发动机喷口面积对加力接通影响的试飞研究

为了研究涡扇发动机喷口面积调节对高空加力接通的影响，开展了飞行试验研究。试飞中出现在加力起动阶段点火成功后，喷口面积放大不足导致风扇后压力急剧增高，发动机主动退出加力，在加力点火成功后增加加力燃油流量时，喷口面积过度放大使得加力燃烧室压力较低而熄火。通过调整喷口控制参数，提高加力点火阶段尾喷口面积放大程度，提高了加力接通性能；通过降低在供油量增加时刻的尾喷口面积放大程度，加力燃烧室能够持续稳定燃烧。试验结果表明：对尾喷口面积控制规律的调节显著提高了发动机的加力接通能力，对于其它涡扇发动机的加力接通设计与改进具有一定的借鉴意义。

Flight Test Study on The Effect of Nozzle Area on Afterburner Connection of Aeroengine

In order to study the influence of nozzle area adjustment of afterburner connection of turbofan engine at high-altitude, the flight test was carried out. During the flight test, after the successful ignition at the starting stage of afterburner, the insufficient expansion of nozzle area led to a sharp increase in the pressure behind the fan, and the engine cut-off the afterburner actively. When the fuel flow of afterburner was increased after the successful afterburner ignition, the excessive expansion of nozzle area led the afterburner flameout due to lower pressure. By adjusting the control parameters of the nozzle, increasing the expansion extent of the nozzle area during the ignition, the performance of the afterburner connection was improved, and reducing the expansion extent of the nozzle area at the time when oil supply increase, the afterburner was capable of sustained and steady combustion. The test results show that the adjustment of the nozzle area control law can significantly improve the ability of reheat lit, which can be used for reference for the design and improvement of other turbofan engines.