静态不均匀涡轮叶尖间隙下发动机性能分析  

Engine performance analysis under static uneven tip clearance

作　　者：曹惠玲[1] 汪晗 CAO Huiling;WANG Han(College of Aeronautical Engineering,CAUC,Tianjin 300300,China)

机构地区：[1]中国民航大学航空工程学院,天津300300

出　　处：《中国民航大学学报》2020年第4期17-20,36,共5页Journal of Civil Aviation University of China

基　　金：中央高校基本科研业务费专项(3122014D010)。

摘　　要：孔探图像显示高压涡轮叶片前缘与罩环之间摩擦严重,对发动机性能影响较大,研究发现热态下HPT部件前后缘会产生不均匀膨胀变形。调整CFM56型航空发动机静态下HPT前缘磨削角度,使叶顶部位前后缘产生不均匀间隙并进行试车实验。利用三维湍流数值方法模拟高压涡轮流场,计算发动机工作状态下的高压涡轮效率以及整机热效率,结合维修与试车实验数据,分析发动机关键性能参数,研究静态不均匀叶尖间隙对涡轮效率以及发动机性能的影响。结果表明:采用不均匀叶尖间隙维修方案可减少罩环磨损并有效提高高压涡轮部件及整机性能。Turbine tip clearance has great influence on engine performance.Borescope inspect image shows that the friction between the leading edges of HPT blade and shroud is severe,and the engine performance keeps low.It is found that the leading and trailing edges of HPT produce uneven expansion deformation under hot state.HPT leading edge grinding angle is adjusted in CFM56 aero-engine under static condition to produce uneven clearance between leading and trailing edges of blade tip position and to carry out the test.3D turbulence numerical simulation is used to simulate the flow field of HPT and calculate its efficiency as well as thermal efficiency of the whole engine under working state.The key performance parameters are analyzed and the influence of static uneven tip clearance on turbine efficiency and engine performance is studied in combination with maintenance and test data.Result shows that the uneven tip clearance maintenance scheme can reduce the friction of shroud and effectively improve the performance of high-pressure turbine components and the engine.

关 键 词：不均匀叶尖间隙 高压涡轮 发动机性能 数值模拟 

分 类 号：V263.6[航空宇航科学与技术—航空宇航制造工程]