某型航空发动机整机振动特性分析
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摘要
发动机整机振动不仅使发动机的工作状态、发动机附件及仪表的工作状态受到影响,而且会使发动机的结构受到巨大的振动应力,影响发动机工作的可靠性。近年来,有限元计算技术和计算机技术的逐渐发展,为航空发动机整机振动特性的研究提供了必要条件。为保证航空发动机的工作安全、可靠,本文针对某型双转子航空发动机结构特点,进行了整机振动特性相关分析;从转子的临界转速特性分析、机匣振动特性分析到整机振动特性分析,开展了如下相关研究工作:
第一,为了使发动机整机振动有限元模型合理可信,本文首先利用有限元理论对发动机机匣模型进行了一定的简化处理,计算了发动机机匣的振动模态及其各主支承处的静刚度与动刚度,比较了两者之间的差别。研究结果表明:由于发动机机匣在工作转速内固有模态的影响,考虑机匣及支承结构动刚度计算的转子临界转速更加合理、可靠,也表明了整机振动分析的必要性。
第二,针对本文研究的航空发动机结构特点,分别分析了高、低压转子考虑机匣及其支承静、动刚度模型下的临界转速特性。
第三,利用传递矩阵法计算了发动机高、低压转子临界转速,并与有限元模型进行了对比。研究结果表明:在相同支承刚度下,传递矩阵法与有限元法计算结果误差在10%以内,计算结果可信。
第四,建立了某型航空发动机整机振动分析模型,进行了整机振动特性分析,分析了双转子耦合效应对系统临界转速的影响,研究了螺栓连接、不同支承刚度、不同转速比对系统临界转速的影响。研究结果表明:对于本文研究的双转子航空发动机,运用整机模型计算其转子的临界转速更加合理,其计算结果更接近于实际。
The whole aero-engine vibration not only influences the working state of engine,accessories and instrument, but also brings engine structure huge vibration stress, so research on the whole body vibration of aero-engine is essential. According to the development of technology of the FEM software and computer, calculating the whole body vibration of aero-engine is becoming possible. In order to ensure aero-engine working safety and reliability, the finite element model of the whole aero-engine is built and used to analyse the whole body vibration, basing on its structural characteristic. The research work is carried out from analysis of the rotor critical speed and the vibration of casing to analysis of the whole body vibration, it is as follows:
Firstly, in oreder to insure bilievable of the model of whole body aero-engine, the finite element calculation model of engine-casing is reasearched using some base theory, the static rigidity and dynamic rigidity of casing is analyzed with model. The calculating result of the critical speed of the rotor indicates that dynamic rigidity model is more reasonable than static rigidity model, owing to the caing natural modal appearing area of the working speed.
Secondly, according to properties of the aero-engine structure, the characteristics of critical speeds are calculated separately adopting static rigidity and dynamic rigidity model of the low-pressure and the high-pressure rotor in the article.
Thirdly, the critical speeds of the low-pressure and the high-pressure rotor are calculated with the transfer matrix method, and the calculating results are compared with the finite element model. It indicates the results of both methods are close; the errors within 10% and the calculating results reliabilities.
Fourthly, the finite element model of the whole aero-engine is built and used to analyse the whole body vibration. The influence of the critical speed with the coupled effect between the dual-rotor is analyzed, and the influence with the different supporter’s stiffness、the different speed ratio and bolt connection is researched in the article. It is found that, the calculating results of the critical speeds with the whole aero-engine model are reasonable, and close to reality.
