加减速控制对航空发动机性能影响的仿真分析

李俊，周玉昭，李瑞军

中国航发沈阳发动机研究所，辽宁 沈阳  110015

摘要：分析某涡轮航空发动机过渡态加减速过程的控制方式，采用AEAYS-606软件搭建过渡态仿真模型，通过调节压气机换算转速实现加减速供油控制算法，结合功率提取法实现过渡态工况仿真，分析不同加减速控制策略对发动机性能的影响。结果表明：加减速供油设计旨在实现加减速时间最短，且需避免加减速过程中各参数超出或逼近各部件稳定边界目标；对比不同的加速控制，加速过程中为了加速时间缩短2 s，最高涡前温度需提高1.4%，压气机稳定裕度减小约4%，发动机寿命和稳定性急剧下降，应根据发动机实际应用需求选择适宜的加速控制策略；不同的减速控制策略下，压气机裕度均明显提高，但减速时间少于3 s时，减速过程中主燃烧室最小油气比低于主燃烧室熄火油气比边界，主燃烧室存在熄火风险。

关键词：航空发动机；加减速控制；仿真分析；过渡态工况；压气机

Simulation analysis of the influence of acceleration and deceleration control on the performance of an aero-engine

LI Jun, ZHOU Yuzhao, LI Ruijun

AECC Shenyang Engine Research Institute，Shenyang 110015，China

Abstract: The mode of the acceleration and deceleration process in the transient state of a certain turbojet aero-engine is analyzed. The transient simulation model is established by using AEAYS-606 software. The acceleration and deceleration fuel control algorithm is realized by adjusting the compressor converted speed. The transient working condition simulation is realized by combining the power extraction method. The influence of different acceleration and deceleration control on the performance of the engine is analyzed. The results show that the design of acceleration and deceleration fuel is aimed at the shortest acceleration and deceleration time, and it is necessary to avoid the acceleration and deceleration process. Each parameter should not exceed or approach the stable boundary of each component for the objective. Comparing different controls, it is found that in order to shorten the acceleration time by 2 s, the maximum vortex temperature needs to be increased by 1.4%, the compressor stability is reduced by 4%, and the engine life and stability are drastically reduced. The appropriate acceleration control law should be selected according to the actual application needs of the engine. Comparing different deceleration controls, it is found that the compressor margin is significantly increased, but when the deceleration time is less than 3 s, the minimum air-fuel ratio the main combustion chamber during deceleration is less than the main combustion chamber extinction air-fuel ratio boundary. There is a risk of misfire in the main combustion chamber.

Keywords: aero-engine; acceleration and deceleration control; simulation analysis; transient working condition; compressor