基于高速慢车的航空发动机快速响应控制

推进技术 ›› 2014, Vol. 35 ›› Issue (9): 1271-1277.

基于高速慢车的航空发动机快速响应控制

陈小磊,郭迎清,杜　宪

西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072;西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:陈小磊(1986—)，男，博士生，研究领域为航空发动机寿命延长控制和应急控制。
基金资助:
航空基金(2011ZB53)。

Fast Response Control of Aircraft Engine Through

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China;School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 针对传统航空发动机响应速度慢，难以在紧急事件中用于控制受损飞机完成起降过程的问题，采用高速慢车控制模式来提升发动机加速性能，通过增加发动机在慢车时高压压气机转速，为加速前期提供更大的燃油流量，从而缩短发动机从慢车至最大状态的加速时间。为保证慢车时高压转子转速提高的同时发动机推力和稳定裕度不变，通过修改高压压气机可调导叶控制计划来调整高压转子工作点。仿真结果显示，与原有控制相比，采用高速慢车快速响应控制模式的发动机加速上升时间从原来的2.00s缩短至1.86s，而高压压气机最小喘振裕度仅由16.01%下降至14.81%，同时慢车推力基本保持不变。

关键词: 涡扇发动机；快速响应控制；高速慢车；VSV调节计划；加速计划

Abstract: The traditional aero-engine response is sluggish and difficult to be used to land a damaged aircraft in some emergency situations. To solve this problem，High Speed Idle (HSI) is introduced to enhance the acceleration performance. By increasing high pressure rotor speed，it can provide greater fuel flow for acceleration process to shorten rise time between the idle to largest state. And in order to ensure the engine thrust and stability margin unchanged while increasing high pressure rotor speed，the Variable Stator Vanes (VSV) control schedule is modified to change the operating point of high pressure rotor. Simulation results show that the rise time reduced to be 1.86s from 2.00s，and at the same time the stability margin of core compressor only decreases to be 14.81% from 16.01%，while the thrust of engine in idle state unchanged.

Key words: Turbofan engines；Fast response control；High speed idle；VSV control schedule；Accelerate schedule

陈小磊,郭迎清,杜　宪. 基于高速慢车的航空发动机快速响应控制[J]. 推进技术, 2014, 35(9): 1271-1277.

CHEN Xiao-lei,GUO Ying-qing,DU Xian. Fast Response Control of Aircraft Engine Through[J]. Journal of Propulsion Technology, 2014, 35(9): 1271-1277.

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