采用改进减缩模型的涡轮叶尖间隙快速分析方法  

Modified reduced model for rapid analysis of tip clearance of high pressure turbine

作　　者：杨晓光[1] 黄佳[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2012年第9期2048-2055,共8页Journal of Aerospace Power

摘　　要：改进了一种预测涡轮叶尖间隙的缩减模型,此模型可模拟发动机各工况下温度、转速和压差对间隙的影响.利用该改进模型在某发动机高压涡轮结构设计中进行叶尖间隙计算,结果显示改进的模型能较好地揭示各工况下叶尖间隙的变化规律.此分析模型只需要输入发动机总体参数、几何参数、基本的材料参数以及传热参数,便能快速得到各个工况下叶尖间隙的变化规律,从而找出最小和最大间隙值及发生时所在工况,可在发动机初步方案设计阶段为叶尖间隙评估提供一种高效率的方法.Considering the effects of temperature,rotating speed and pressure difference in engine operating conditions for predicting changes in turbine tip clearance,a modified reduced model was presented.In the process of designing structures for high pressure turbine in an aircraft engine,tip clearance was predicted using this modified model,and results show that the modified model can predict tip clearance changes into engine operating conditions more accurately.By simply inputting geometric,heat transfer,material and population parameters in this model,the variation of tip clearances can be obtaine quickly,and the conditions when the maximum and minimum tip clearance happened can be determined.Therefore,this method can be a way to evaluate tip clearance efficiently during the preliminary design of an aircraft engine.

关 键 词：航空发动机 高压涡轮 叶尖间隙 缩减模型 数值分析 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]