航空发动机

刘作宏1，2 ，李季1，3 ，高为民 1 ，何志强 1 ，王德轩 1 ，张帅1.推力矢量发动机喷管气动稳定性故障分析[J].航空发动机,2025,51(6):77-83

推力矢量发动机喷管气动稳定性故障分析

Analysis of an Aerodynamic Stability Fault in a Thrust Vectoring Engine Nozzle

DOI：

英文关键词:nozzle oscillation thrust vectoring aerodynamic stability sudden load change nozzle area ratio aeroengine

基金项目:国家级研究项目资助

作者	单位
刘作宏1，2 ，李季1，3 ，高为民 1 ，何志强 1 ，王德轩 1 ，张帅1	1.中国航发沈阳发动机研究所，沈阳110015；2.中国航空研究院能源与动力工程学院，江苏扬州225000； 3.西北工业大学卓越工程师学院，西安710072

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中文摘要:

针对推力矢量发动机喷管使用过程中出现抖动的气动稳定性故障，分析控制器数据和台架采集数据，结合喷管控制和工作原理，认为故障原因是在作动筒调整后喷管面积解算规律不一致使喷管出口面积A 9 小于喉道面积A 8 所致。对喷管工作过程开展仿真计算，结果表明：故障发生时，喷管A 9 先于A 8 抖动，A 8 喉道后移，实际面积比Ar减小。抖动过程中喷管面积比Ar恰处于亚声速向超声速流动转变的区间内。相同进口压力下，当面积比Ar由0.964至0.969，扩张段载荷由压力转变为吸力，喷管抖动过程中，Ar恰处于压力转变成吸力区间，实际工作面积比和进口压力导致气流流动发生转变，扩张段载荷换向导致扩张调节片抖动。

英文摘要:

To address the aerodynamic stability fault manifesting as nozzle oscillation during the operation of a thrust vectoring engine nozzle, controller data and facility data were analyzed. Based on the nozzle control and working principles, the fault was attributed to the inconsistency in the nozzle area calculation law after the actuator cylinder adjustment, leading to the nozzle exit area (A 9 ) being smaller than the throat area (A 8 ). Simulation of the nozzle operation process revealed that during the fault, the nozzle A 9 oscillates before A 8 , the A 8 throat moves backward, and the actual area ratio (A r ) decreases. During the oscillation, the nozzle area ratio Ar is exactly in the interval where the flow regime shifts from subsonic to supersonic. Under constant inlet pressure, as the area ratio Ar increases from 0.964 to 0.969, the load on the divergent section changes from pressure force to suction force. During the oscillation, the area ratio Ar is exactly in the interval of load reversal, the actual working area ratio and inlet pressure cause the flow regime transition, and the load reversal of the divergent section leads to the oscillation of the divergent control flap.

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