涡轮气热弹耦合计算模型与算例  

Calculation Model and Calculation Examples for Thermal-flow-elastic Conjugate Simulation of Turbine Engine

作　　者：郭兆元[1] 王强[1] 冯国泰[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空学报》2009年第2期213-219,共7页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50476028)

摘　　要：针对涡轮气热弹多场耦合不变量方程,推导了任意曲线坐标系中的多场耦合控制方程,讨论了气热弹多场耦合的4种类型:气热、气弹、热弹和气热弹耦合,给出了相应的计算模型与耦合边界条件,建立了能够采用统一差分格式求解涡轮气热弹多场耦合的三维数值仿真平台的计算模型。并通过对一个具有解析解空心圆筒的热弹性计算和对MarkⅡ叶片气热耦合计算,初步验证了应用有限差分计算气热弹多场耦合计算模型的可行性。Based on the invariant equation for thermal-flow-elastic conjugate simulation of turbine engines, the multi-field conjugate governing equation in curvilinear coordinate systems is derived. Calculation models and conjugate boundary conditions of different multi-field coupling types are presented, including thermal-flow, aeroelastics, thermal elastic, and thermal-flow elastic couplings. Then a calculation model of 3D thermal-flow- elastic conjugate simulation platform for turbines is constructed, to which the finite difference method is conveniently applied. The thermal-elastic simulation of a hollow cylinder and the conjugate heat transfer simulation of a Mark Ⅱ blade are accomplished. The numerical results are compared to analytic solutions and experimental results. Thus the feasibility of applying finite difference method to thermal-flow-elastic coupling is validated.

关 键 词：涡轮 数值仿真 气热弹耦合 计算模型 可行性 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]