变循环发动机地面起动建模及控制规律设计方法

郝旺; 王占学; 张晓博; 周莉; 王靖凯

doi:10.13224/j.cnki.jasp.20210132

变循环发动机地面起动建模及控制规律设计方法

doi: 10.13224/j.cnki.jasp.20210132

1.
西北工业大学动力与能源学院陕西省航空发动机内流动力学重点实验室，西安 710129
2.
中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015

基金项目: 国家自然科学基金（51876176，51906214，52076180）；两机重大专项基础研究项目（J2019-Ⅰ-0021-0020）

详细信息

作者简介:
郝旺（1994-），男，博士生，主要从事航空发动机总体性能仿真与设计。

中图分类号: V231.1
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出版历程
- 收稿日期: 2021-04-02
- 刊出日期: 2022-01-28

Ground starting modeling and control law design method of variable cycle engine

1.
Shaanxi Key Laboratory of Internal Aerodynamics in Aero-Engine， School of Power and Energy，Northwestern Polytechnical University，Xi'an 710129，China
2.
Shenyang Engine Research Institute， Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要: 针对旋转部件等熵效率不连续的问题，提出使用换算扭矩代替等熵效率的方法，给出了旋转部件低转速特性拓展方法并获取了旋转部件的全转速特性。提出了可考虑点火及燃烧稳定性的燃烧室稳定性模型，最终建立了变循环发动机部件级整机起动模型。考虑了变循环发动机的8个可调参数，采用差分进化算法对变循环发动机在双外涵及单外涵模态下的起动过程进行了优化。结果表明：变循环发动机在双外涵及单外涵模态下的起动时间分别为17.2 s与12.8 s；双外涵模态下，需要调节燃油流量、喷管喉部面积与后可变面积涵道引射器外涵面积；单外涵模态下，需要调节燃油流量、喷管喉部面积与低压涡轮进口导叶面积；迎风来流马赫数为0.04时，变循环发动机在双外涵与单外涵模态时的起动时间比静止状态均减少0.2 s。
- 变循环发动机 /
- 部件级起动模型 /
- 部件特性 /
- 控制规律设计 /
- 差分进化算法
Abstract: To solve the problem of discontinuous isentropic efficiency of rotating components，a method of using correct torque instead of isentropic efficiency was proposed.The extrapolation method of low speed characteristics of rotating components was given，and the full speed characteristics of rotating components were obtained.A burner stability model considering ignition and burn stability was proposed.Finally，a component-level starting model of the variable cycle engine was established.Considering the eight variable parameters of the variable cycle engine，the differential evolution algorithm was used to optimize the starting process of the variable cycle engine in the double bypass and single bypass modes.The results showed that the starting time of the variable cycle engine in the double bypass and single bypass modes was 17.2 s and 12.8 s，respectively.In the double bypass mode，the fuel flow，nozzle throat area and outer bypass area of rear variable area bypass injector need to be adjusted.In the single bypass mode，the fuel flow，nozzle throat area and low pressure turbine inlet guide vane area need to be adjusted.When the free stream Mach number was equal to 0.04，the starting time of the variable cycle engine in the double bypass and single bypass modes was 0.2 s less than the static state.
- variable cycle engine /
- component-level starting model /
- component characteristics /
- control law design /
- differential evolution algorithm

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参考文献(33)

