基于模型的涡轮叶尖间隙快速预测方法  

Fast Prediction Method for Turbine Tip Clearance Based on Model

作　　者：雷杰[1] 许艳芝[1] 郭政波 LEI Jie;XU Yan-zhi;GUO Zheng-bo(Engine Department of Chinese Flight Test Establishment, Xi′an Shaanxi 710089, China)

机构地区：[1]中国飞行试验研究院发动机所,陕西西安710089

出　　处：《机械研究与应用》2019年第1期77-80,85,共5页Mechanical Research & Application

摘　　要：针对发动机涡轮叶尖间隙变化预测需求,以涡轮叶尖间隙热控制法为研究对象,采用了一种简化的涡轮叶尖间隙计算模型,针对某型发动机高压涡轮的结构特点,分别建立了涡轮机匣、轮盘、叶片的计算模型。以发动机数学模型计算结果作为输入,对高压涡轮叶尖间隙变化进行了仿真计算,结果表明模型计算的涡轮叶尖间隙变化与实际工作过程相符,可在发动机初步方案设计阶段为叶尖间隙评估提供一种快速预测方法。Aiming at the demand for engine turbine tip clearance variation prediction, a simplified calculation model of turbine tip clearance was adopted by taking the thermal control method of turbine tip clearance as the research object. According to the structural characteristics of a certain engine high-pressure turbine, the calculation models of turbine casing, rotating disk and blade are established respectively. Taking the results of engine mathematical model as input, the blade tip clearance variation of high pressure turbine is simulated. The results show that the change of turbine tip clearance calculated by the model is consistent with the actual working process, which can provide a fast prediction method for tip clearance assessment in the initial engine design phase.

关 键 词：涡轮叶尖间隙 数学模型 引气和冷却系统 大涵道比涡扇发动机 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]