摘要 设计了一种用于航空发动机他机领先试飞的引气负载系统,详细介绍了该系统的总体布局、技术要求、工作原理和具体实施方案。整个系统主要由引气控制系统、引气流量测量控制系统、引气流量调节装置及限流文氏管等组成,通过测量控制系统,控制压力调节/关断阀和引气流量调节阀,测量、显示和记录流量测量装置获取的参数。地面试验和飞行试验表明,该系统工作时发动机状态稳定,且能满足发动机不同功率下的流量需求。 An air intake load system for leading flight test of other aero-engine was designed.The overall layout,technical requirements,working principle and specific implementation scheme of the system were in⁃troduced.The whole system was mainly composed of air intake control,air intake flow measurement control system,air intake flow regulating device and current limiting Venturi tube.The pressure regulating/closing valve and the air intake flow regulating valve are controlled through the measurement control system,and measure,display and record the parameters obtained by the flow measuring device.The ground test and flight test show that the system works stably and can meet the flow demand of the engine at different power levels.
机构地区 海军装备部
出处 《燃气涡轮试验与研究》 北大核心 2021年第1期58-62,共5页 Gas Turbine Experiment and Research
关键词 航空发动机 引气负载系统 飞行试验 流量测量 飞行台 控制系统 aero-engine air intake load system flight test flow measurement flying test bed control system
