考虑多工况性能可靠性的航空发动机循环设计方法

曹大录; 白广忱; 吕晶薇; 肖翼

doi:10.13224/j.cnki.jasp.2019.01.025

考虑多工况性能可靠性的航空发动机循环设计方法

doi: 10.13224/j.cnki.jasp.2019.01.025

1.
北京航空航天大学能源与动力工程学院,北京 100191
2.
中国航天科技集团有限公司中国空间技术研究院北京卫星制造厂，北京 100190
3.
中国航空发动机集团有限公司中国航空发动机研究院,北京 101304

基金项目: 国家自然科学基金（51175017）

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出版历程
- 收稿日期: 2017-12-08
- 刊出日期: 2019-01-28

Aero-engine cycle design approach for multiple operating conditions performance reliability

摘要

摘要: 为实现航空发动机总体性能设计方法由传统的确定性设计向不确定性概率设计转变，提出基于分布式协同响应面法思想的航空发动机多工况性能可靠性循环优化设计方法：建立了引入非确定性部件性能的航空发动机性能仿真模型，通过试验设计、非设计点性能仿真试验等步骤，构建了各典型工况下发动机推力与耗油率性能可靠度关于设计点循环参数的分布式响应面模型，并以此构建多工况性能协同响应面模型进行循环参数优化设计，最终获得循环参数非劣解集并通过随机试验进行验证。结果表明，通过多工况性能可靠性循环优化设计方法获得的循环参数非劣解集均能使发动机在多个典型工况下的总体性能同时达到不低于97.5%的高可靠度，为设计人员根据实际情况选取循环参数提供依据。
- 航空发动机 /
- 总体性能 /
- 可靠性 /
- 循环设计 /
- 非劣解集 /
- 分布式协同响应面法
Abstract: In order to evolve aeroengine overall performance design from the deterministic design to the probabilistic design, an aeroengine cycle optimization design approach for multiple operating conditions performance reliability based on distributed cooperative response surface method (DCRSM) was proposed. The turbofan engine simulation model with uncertainty component performance was established as an example. The distributed response surface models of thrust and special fuel consumption performance under several typical operating conditions were established by the experimental design and the off design point performance simulation, and then the cooperative response surface model was established for cycle optimization. The non inferiority solution set of the cycle parameters was generated from optimization and verified by the random trial. The results showed that the all cycle parameters from the non inferiority solution set could make the engine overall performance achieve a high reliability of not less than 97.5% simultaneously under all expected operating conditions. From the non inferiority solution set obtained by multiple operating conditions performance reliability cycle optimization method, the most suitable cycle selection can be decided according to the physical truth in engine preliminary design phase.
- aero-engine /
- overall performance /
- reliability /
- cycle design /
- pareto-optimal solutions /
- distributed cooperative response surface method

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参考文献(24)

