大涵道比涡扇发动机低压涡轮间隙分析与设计  

Analysis and Design of Low Pressure Turbine Tip Clearance for High Bypass Ratio Turbofan Engine

作　　者：张清[1] 郝勇[1] 张大义[2] 刘宝龙[2] 洪杰[2] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空发动机》2014年第2期56-60,共5页Aeroengine

基　　金：国家自然科学基金(51106004)资助

摘　　要：航空发动机涡轮叶尖间隙的准确分析与合理设计对改善发动机性能有重要意义。对叶尖间隙的影响因素进行了详细分析,并指出在总体结构初步设计中,涡轮叶尖间隙分析和设计需要重点考虑的载荷因素;给出采用NX-NASTRAN进行间隙计算的求解方法和详细步骤;以某大涵道比发动机低压涡轮的间隙分析为例,给出详细的求解过程,求解得到低压涡轮在地面起飞状态等8个工况下间隙变化值为-0.4～1.1 mm,并指出间隙初始值的确定应当主要考虑设计点状态、起飞状态和地面慢车状态。The accurate calculation and proper design on turbine tip clearance are very important to improve the engine performance.The influence factors of tip clearance were analyzed in detail,and the key load factors which should be considered during preliminary structure design were emphasized.The computation method and detailed steps for computing tip clearance were given by NX-NASTRAN.Taking tip clearance analysis of high bypass ration turbofan engine as an example,the calculation process was shown particularly,and the tip clearance variation zone at eight operation statuses were obtained from-0.4 mm to 1.1 mm.The key design operation statuses were acquired as standard operation,taking off and ground idle which should be considered during tip clearance design especially.

关 键 词：大涵道比发动机 涡轮 叶尖间隙 有限元 结构设计 NX-NASTRAN 

分 类 号：V214.4[航空宇航科学与技术—航空宇航推进理论与工程]