基于光纤复合测量技术的涡轮叶片气膜孔检测

为了解决航空发动机涡轮叶片气膜孔几何特征参数有效检测手段缺乏、测量结果一致性差的问题，设计并搭建了基于 光纤复合测量技术的涡轮叶片气膜孔检测系统，提出了利用该系统对涡轮叶片气膜孔进行测量的方法，通过试验进行了方法验 证。搭建的系统为多传感器测量系统，具备叶片接触与非接触测量、空间姿态定位及3D投影能力，实现了涡轮叶片全范围气模孔 的测量。在试验中，选取高压涡轮叶片作为被测物体，应用该测量系统对叶片上的气膜孔进行了测量，计算得到了气膜孔直径、轴 线角度及位置度的准确信息。结果表明：通过测量不确定度的分析评定可知，该系统对气膜孔直径、位置度的测量不确定度均小 于0.01 mm，完全满足设计公差对测量仪器的精度要求，可以用于涡轮叶片气膜孔工程化测量。

Inspection of Turbine Blade Film Cooling Holes Based on Fiber Optic Multi-sensor Measurement Technique

In order to solve the problems of lacking effective inspection means and poor consistency of measurement results for aeroengine turbine blade film cooling hole geometrical feature parameters, an inspection system for turbine blade film cooling holes was designed and established based on fiber optic-based multi-sensor measurement technique. The measurement method of the film cooling holes using the system was proposed, and verified by measurement practices. The system is a multi-sensor measurement system with the ability of contact and non-contact measurement, spatial attitude positioning, and 3D projection, realizing measurement of film cooling holes over the entire turbine blade. A high-pressure turbine blade was selected for conducting the film cooling hole measurement by using the measurement system. Accurate geometrical feature parameters of the film cooling holes were calculated, including their diameters, axis angles, and position. The results show that through measurement uncertainty analysis and evaluation, uncertainties of the diameters and the positions are both less than 0.01mm, which fully meets the accuracy requirements of the measuring instrument derived from the design tolerances, and the system can be used for the inspection of the film cooling hole of the turbine blade.