[1]	KURZ R,BRUN K.Degradation in gas turbine systems［J］.Journal of Engineering for Gas Turbines and Power,2001,123(1):70-77.
[2]	ERIE S H.A multi-level multi-design point approach for gas turbine cycle and turbine conceptual design［D］.Georgia,USA:Georgia Institute of Technology,2017:47-52.
[3]	MAVRIS D N,MAESOTAI N I,ROTH B.A probabilistic design methodology for commercial aircraft engine cycle selection［R］.SAE Paper 985510,1998.
[4]	MAVRIS P D,ROTH M B,MAESOTAI M N.A method for probabilistic sensitivity analysis of commercial aircraft engines［R］.Florence,Italy:14th International Society For Air Breathing Engines Conference,1999.
[5]	TONG M T,JONES S M,AREARA P C,et al.A probabilistic assessment of NASA ultra-efficient engine technologies for a large subsonic transport［R］ASME Paper GT-2004-53485,2004.
[6]	ROTH B,MAVRIS D.A probabilistic approach to UCAV engine sizing［R］.AIAA 98-3264,1998.
[7]	GORLA R S R,PAI S S,RUSICK J.Probabilistic analysis of gas turbine field performance［R］.NASA/TM-2002-211699,2002.
[8]	BANDTE O.A probabilistic multi-criteria decision making technique for conceptual and preliminary aerospace systems design［D］.Georgia,USA:Georgia Institute of Technology,2000.
[9]	FOX E P.The Pratt & Whitney probabilistic design system［R］.AIAA-94-1442-CP,1994.
[10]	STRACK W,MAHADEVAN S,VENKATARAMAN S,et al.A probabilistic software tool subjecting component designs to system-level reliability constraints［R］.Parma Heights,Ohio:N & R Engineering,2007.
[11]	SCHUTTE J,TAI J,SANDS J,et al.Cycle design exploration using multi-design point approach［R］.ASME Paper GT2012-69334,2012.
[12]	HUGHES M J,PERULLO C,MAVRIS D N.Common core engine design for multiple applications using a concurrent multi-design point approach［R］.AIAA 2014-3443,2014.
[13]	HENDRICKS E S.Development of an open rotor cycle model in NPSS using a multi-design point approach［R］.NASA/TM-2011-217225,2011.
[14]	胡殿印,裴月,王荣桥.涡轮盘低循环疲劳的概率设计［J］.推进技术,2008,29(4):481-487.HU Dianyin,PEI Yue,WANG Rongqiao.Probability design for low cycle fatigue of turbine disk［J］.Journal of Propulsion Technology,2008,29(4):481-487.(in Chinese)
[15]	裴月,薛飞,王荣桥.涡轮盘低循环疲劳寿命可靠性研究［J］.燃气涡轮试验与研究,2007,20(1):39-43.PEI Yue,XUE Fei,WANG Rongqiao.Reliability research for the low cycle fatigue life of a turbine disk［J］.Gas Turbine Experiment and Research,2007,20(1):39-43.(in Chinese)
[16]	李晓斌,王林.基于概率论与可信性理论的不确定性设计方法［J］.弹箭与制导学报,2009,29(6):245-248,252.LI Xiaobin,WANG Lin.Uncertainty design method using probability theory and credibility theory［J］.Journal of Projectiles,Rocket,Missiles and Guidance,2009,29(6):245-248,252.(in Chinese)
[17]	唐海龙,张坤.部件性能非确定对涡轴发动机影响量化方法研究［J］.推进技术,2015,36(8):1143-1150.TANG Hailong,ZHANG Kun.Quantification method of effects of uncertainty on component performance for turbo-shaft engine performance［J］.Journal of Propulsion Technology,2015,36(8):1143-1150.(in Chinese)
[18]	BAI G,FEI C.Distributed collaborative response surface method for mechanical dynamic assembly reliability design［J］.Chinese Journal of Construction Machinery,2013,26(6):1160-1168.
[19]	费成巍,白广忱.基于DCRSM的HPT叶尖径向运行间隙可靠性分析［J］.航空学报,2013,34(9):2141-2149.FEI Chengwei,BAI Guangchen.Reliability analysis for HPT blade-tip radial running clearance based on DCRSM［J］.Acta Aeronautica et Astronautica Sinica,2013,34(9):2141-2149.(in Chinese)
[20]	FERREIRA S L C,BRUNS R E,FERREIRA H S,et al.Box-Behnken design:an alternative for the optimization of analytical methods［J］.Analytica Chimica Acta,2007,597(2):179-186.
[21]	李立君,尹泽勇,乔渭阳.基于多目标遗传算法的航空发动机总体性能优化设计［J］.航空动力学报,2006,21(1):13-18.LI Lijun,YIN Zeyong,QIAO Weiyang.Performance optimal design of aircraft engine based on multi-objective genetic algorithms［J］.Journal of Aerospace Power,2006,21(1):13-18.(in Chinese)
[22]	刘大响,程荣辉.世界航空动力技术的现状及发展动向［J］.北京航空航天大学学报,2002,28(5):490-496.LIU Daxiang,CHENG Ronghui.Current status and development direction of aircraft power technology in the world［J］.Journal of Beijing University of Aeronautics and Astronautics,2002,28(5):490-496.(in Chinese)
[23]	肖树国,钱秦生.航空发动机设计手册:第五册涡喷及涡扇发动机总体［M］.北京:航空工业出版社,2003:26-33.
[24]	何为,薛卫东,唐斌.优化试验设计方法及数据分析［M］.北京：化学工业出版社,2012:243-245.