[1]	JOHNSON J E.Variable cycle engine developments at general electric 1955-1995[R].AIAA 97-15033,1997.
[2]	HURTLE J E,TOOT P D,WANGER R P.Full authority digital electronic control （FADEC）:variable cycle engine demonstration[R].AIAA 81-1498,1981.
[3]	FRENCH M W,ALLEN G L.NASA VCE test bed engine aerodynamic performance characteristics and test results[R].AIAA 81-1594,1981.
[4]	张晓博,王占学,周红.FLADE变循环发动机模态转换过程特性分析[J].推进技术,2018,39（1）:14-22.
[5]	姜涛,李应红.基于动态RBF网络的发动机起动过程模型辨识[J].航空动力学报,2002,17（3）:381-384.
[6]	李应红,刘建勋.基于支持向量机的涡扇发动机起动性能估算研究[J].航空学报,2005,26（1）:32-35.
[7]	吴利荣,李剑,谢寿生,等.某型发动机高原起动过程数学模型建立[J].航空动力学报,2004,19（1）:58-60.
[8]	伍恒,李本威,张赟,等.基于QPSO-ELM的某型涡轴发动机起动过程模型辨识[J].航空学报,2018,39（11）:1-11.
[9]	苏伟生,孙健国,程蓝,等.基于扭矩特性的航空发动机起动系统数学模型[J].航空动力学报,2005,20（3）:499-502.
[10]	傅强.某型涡轴发动机起动过程建模及仿真[J].计算机仿真,2013,30（12）:57-60.
[11]	王占学,乔渭阳,李文兰.基于部件匹配技术的涡扇发动机起动过程数值模拟[J].航空动力学报,2004,19（4）:444-448.
[12]	黄向华,郑绪生.基于逐级叠加法的航空发动机起动模型研究[J].航空学报,2005,26（5）:540-544.
[13]	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.
[14]	吴虎,冯维林.某型涡扇发动机起动过程数值模拟[J].航空动力学报,2007,22（12）:2068-2072.
[15]	唐宏刚,蔡元虎.某型涡扇发动机起动和加速过程数值模拟[J].推进技术,2007,28（3）:264-268.
[16]	居新星,张海波,陈浩颖.一种通用涡轴发动机起动过程建模方法研究[J].推进技术,2017,38（6）:1386-1394.
[17]	施洋,屠秋野,严红明,等.一种航空发动机全状态性能模型[J].航空动力学报,2017,32（2）:373-381.
[18]	张东方,李应红,陈东林.基于PSO算法的航空发动机起动燃油控制[J].航空动力学报,2007,22（6）:923-927.
[19]	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.
[20]	张天宏,黄向华,曹谦.微型涡轮发动机控制系统仿真及台架试验[J].推进技术,2006,27（5）:445-449.
[21]	徐建国,张天宏.微型涡轮发动机燃油闭环控制起动方法[J].航空动力学报,2012,27（3）:701-706.
[22]	JOACHIM K.How to get component maps for aircraft gas turbine performance calculation[R].ASME Paper 96-GT-164,1996.
[23]	张明阳,王占学,张晓博,等.串联式TBCC发动机风车冲压模态性能模拟[J].航空动力学报,2018,33（12）:2939-2949.
[24]	FERRERVIDAL L E,PACHIDIS V,TUNSTALL R J.An enhanced compressor sub-idle map generation method[R].Zurich,Switzerland:GPPS Forum,GPPS-2018-0004,2018.
[25]	SEXTON W R.A method to control turbofan engine starting by varying compressor surge valve bleed[D].Blacksburg,Virginia，US:The Virginia Polytechnic Institute and State University,2001.
[26]	廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005.
[27]	KURZKE J,HALLIWELL L.Propulsion and power:an exploration of gas turbine performance modeling[M].Cham,Switzerland:Springer International Publishing,2018.
[28]	GAUDET S R,GAUTHIER D.A simple sub-idle component map extrapolation method[R].ASME Paper 2007-GT-27193,2007.
[29]	WALSH P P,FLETCHER P.Gas turbine performance[M].Oxford,UK:Blackwell Science Limited,2004.
[30]	周红,王占学,张晓博,等.变循环发动机模态转换的几何调节规律[J].航空动力学报,2015,30（9）:2160-2166.
[31]	周红.变循环发动机特性分析及其与飞机一体化设计研究[D].西安:西北工业大学,2016.
[32]	STORN R,PRICE K.Differential evolution-a simple and efficient heuristic for global optimization over continuous spaces[J].Journal of Global Optimization,1997,11（4）:341-359.
[33]	HAO Wang,WANG Zhanxue,ZHANG Xiaobo,et al.A new design method for mode transition control law of variable cycle engine[R].AIAA 2018-4821,2018.