第一,为了使发动机整机振动有限元模型合理可信,本文首先利用有限元理论对发动机机匣模型进行了一定的简化处理,计算了发动机机匣的振动模态及其各主支承处的静刚度与动刚度,比较了两者之间的差别。研究结果表明:由于发动机机匣在工作转速内固有模态的影响,考虑机匣及支承结构动刚度计算的转子临界转速更加合理、可靠,也表明了整机振动分析的必要性。
第二,针对本文研究的航空发动机结构特点,分别分析了高、低压转子考虑机匣及其支承静、动刚度模型下的临界转速特性。
第三,利用传递矩阵法计算了发动机高、低压转子临界转速,并与有限元模型进行了对比。研究结果表明:在相同支承刚度下,传递矩阵法与有限元法计算结果误差在10%以内,计算结果可信。
第四,建立了某型航空发动机整机振动分析模型,进行了整机振动特性分析,分析了双转子耦合效应对系统临界转速的影响,研究了螺栓连接、不同支承刚度、不同转速比对系统临界转速的影响。研究结果表明:对于本文研究的双转子航空发动机,运用整机模型计算其转子的临界转速更加合理,其计算结果更接近于实际。
The whole aero-engine vibration not only influences the working state of engine,accessories and instrument, but also brings engine structure huge vibration stress, so research on the whole body vibration of aero-engine is essential. According to the development of technology of the FEM software and computer, calculating the whole body vibration of aero-engine is becoming possible. In order to ensure aero-engine working safety and reliability, the finite element model of the whole aero-engine is built and used to analyse the whole body vibration, basing on its structural characteristic. The research work is carried out from analysis of the rotor critical speed and the vibration of casing to analysis of the whole body vibration, it is as follows:
Firstly, in oreder to insure bilievable of the model of whole body aero-engine, the finite element calculation model of engine-casing is reasearched using some base theory, the static rigidity and dynamic rigidity of casing is analyzed with model. The calculating result of the critical speed of the rotor indicates that dynamic rigidity model is more reasonable than static rigidity model, owing to the caing natural modal appearing area of the working speed.
Secondly, according to properties of the aero-engine structure, the characteristics of critical speeds are calculated separately adopting static rigidity and dynamic rigidity model of the low-pressure and the high-pressure rotor in the article.
Thirdly, the critical speeds of the low-pressure and the high-pressure rotor are calculated with the transfer matrix method, and the calculating results are compared with the finite element model. It indicates the results of both methods are close; the errors within 10% and the calculating results reliabilities.
Fourthly, the finite element model of the whole aero-engine is built and used to analyse the whole body vibration. The influence of the critical speed with the coupled effect between the dual-rotor is analyzed, and the influence with the different supporter’s stiffness、the different speed ratio and bolt connection is researched in the article. It is found that, the calculating results of the critical speeds with the whole aero-engine model are reasonable, and close to reality.
引文
[1]任兴明.航空发动机整机动力特性分析方法研究[博士论文].西安:西北工业大学,1999.
[2]傅志方.模态分析技术在航空发动机振动故障分析中的应用.第四届全国振动理论及应用学术会议论文集,河南郑州,1990年4月:541～548.
[3] Graziano Curti, Francesco A.Raffa, and Furio Vatta.Steady-State Unbalance Response of Continuous Rotors on Ansotropic Supports.The 1993 ASME Design Technical Conferences 14th BIENNIAL Conference on Mechanical Vibration and Naoise, DE-Vol.60, Vibration of Rotating Systems, ALBUQUERQUE, NEW MEXICO ,September 19,1993:27～34.
[4]孟光.转子动力学研究的回顾与展望.振动工程学报,2002年3月,15(1)
[5]欧园霞,李彦.子结构传递矩阵法、有限元素法、模态综合法应用于转子动力特性计算时的对比分析.全国第三届转子动力学学术讨论会论文集,山东青岛,1992年10月:47～53.
[6]郭力.子结构传递矩阵法、有限元素法和模态综合法应用于转子动力特性计算时的对比分析.Power System Engineering,1999年3月.
[7] Gu Jialiu. An Improved Transfer Matrix-Direction Integration Method for Rotordynamics, Tans.ASME, Journal of Vibration, Acoustics, Stress, and Reliability in Design,Vol.108,April 1986,182～188
[8]顾家柳等.转子动力学[M].北京:国防工业出版社,1985.
[9]欧园霞,李平.用模态综合法分析发动机整机振动特性.航空动力学报,1987年7月,第2卷第3期:209～214.
[10]欧园霞,李彦.转子动力特性计算中常用方法的对比分析.航空动力学报,1994,第9卷第2期.
[11]华明达,李其汉.复杂转子——支承——机匣系统的动力特性分析.全国第三届转子动力学学术讨论会论文集,山东,青岛,1992年10月:1～6.
[12]苏民,戴远建.复杂转子整机振动计算.热能动力工程,1988年11月,第3卷第6期:46～50.
[13] Zheng Zhao-chang et al. The Complex Modal Analysis for the large Rotor-Bearing -Foundation-System. The 1987 ASME Design Technology Conferences 11th BIENNIAL Conference on Mechanical Vibration and Noise , Boston, MASSACHUSETS, September 27, 1987:391～397.
