航空涡扇发动机偏流板前扩稳控制技术  

Steady Enhancement Control Technology of Aircraft Turbofan Engine for Surface Takeoff

作　　者：刘亚君 彭云龙 邢洋 杨怀丰 郭海红 LIU Yajun;PENG Yunlong;XING Yang;YANG Huaifeng;GUO Haihong(Shenyang Aeroengine Research Institute,Aero Engine Corporation of China,Shenyang Liaoning 110015,China;The 92728th of PLA,Shanghai 200436,China)

机构地区：[1]中国航发沈阳发动机研究所,辽宁沈阳110015 [2]92728部队,上海200436

出　　处：《海军航空大学学报》2024年第4期501-506,514,共7页Journal of Naval Aviation University

摘　　要：为提升航空涡扇发动机舰面偏流板前起飞时的气动稳定性,提出利用压气机进口温度和总增压比2种方法识别发动机进口温升,进而调节压气机可调叶片角度,以提高舰面起飞时发动机稳定裕度。此外,为改善偏流板前进气畸变环境,提出在主机状态不变前提下直接减小加力供油量,以降低发动机出口排气温度,实现发动机舰面起飞前主动扩稳,仿真结果表明,提出的措施有效可行,可为舰载战斗机发动机舰面起飞扩稳控制提供参考。In order to improve the aerodynamic stability of aircraft turbofan engines for surface takeoff,two methods are proposed to identify engine inlet temperature rise using compressor inlet temperature and total supercharging ratio,and then the adjustable blade angle of the compressor is adjusted to improve the engine stability margin during takeoff.In addition,to improve the intake distortion circumstances,a method is introduced that reducing the afterburner oil gas ratio directly while the main engine state remains unchanged to reduce the exhaust temperature of the engine outlet.The simulation results show that the measure are effective and feasible.The above methods and measures can provide reference for carrier-based fighter engine stability control.

关 键 词：偏流板 发动机稳定性 压气机可调叶片角度 温度畸变 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]