脉冲爆震载荷作用下转子系统动力学特性

李胜远; 郑龙席; 贾胜锡; 梅庆

doi:10.13224/j.cnki.jasp.2019.09.010

脉冲爆震载荷作用下转子系统动力学特性

doi: 10.13224/j.cnki.jasp.2019.09.010

1.
西北工业大学动力与能源学院,西安 710072
2.
中国航空发动机集团有限公司湖南动力机械研究所航空发动机振动技术航空科技重点实验室,湖南株洲 412002

计量
- 文章访问数: 1290
- HTML浏览量: 276
- PDF量: 1011
- 被引次数: 0
出版历程
- 收稿日期: 2019-04-24
- 刊出日期: 2019-09-28

Dynamic characteristics of rotor system subjected to pulse detonation aerodynamic loads

摘要

摘要: 针对脉冲爆震涡轮发动机(PDTE)气动载荷具有周期性、非定常的特点,应用有限元法建立了PDTE转子系统动力学特性计算模型。在验证计算模型准确性的基础上,研究了周期性、非定常轴向力和扭矩对转子系统动力学特性的影响。研究结果表明:与传统燃气涡轮发动机相比,PDTE转子系统同时存在弯曲振动、轴向振动和扭转振动。脉冲爆震燃烧室的气动载荷会改变转子系统的弯曲刚度,但对气动载荷合理设计后,其对弯曲振动的影响较小。周期性、非定常轴向力引起转子系统轴向振动,且轴向振动特性主要受零频和1阶轴向共振频率处响应的影响。PDTE工作时滚珠轴承的轴向支反力会不断变向,在设计滚珠轴承时应予以考虑。周期性、非定常扭矩引起转子系统扭转振动,1阶扭转共振频率分量在扭转振动响应中占优。
- 脉冲爆震涡轮发动机 /
- 非定常气动载荷 /
- 转子动力学 /
- 弯曲振动 /
- 轴向振动 /
- 扭转振动
Abstract: In view of the periodic and unsteady aerodynamic loads of pulse detonation turbine engine(PDTE), finite element method was used to establish a dynamic characteristics calculation model for rotor system of PDTE. On the basis of verifying the accuracy of the calculation model, the effects of periodic and unsteady axial force and torque on the dynamics characteristics of rotor system were studied. The results show that compared with traditional gas turbine engine, the rotor system of PDTE has bending vibration, axial vibration and torsional vibration at the same time. Aerodynamic loads of pulse detonation combustor change bending stiffness of rotor system, but it has little effect on bending vibration in case of reasonable design. Periodic and unsteady axial force causes axial vibration of rotor system, and the axial vibration characteristics are mainly affected by the responses at zero frequency and the first order axial resonance frequency. When PDTE is in service state, the axial reaction force of ball bearing changes direction continuously, which should be considered in the design of ball bearings. Periodic and unsteady torque causes torsional vibration of rotor system, and the first order torsional resonance frequency component is dominant in torsional vibration response.
- pulse detonation turbine engine /
- unsteady aerodynamic loads /
- rotordynamics /
- bending vibration /
- axial vibration /
- torsional vibration

HTML

参考文献(23)

