摘要
为解决航空发动机在不加力超声速巡航状态的性能寻优问题,提出进气道放气、风扇与压气机导叶角与燃油流量、尾喷管喉道面积五变量的序列二次规划优化调节方案,验证了航空发动机在最大安装推力、最小油耗、最低涡轮前温度三种控制模式时,相比较于传统的不带进气道放气的四变量优化方案,五变量优化方案优势明显,可分别提升最大安装推力7.5%,降低燃油消耗率4.6%,降低低压涡轮前温度1.5%;同时,为满足机载发动机模型自适应要求,建立基于输入端带积分补偿的卡尔曼滤波器的发动机自适应模型,并验证了航空发动机在发生蜕化时,五变量优化方案同样具有全局寻优优势。
In order to solve the problem of performance seeking control in the aero-engine supersonic cruise without afterburner,a new optimization program by sequential quadratic programming（SQP） with five variables is proposed,which is by means of adding a new variable called inlet-bleeding coefficient to the conventional optimizing variables made up of guided vanes of fan and compressor,fuel flow,nozzle throat area. Better effectiveness is certificated by the simulation results via the new optimization program than the conventional SQP with four variables in the modes of the maximum thrust mode,the minimum fuel-consumption mode and the minimum turbine temperature mode. The installed thrust is enhanced by 7.5% in the maximum thrust mode,4.6%drop of fuel-consumption in the minimum fuel-consumption mode,1.5% drop of turbine blade temperature in the minimum turbine temperature mode. Meanwhile,a new type of engine adaptive model is developed to meet the adaptive requirements of onboard model which is improved by adding the output error feedback to the Kalman filter. The new optimization program with five variables also shows an obvious advantage in global optimization while performance degradation happens.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2015年第8期1248-1256,共9页
Journal of Propulsion Technology
基金
江苏省普通高校研究生科研创新计划项目(KYLX15_0257)
航空科学基金(20120652)
