径流与斜流涡轮设计的通流反问题方法  

A through flow inverse design approach for radial and mixed-flow turbines

作　　者：赵彬[1] 单鹏[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2008年第3期476-482,共7页Journal of Aerospace Power

摘　　要：自主发展了径流及斜流涡轮的准三维流线曲率法通流设计程序,应用该程序给出了一项500 N推力级微型涡喷发动机斜流涡轮的气动设计和叶片造型.通过计算流体力学检验和整体叶轮强度检验,该微型斜流涡轮超过了预定的设计指标.为实现径流涡轮和斜流涡轮设计反问题的统一,流线曲率法的S2,m流面准径向平衡方程是沿流线方向m和流线的准法线方向q写出,该系统也可用于轴流涡轮的设计.采用了在所有计算站上的"全可控涡法"进行气动设计.A code of quasi-3D streamline curvature was developed through flow method for the inverse design of radial and mixed-flow turbines. This code was used to design a single stage mixed-flow type turbine which served as the turbine of a micro-turbojet engine with a thrust of 500 N. By computational fluid dynamics examination of the turbine stage and intensity evaluation of the blisk, it is proved that the micro-turbine design has achieved all its design goals. To realize consolidation of design schemes for centripetal-, centrifugal-and mixed-flow turbines,S2.m, streamline curvature equilibrium equation was written along the directions of both the streamline ‘m＇ and the streamline＇s quasi-normal-line ‘q＇. Thus this scheme can also be used in the design of axial-flow turbine. The through flow design code utilized the ‘whole controllable vortex＇ method in all computation stations.

关 键 词：航空 航天推进系统 叶轮机设计反问题 径流式涡轮 斜流式涡轮 流线曲率法 全可控涡法 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]