涡扇发动机高空小表速加力接通试验研究

Experimental Study on Afterburner Light-on Process with Small Airspeed at High Altitude for a Turbofan Engine

以涡扇发动机加力接通过程为研究对象,开展了高空小表速区域加力接通试验。通过分析发动机试验数据,得出加力未接通的主要原因:在点火区混合油气压力(通过涡轮后压力表征)较低的条件下,点火区混合油气不能可靠点燃。基于以上原因,采取了延迟发出加力点火指令的改进措施,在较高的涡轮后压力下实现加力点火。试验结果表明,改进措施可以提高高空小表速区域加力接通的成功率,该结果对其他涡扇发动机的加力接通设计具有一定的借鉴意义。

A turbofan engine is chosen for the test of the afierbumer light-on process with small airspeed at high altitude in this study. The main reason leading to the failure of afterbuming process and corresponding solutions are investigated. By analyzing the test data, it is found that the fuel-air mixture cannot be ignited reliably in the afterburner ignition zone under the low pressure condition （represented by the pressure after turbine）. For this reason, delaying the igniting command and igniting under higher pressure are implemented. The results show dramatic improvement and are believed to be helpful for other turbofan engine design procedure.