航空发动机超声速巡航性能寻优控制研究

推进技术 ›› 2015, Vol. 36 ›› Issue (8): 1248-1256.

航空发动机超声速巡航性能寻优控制研究

孙丰勇,张海波,叶志锋,郑前钢

南京航空航天大学能源与动力学院/江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院/江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院/江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院/江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:孙丰勇(1990—)，男，博士生，研究领域为航空发动机建模及控制。E-mail:fengyongsun@126.com 通讯作者:张海波(1976—)，男，博士，教授，研究领域为航空发动机控制。
基金资助:
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)。

A Study of Aero-Engine Supersonic Cruise

College of Energy and Power Engineering/Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering/Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China,College of Energy and Power Engineering/Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China and College of Energy and Power Engineering/Jiangsu Province Key Laboratory of Aerospace Power System，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

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。

关键词: 超声速巡航；性能寻优控制；进气道放气；自适应模型

Abstract: 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.

Key words: Supersonic cruise；Performance seeking control；Inlet bleeding；Adaptive model

孙丰勇,张海波,叶志锋,郑前钢. 航空发动机超声速巡航性能寻优控制研究[J]. 推进技术, 2015, 36(8): 1248-1256.

SUN Feng-yong,ZHANG Hai-bo,YE Zhi-feng,ZHENG Qian-gang. A Study of Aero-Engine Supersonic Cruise[J]. Journal of Propulsion Technology, 2015, 36(8): 1248-1256.

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