航空发动机尾喷管热流固耦合分析

Abstract

航空发动机尾喷管运行在高温高压的环境中，持续受到复杂载荷影响，其中热载荷和气动载荷是影响尾喷管寿命的主要因素。为了探究不同工作状态下尾喷管的结构动态特性，本文基于有限元分析方法，通过建立仿真技术路线，采用单向热流固耦合方法模拟尾喷管的工作过程，得到模态参数和振型。通过对相同振型在不同工作状态下频率变化的对比分析，揭示了温度场、流场和结构之间的作用关系，这在尾喷管的研制试验中具一定的指导意义。 The aero-engine nozzle works in the high temperature and high pressure environment, which is affected by the complex loads. The thermal load and the aerodynamic load are the main factors influencing the nozzle durability. Aiming at the problem of thermal-fluid-solid coupling for nozzle affected by high intensive pressure and high constant temperature, on the basis of finite element analysis, this paper applies ANSYS to build technology roadmap simulating one-way three fields coupling of an aircraft engine nozzle. Simultaneously, by means of analyzing main coupling characteristics, the results show the relationship among temperature field, flow field and the structure in the modal analysis, which has significant meaning in the design process of nozzle.