[1]	严传俊,何立明,范玮,等.脉冲爆震发动机的研究与发展［J］.航空动力学报,2001,16(3):212-217.YAN Chuanjun,HE Liming,FAN Wei,et al.Research and development of pulse detonation engine［J］.Journal of Aerospace Power,2001,16(3):212-217.(in Chinese)
[2]	ENDO T,KASAHARA J,MATSUO A,et al.Pressure history at the thrust wall of a simplified pulse detonation engine［J］.AIAA Journal,2004,42(9):1921-1930.
[3]	郑龙席,卢杰,严传俊,等.脉冲爆震涡轮发动机研究进展［J］.航空动力学报,2014,29(5):993-1000.ZHENG Longxi,LU Jie,YAN Chuanjun,et al.Research progress on pulse detonation turbine engine［J］.Journal of Aerospace Power,2014,29(5):993-1000.(in Chinese)
[4]	邓芃,郑龙席,王凌羿.脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究［J］.航空动力学报,2018,33(8):1864-1871.DENG Peng,ZHENG Longxi,WANG Lingyi.Numerical study on matching mechanism and efficiency of pulse detonation combustor and impulse turbine［J］.Journal of Aerospace Power,2018,33(8):1864-1871.(in Chinese)
[5]	YE F,BUTUK N,HUQUE Z,et al.CFD optimization of a integrated multi-tube PDE/inlet concept using complex variables［R］.AIAA 99-3229,1999.
[6]	RASHEED A,FURMAN A H,DEAN A J.Pressure measurements and attenuation in a hybrid multitube pulse detonation turbine system［J］.Journal of Propulsion and Power,2009,25(1):148-161.
[7]	GIULIANI F,LANG A,IRANNEZHAD M,et al.Pulse detonation as an option for future innovative gas turbine combustion technologies:a concept assessment［C］∥Proceedings of 27th International Congress of the Aeronautical Sciences.Nice,France:International Council of the Aeronautical Sciences,2010:19-24.
[8]	李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验［J］.航空动力学报,2013,28(12):2731-2736.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Two phase pulse detonation turbine engine original rational test［J］.Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
[9]	邱华,徐泽阳,郑龙席,等.脉冲爆震涡轮发动机增推装置性能试验［J］.航空学报,2016,37(2):522-532.QIU Hua,XU Zeyang,ZHENG Longxi,et al.Tests of pulse detonation turbine engine performance with thrust augmentation devices［J］.Acta Aeronautica et Astronautica Sinica,2016,37(2):522-532.(in Chinese)
[10]	RASHEED A,FURMAN A,DEAN A J.Experimental investigations of an axial turbine driven by a multi-tube pulsed detonation combustor system［R］.AIAA-2005-4209,2005.
[11]	RASHEED A,FURMAN A H,DEAN A J.Experimental investigations of the performance of a multitube pulse detonation turbine system［J］.Journal of Propulsion and Power,2011,27(3):586-596.
[12]	ROUSER K,KING P,SCHAUER F,et al.Unsteady performance of a turbine driven by a pulse detonation engine［R］.AIAA-2010-1116,2010.
[13]	ROUSER K,KING P,SCHAUER F,et al.Parametric study of unsteady turbine performance driven by a pulse detonation combustor［R］.AIAA-2010-6536,2010.
[14]	CALDWELL N,GLASER A,DIMICCO R,et al.Acoustic measurements of an integrated pulse detonation engine with gas turbine system［R］.AIAA-2005-413,2005.
[15]	GLASER A,CALDWELL N,GUTMARK E.Performance of an axial flow turbine driven by multiple pulse detonation combustors［R］.AIAA-2007-1244,2007.
[16]	路振勇,陈予恕,侯磊,等.常开空心轴裂纹转子系统的动力学特性［J］.航空动力学报,2015,30(2):422-430.LU Zhenyong,CHEN Yushu,HOU Lei,et al.Dynamic characteristics of a open crack in hollow shaft rotor system［J］.Journal of Aerospace Power,2015,30(2):422-430.(in Chinese)
[17]	KHULIEF Y A,AL-NASER H.Finite element dynamic analysis of drillstrings［J］.Finite Elements in Analysis and Design,2005,41(13):1270-1288.
[18]	FENG T,VADALI M,MA Z,et al.A finite element method with full bit-force modeling to analyze drillstring vibration［J］.Journal of Dynamic Systems,Measurement,and Control,2017,139(9):091016.1-091016.10.
[19]	DAWE D J.Matrix and finite element displacement analysis of structures［M］.New York:Oxford University Press,1984.
[20]	ZORZI E S,NELSON H D.The dynamics of rotor-bearing systems with axial torque-a finite element approach［J］.Journal of Mechanical Design,1980,102(1):158-161.
[21]	NELSON H D,MCVAUGH J M.The dynamics of rotor-bearing systems using finite elements［J］.Journal of Engineering for Industry,1976,98(2):593-600.
[22]	FRISWELL M I,PENNY J E T,GARVEY S D,et al.Dynamics of rotating machines［M］.New York:Cambridge University Press,2010.
[23]	路振勇,陈予恕,李洪亮,等.航空发动机转子系统动力学模型的可逆化简化方法［J］.航空动力学报,2016,31(1):57-64.LU Zhenyong,CHEN Yushu,LI Hongliang,et al.Reversible model-simplifying method for aero-engine rotor systems［J］.Journal of Aerospace Power,2016,31(1):57-64.(in Chinese)