航空涡扇发动机加力供油系统排故测试技术

采用传统测试技术对航空涡扇发动机可测量参数较少，导致排故测试精准度较低，针对该问题，提出了航空涡扇发动机加力供油系统排故测试技术。依据航空涡扇发动机加力供油系统结构，分析加力供油系统工作原理。通过分析加力外涵计量活门位置的异常波动情况，确定加力外涵供油流量不足原因。列出故障树，根据故障原因分析结果，确认线性可变差动变压器摩擦力异常。研究线性可变差动变压器结构，使用F150型号的内窥镜观察变压器底部存在的金属堆积物，完成加力供油系统计量活门摆动排故测试。根据加力启动供油装置，分析具体故障原因，并计算启动过程中损失的压力大小，获取航空涡扇发动机工作喷嘴燃油流量。对比分析模拟关闭电磁活门时的油泵出口压力和实际压力，排除加力供油系统启动点火故障。由实验结果可知，该技术测试精准度较高，最高可达到0.9815，为系统稳定工作裕度提供支持。

Trouble-shooting test technology for aviation turbofan engine afterburner system

The traditional turbo-fan engine has fewer measurable parameters using traditional testing techniques, which leads to a lower accuracy of the troubleshooting test. In response to this problem, a turbo-fan engine fueling system troubleshooting test technology is proposed. Based on the structure of the afterburner fuel supply system of the aviation turbofan engine, the working principle of the afterburner fuel supply system is analyzed. By analyzing the abnormal fluctuation of the position of the measuring valve of the afterburner culvert, the cause of insufficient fuel flow of the afterburner culvert is determined. List the fault tree and confirm the abnormality of the frictional force of the linear variable differential transformer according to the analysis result of the fault cause. Investigate the structure of linear variable differential transformer, use F150 type endoscope to observe the metal deposits on the bottom of the transformer, and complete the swing valve troubleshooting test of the afterburner fueling system. Start the fuel supply device according to the afterburner, analyze the specific failure cause, and calculate the pressure loss during the startup process to obtain the fuel flow of the working nozzle of the aviation turbofan engine. Contrast analysis and simulation of the pump outlet pressure and actual pressure when the electromagnetic valve is closed, excluding the ignition failure of the afterburner fuel supply system. It can be known from the experimental results that the test accuracy of this technology is relatively high, which can reach a maximum of 0.9815, providing support for the system''s stable working margin.