民用涡扇发动机起动过程改进的分段组合控制计划研究与试验

孔祥兴; 王曦; 张绍基; 尹长志; 王祥宇

doi:10.13224/j.cnki.jasp.2014.12.019

民用涡扇发动机起动过程改进的分段组合控制计划研究与试验

doi: 10.13224/j.cnki.jasp.2014.12.019

1. 中国航空工业集团公司中航空天发动机研究院有限公司, 北京 100028;
2. 北京航空航天大学能源与动力工程学院, 北京 100191;
3. 中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015

详细信息

作者简介:
孔祥兴(1982-), 男, 河北保定人, 工程师, 博士, 主要从事航空发动机建模、控制律设计与故障诊断方面的研究.

中图分类号: V233.7
计量
- 文章访问数: 1404
- HTML浏览量: 3
- PDF量: 1001
- 被引次数: 0
出版历程
- 收稿日期: 2013-07-29
- 刊出日期: 2014-12-28

Research and experiment on improved sectional combination control scheme for civil turbofan engine's startup process

1. Academy of Aeronautic Propulsion Technology, Aviation Industry Corporation of China, Beijing 100028, China;
2. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
3. Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 针对某型民用涡扇发动机,将n-dot闭环控制算法应用于涡扇发动机起动过程,设计了涡扇发动机起动过程开环与闭环分段组合的控制计划,仿真表明:涡扇发动机起动过程采用n-dot闭环控制算法在初始阶段会出现参数摆动的情况.为此,基于油气比作控制变量进行消喘的原理,对n-dot闭环控制算法进行了改进,以消除起动初始阶段的参数摆动.试验结果表明:改进后的分段组合的控制计划能够有效抑制参数摆动现象;并且,对于不同大气条件的起动测试,起动过渡态过程高压转子转速的数值差距不大于1.0%,延时不超过0.9s;而对于不同飞行状态的起动测试,起动过渡态过程高压转子转速的数值差距不大于1.0%,延时不超过1.2s,具有良好的稳定性和重复性.
- n-dot闭环控制 /
- 闭环控制 /
- 自适应控制 /
- 起动控制规律 /
- 涡扇发动机
Abstract: A n-dot closed loop control algorithm was applied to the startup process for a civil turbofan engine. Therefore, an openned/closed loop sectional combination control scheme for turbofan engine's starup process was designed. The simulation result shows that the n-dot closed loop control algorithm could cause oscillation at the beginning of startup process of turbofan engine. To eliminate the parameters' oscillation at the beginning of startup process, the n-dot closed loop control algorithm was improved according to the rationale of surge recovery by using fuel air ratio unit as the control variable. The experiment results illustrate that the improved sectional combination control scheme could effectively restraine the parameters' oscillation, and furthermore the startup transition process had satisfying stability and repetitive. The numerical difference of high pressure rotor speed under different atmosphere conditions does not exceed 1.0% and the time delay does not exceed 0.9s; meanwhile the numerical difference of high pressure rotor speed under different flight conditions does not exceed 1.0% and the time delay does not exceed 1.2s.
- n-dot closed loop control /
- closed loop control /
- adaptive control /
- startup control law /
- turbofan engine

HTML

参考文献(18)

