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基于压力受感器的设计经验,为探索中小型航空发动机叶型稳态压力受感器的设计方向,本文利用开口吹气式亚音速校准风洞,对不同结构形式的叶型稳态压力受感器进行了吹风校准试验。通过测取不同工况下受感器的压力值,计算总压测量系数,分析了带整流套和不带整流套对于受感器不敏感角的影响,为进一步优化中小型航空发动机叶型稳态压力受感器设计提供了指导。
Based on the pressure sensor design experience, in order to explore the design direction of small and medium aero-engine blade-type steady-state pressure sensors, the open-air blowing subsonic subsonic wind tunnel is used to study the influence of different structural forms on the steady- Sensor conducted a hair calibration test. By measuring pressure values of sensors under different working conditions, the total pressure measurement coefficient was calculated. The influence of non-sensor angle with and without rectification sleeve was analyzed. In order to further optimize the airfoil stability State pressure sensor design provides a guide.