高压涡轮瞬态叶尖径向运行间隙计算分析

Calculation and Analysis for Transient Blade-Tip Radial Running Clearance of HPT

为了改善现代航空发动机整体性能和可靠性,将热分析和结构分析耦合起来,以航空发动机从地面启动到巡航这一过程为研究对象,对涡轮转子进行瞬态叶尖径向运行间隙计算分析。在计算中考虑了材料、温度和离心载荷的非线性,以及惯性力和温度的复杂的边界条件,分别对叶片、轮盘和机匣的变形进行计算和分析,进而得出涡轮叶尖径向运行间隙的变化规律以及与试验相符合的计算结果。该计算分析方法为涡轮叶尖径向运行间隙的概率分析和优化设计奠定了基础。

In order to improve the perfor-mance and the probability of the aeroengine, coupling of thermal analysis and structural analysis, taking the process of aeroengine from the ground to cruise as re-search object, the tip radial running clearance of turbine rotor is analyzed and calculated. In the calculation, the thermal-structure coupled displacements of the casing, disc and blade are analyzed taking into account the non-linear of the material, temperature and centrifugal loads, and the complex boundary conditions of the transient inertia force and the transient temperature, and then it is obtained to the change regularity of blade-tip radial run-ning clearance with time and the reasonable calculation result . The analysis and calculation methodology in this paper is basic of probability analysis and reliability op-timization design for turbine tip radial clearance.