[1]	张绍基.涡扇发动机空中起动特性分析[J].航空发动机,2003,30(4):1-4. ZHANG Shaoji.Analysis of windmilling start characteristics for a typical turbofan engine[J].Aeroengine,2003,30(4):1-4.(in Chinese)
[2]	王兆铭,王福德,左伟,等.某型航空发动机空中起动供油规律的研究[J].航空动力学报,2010,25(5):1163-1168. WANG Zhaoming,WANG Defu,ZUO Wei,et al.Research on fuel supply control law of airstart for an aero-engine[J].Journal of Aerospace Power,2010,25(5):1163-1168.(in Chinese)
[3]	乔洪信,夏爱国,杨立.某型航空发动机高原使用起动供油量调整研究[J].航空动力学报,2003,18(4):534-537. QIAO Hongxin.XIA Aiguo,YANG Li.Study of adjusting aeroengine starting fuel supply in the plateau area[J].Journal of Aerospace Power,2003,18(4):534-537.(in Chinese)
[4]	陈玉春,王朝蓬,黄兴鲁,等.功率提取法在涡喷发动机起动特性模拟及控制规律设计中的应用[J].航空动力学报,2010,25(6):1277-1283. CHEN Yuchun,WANG Zhaopeng,HUANG Xinglu,et al.Application of power extraction method in starting process simulation and control law design of turbojet engines[J].Journal of Aerospace Power,2010,25(6):1277-1283.(in Chinese)
[5]	屠秋野,唐狄毅.涡扇发动机起动模型及起动控制规律的研究[J].推进技术,1999,20(2):21-24. TU Qiuye,TANG Diyi.Study on startup model and startup control law of turbofan engine[J].Journal of Propulsion Technology,1999,20(2):21-24.(in Chinese)
[6]	朴英.航空燃气涡轮发动机起动性能分析[J].航空动力学报,2003,18(6):777-782. PIAO Ying.An analysis of the starting characteristics of aeroengine[J].Journal of Aerospace Power,2003,18(6):777-782.(in Chinese)
[7]	Howlett J J,Morrison T,Zagaranski R D.Adaptive fuel control for helicopter applications[J].Journal of the American Helicopter Society,1984,29(4):43-54.
[8]	Achgill D M,Zagaranski R D.Adaptive fuel control testing[C]//American Helicopter Society 41st Annual Forum Proceedings.Fort Worth,US:American Helicopter Society,1985:197-211.
[9]	李胜泉,杨征山,张基钢,等.转速速率闭环的涡轴发动机起动过程自适应控制[J].南京航空航天大学学报,2007,39(3):302-306. LI Shengquan,YANG Zhengshan,ZHANG Jigang,et al.Adaptive startup control based on rotate speed rate for turbo-shaft engine[J].Journal of Nanjing University of Aeronautics and Astronautics,2007,39(3):302-306.(in Chinese)
[10]	赵连春,马丁利.飞机发动机控制:设计、系统分析和健康监视[M].张新国,译.北京:航空工业出版社,2011:104-114.
[11]	Ait Rami M,El Faiz S,Benzaouia A,et al.Robust exact pole placement via an LMI-based algorithm[J].IEEE Transactions on Automatic Control,2009,54(2):394-398.
[12]	Crusius C A R,Trofino A.Sufficient LMI conditions for output feedback control problems[J].IEEE Transactions on Automatic Control,1999,44(5):1053-1057.
[13]	Wang X,Sun Y,Zheng T,et al.Static output feedback-based PI control for aeroengines using linear matrix inequality[R].AIAA-2008-4581,2008.
[14]	Tarbouriech S,Turner M.Anti-windup design:an overview of some recent advances and open problems[J].Control Theory and Applications,2009,3(1):1-19.
[15]	KONG Xiangxing,WANG Xi,TAN Daoliang,et al.A non-iterative aeroengine model based on volume effect[R].AIAA-2011-6623,2011.
[16]	周文祥,黄金泉,窦建平.涡扇发动机部件级起动模型[J].航空动力学报,2006,21(2):248-253. ZHOU Wenxiang,HUANG Jinquan,DOU Jianping.Development of component-level startup model for a turbofan engine[J].Journal of Aerospace Power,2006,21(2):248-253.(in Chinese)
[17]	Mink G,Behbahani A.The AFRL ICF generic gas turbine engine model[R].AIAA-2005-4538,2005.
[18]	Dalton J S,Behbahani A.An integrated approach to conversion,verification,validation and integrity of AFRL genetic engine model and simulation[R].California:42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit,2006.