,因而,弱化激波设计是高负荷涡轮研究的热点之一。针对这一问题,本文以两个典型超/跨音涡轮叶栅为例,以伴随方法寻优为手段,给定流量和出口气流角约束,在不同工况点下进行优化,并对比研究变工况特性、流动特征和造型参数,探索弱化激波涡轮叶栅设计技术及规律。The shock waves have serious impacts on the aerodynamic performance,cooling characteristics and integrity of structure of supersonic/transonic turbines.Hence,the nozzle/blade design with weakened shock wave is one of the research hotspots of highly-loaded turbine.The paper focuses on this aspect.Two typical Russia supersonic/transonic turbine cascades under different design conditions are selected as examples.By using the adjoint method with the constraints of mass flow rate and outflow angle to find the best geometry parameters for the optimum aerodynamic performance at three different back pressures respectively.Their performance,flow characteristics and geometric parameters are compared to explore the design technology and rules of the turbine cascades with reduced shock wave.

关 键 词：超/跨音涡轮叶栅 弱化激波设计 伴随优化 

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]