通用核心机涡轮气动设计准则  

Turbine aerodynamic design criteria of versatile core

作　　者：付超[1] 邹正平[1] 刘火星[1] 李维[2] 周颖[2] 

机构地区：[1]北京航空航天大学能源与动力工程学院/航空发动机气动热力重点实验室,北京100191 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《推进技术》2011年第2期165-174,共10页Journal of Propulsion Technology

基　　金：国家自然科学基金(50776003)

摘　　要：针对通用核心机对涡轮部件性能的要求,尝试给出了描述涡轮气动通用性的定义,研究了速度三角形系列参数对涡轮气动通用性的影响规律,在此基础上,得到了通用核心机涡轮部件气动设计参数选取准则,并通过S2和三维数值模拟手段,利用一组真实涡轮的数据对涡轮气动通用性的定义和设计参数选取准则进行了验证。结果表明:在涡轮设计参数选择中,存在使涡轮部件气动通用性最优的速度三角形参数范围;一般情况下气动设计参数在Ω=0.35～0.45,μ=1.65～1.9,K1=0.55～0.6区域内时,所设计的涡轮气动通用性较好;一系列涡轮气动设计参数的分析表明本文给出的涡轮部件气动通用性的定义和得到的涡轮部件气动设计参数选取准则基本合理。In allusion to the requirement of designing versatile core,a definition of the aerodynamics versatility of turbine was demonstrated.Primarily,by analyzing the laws that parameters of velocity triangle affect the aerodynamic versatility,a design criterion of designing turbine aerodynamics of versatile core was put forward.Then numerical simulation with S2 and 3D viscous solvers was carried out,comparing with a set of details of some real turbines,to validate the definition and laws which describes the aerodynamics versatility of turbine.The results indicate that there is a range of selecting velocity triangle parameters which may contribute to an optimal design of aerodynamics versatility of turbine,especially,when selecting the parameters of velocity triangle,Ω=0.35~0.45,μ=1.65~1.9,K1=0.55~0.6,the aerodynamics versatility of turbine was proved to be good.The analysis of the parameters of aerodynamics design of turbines was provided,and thus it is reasonable and credible to conclude that the definition of the aerodynamics versatility of turbine and the laws of selecting the aerodynamics design factors to design versatile core are valid.

关 键 词：通用核心机 涡轮 速度三角形 气动设计 准则 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]