机动飞行下的涡轮叶尖间隙动态变化规律  

Dynamic changes rule of aero-engine turbine tip clearance in maneuver flight

作　　者：贾丙辉[1] 张小栋[1] 彭凯[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2011年第12期2757-2764,共8页Journal of Aerospace Power

基　　金：深圳市传感器技术重点实验室开放基金(SST201008)

摘　　要：在对涡轮叶尖间隙的变化机理进行初步分析的基础上,建立机匣、叶片和转子的简化模型,并重点研究了转子在飞行器机动飞行情况下的振动幅值对叶尖间隙的影响.结果表明:高压涡轮叶尖间隙动态变化范围约为0.44mm到1.45mm,同时飞行器均加速导致的转子振动会引起间隙局部增大或减小,俯仰机动和水平盘旋机动飞行都会使得间隙动态变化的非线性明显增强.Based on the preliminary analysis of the change mechanism of the turbine blade tip clearance,the simplified model of blade,rotor and casing was established,and the effect of rotor vibration amplitude of aero craft in-flight maneuver state was researched.The results show：reduction of clearance is approximately 0.44 to 1.45 mm;local tip clearance would increase or decvease caused by uniformity acceleration of aero craft;pitching maneuver and horizontal circling would bring vibration of tip clearance,which makes the nonlinear of clearance variation markedly enhanced.

关 键 词：涡轮叶尖间隙 航空发动机 机动飞行 转子振动 动态模型 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]