民用大涵道比发动机叶尖间隙控制结构设计分析  

Structure design for the clearance control of blade tip of a high bypass ratio aeroengine

作　　者：张清[1] 郝勇[1] 霍枫[1] 牛坤[1] 

机构地区：[1]中航工业沈阳发动机设计研究所航机总体设计二部,沈阳110015

出　　处：《沈阳航空航天大学学报》2014年第2期14-19,共6页Journal of Shenyang Aerospace University

摘　　要：首先从转子变形、静子变形和其他因素三方面对叶尖间隙的影响因素进行了详细分析,给出叶尖间隙设计过程中需要重点考虑的载荷因素,并结合部件特点分别给出压气机和涡轮叶尖间隙的设计方法;其次,对叶尖间隙控制机理进行分析,提出主动间隙控制、被动间隙控制和重建密封的间隙控制方法;最后从控制转、静子变形、保持间隙均匀和改善转、静子变形协调性四个方面出发,以大涵道比发动机整机结构为例,进行间隙控制结构的详细设计分析,总结了适合大涵道比发动机的叶尖间隙控制结构设计方法。Firstly,the influential factors to blade tip clearance were analyzed thoroughly from three aspects, namely rotor deformation,stator deformation and other factors. The factors of loads to be noticed in the de-sign for blade tip clearance were presented. And the designs of air-compressor and turbine blade tip clearance were introduced respectively for the parts with different features. Secondly,the principles of blade tip clear-ance control were analyzed,and three methods-active clearance control,passive clearance control,reconstruc-tion of hermetic clearance control- were proposed. Finally,taking the high bypass ratio engine as an exam-ple,the analysis of detailed design for clearance control was put forward from four aspects-controlling the deformation of rotor and stator,keeping the even clearance,improving the coordination of rotor deformation and stator deformation,and the proper methods of structure design for the clearance control of blade tip of a high bypass ratio engine were summarized.

关 键 词：大涵道比 航空发动机 间隙控制 结构设计 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]