摘要
为防止加力接通过程中因喷口过小导致发动机喘振,某型发动机借鉴国外经验设置了喷口前馈线。分析了喷口前馈线的控制原理及设计特点,并结合实际试飞数据对同一加力接通逻辑下不同喷口前馈线对加力接通结果的影响进行了对比研究。结果表明:当控制系统正常工作时,喷口前馈线不参与喷口的实际控制过程,且不会对加力接通结果产生较大影响;但当喷口给定故障时,喷口前馈线可保证发动机安全工作。
To avoid engine surge in the course of reheat lit due to small nozzle, control laws of feedback ex-haust nozzle area of foreign engines was adopted for reference. The theory and the characteristic of controllaws of feedback exhaust nozzle area were analyzed, and the impact of control laws of feedback exhaust noz-zle area to the reheat lit tests results under the same control logic of reheat lit was contrasted and investigat-ed based on the real flight tests data. The results indicate that when the control system works normally, thecontrol laws of feedback exhaust nozzle area don’t participate in the actual control of nozzle and will notmake a strong impact on the reheat lit tests results; however, it ensures that the engine work safely when thegiven nozzle area was set inaccurately.
出处
《燃气涡轮试验与研究》
北大核心
2017年第3期6-10,共5页
Gas Turbine Experiment and Research
关键词
航空发动机
喷口面积
反馈
控制规律
加力接通
落压比
飞行试验
aero-engine
exhaust nozzle area
feedback
control laws
reheat lit
pressure drop ratio
flight test
