单级低压涡轮气动设计方法研究  

Method Investigation of One-stage Axial Turbine Aero-dynamical Design

作　　者：张培[1] 楚武利[1] 吴艳辉[1] 张扬[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《计算机仿真》2010年第1期102-105,共4页Computer Simulation

基　　金：西北工业大学研究生创业种子基金资助(200825)

摘　　要：研究一套单级轴流式涡轮气动设计仿真程序。在通流设计阶段,融入了先进的可控涡和可变涡轮功设计思想,有着AMDC、Soderberg、Carter三种模型可供选择。仿真程序采用一种新的涡轮平面叶栅反设计方法,相比传统反设计算法,更加简单实用;在原有理论基础上,引入非均匀有理B样条曲线,改进了前、后倒圆生成方法,消除了低能阻塞区;为验证设计程序,给出了单级涡轮设计实例进行仿真,结果表明程序稳定,可以实现涡轮叶片设计,叶片通道收敛效果良好。An one-stage axial turbine aero-dynamical design computer program was completed.In the phase of through-flow design,controlled-vortex design method and variable turbine work design approach were introduced,in which three loss models could be chosen,namely AMDC,Soderberg,Carter.For the part of plane cascade design,a new turbine cascade inverse design method was adopted,which was more feasible compared with traditional inverse design method.The inverse method was improved through using NURBS curve in the aspect of leading and trailing edge design.To testify turbine design computer program,an one-stage axial turbine was designed.The result revealed that the program was robust,and the turbine blade design algorithm was feasible.

关 键 词：轴流涡轮 可控涡 可变涡轮功 反设计 

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]