航空发动机高涡叶尖外撑测量工艺设计与分析
Design and Analysis of External Support Measurement Process for HPTR Blade Tips of Aero-engine

为解决航空发动机高压涡轮转子叶尖外径测量时存在装配间隙、外表易磕碰、难以固定等问题，提出一种将相邻左右叶片的叶尖作为支反力作用点，对待测叶片进行径向外撑消隙的新型工艺方案。设计高涡叶片外撑测量装置，在高压涡轮不拆分后挡板的状态下，对转子叶片进行径向外撑和固定。进行高涡叶尖外径测量试验，对测量系统进行精确度分析，测量精度可达到0.04 mm，满足现有测量要求，为今后研制航空发动机高精密高涡叶尖外径测量仪器奠定重要基础。
To solve the tip diameter measurement of existing assembly clearance, easy clashing appearance, difficulty in fixation of aero-engine high pressure turbine rotor (HPTR) blades, a new process method is proposed by taking the adjacent left and right blade tips as the support reaction force points which externally support the measuring blade to eliminate the radial clearance. External support measurement device for HPTR blades is designed, and on the condition of high pressure turbine without dividing the rear baffle, the rotor blades are externally supported and fixed. The tip diameter measurement experiment for HPTR Blades is carried out and the measurement system accuracy is analyzed, whose the accuracy is 0.04 mm to meet the present measurement reqirement, which will lay an important foundation for developing the high precision tip diameter measuement instruments for aero-engine HPTR blades