[14] Verhoeven J .Excitation Force Identification of Rotating Machines Using Operational RotorAmplitude Data And Analytical Synthesized Transfer Functions, The 1987 ASEM Design Technology Conferences 11th BIENNIAL Conference on Mechanical Vibration and Noise, Boston, MASSACHUSETS, September 27.1987:207～214.
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[16] H.D. Nelson, J.M. Mc Vaugh: The Dynamics of Rotor-Bearing Systems Using Finite Elements, J. of Eng. for Indus. Trans. ASME vol.98,No.2,May 1976:593～600.
[17] R. Gasch: Vibration of Large Turbo-Rotors in Fluid-Film Bearing on An Elastic Foundation, J. of Sound and Vib.vol.47, No.1,1976:53～73.
[18] E,S. Zorzi, H.D .Nelson. Finite Element Simulation of Rotor Bearing Systems with Internal Damping, J. of Eng, for Power,ASME,vol.99,No.1,Jan 1977:71～76.
[19] H.D. Nelon: A Finite Rotating Shaft Element using Timoshenko Beam Theory, J.of Mech. Des. Trans. ASME, vol. 102, oct. 1980:793～803.
[20] H.Nevzat ozguven, Z Levent ozkan. Whirl Speeds and Unbalance Response of Multi bearing Rotors using Finite Element, J. of Vib. Acoustics, Stress and Reliability in Des.Trans.ASME,vol.106, No.1, Jan.1984:72～79.
[21] E. Hashish, T. S. Sankar: Finite Element and Modal Analyses of Rotor-Bearing Systems Under Stochastic Loading Conditions, Ibid. vol.106, No.1, Jan. 1984:80～89.
[22]付才高,郑大平.航空发动机设计手册(第十九册):转子动力学及整机振动.航空工业出版社,2000年:60～61,150～158.
[23]李智炜,杨伸纪.航空发动机支承系统的动柔度系数矩阵及其测量.航空动力学报.1988,第3卷第1期:73～75.
[24]吕和祥.发动机机匣、支板系统结构动力分析.航空动力学报,1994,第9卷第2期.
[25]高金海,洪杰.航空发动机整机动力特性建模技术研究.战术导弹技术,2006年5月:29～35.
[26]洪杰,王华.转子支承动刚度对转子动力特性的影响分析.航空发动机,2008,3,34(1)
[27]李玲玲,王克明.某型航空发动机后支承动刚度的有限元计算.沈阳航空工业学院学报,2007,24(3).
[28]闻邦春,顾家柳,夏松波等.高等转子动力学——理论、技术与应用[M].北京:机械工业出版社,2000.
[29]钟一鄂等.转子动力学[M].北京:清华大学出版社,1984:3～17.
[30]陈萌等.航空发动机整机有限元模型转子动力学分析.北京航空航天大学学报,2007年月,第33卷第9期:1013～1016.
[31]孙红岩.利用有限元进行转子系统的动力学分析[硕士论文].西安:西安建筑科技大学,2008.6.
[32] Wettergren H L. Dynamics Instability of Composite Rotors. Proceeding of The 4th International Conference on Rotor dynamics, IFToMM, Chicago, USA, 1994:287～292.
[33]陈萌,洪杰.基于实体单元的转子动力特性计算方法.北京航空航天大学学报,2007,33(1).
[34] Gunter E J et al. Dynamics Characteristics of a Two-Spool Gas Turbine Helicopter Engine. Proceedings of The Conference on Stability and Dynamics Response of Rotors with Squeeze Film Bearings, Charlottesville, USA, 1979.
[35] Vance J M. Rotor dynamics of Turbo machinery. New York: John Wiley & Sons ,1988.
[36] H.D. Nelson, Rotor dynamic modeling and analysis procedures: a review. JSME International Journal, Series C 41 (1998) 1～12.
[37]刘铁牛,吴江宁.航空发动机系统的动力分析.航空动力学报,1994年,第9卷第2期.
[38]将苏运等.用整体传递矩阵法计算航空发动机整机临界转速特性.哈尔滨工业大学学报.1998,1.(30).
[39]李永强,朱亮等.用整体传递矩阵法计算旋转机械整机固有频率特性.东北大学学报.2005.12.(26).
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[2]傅志方.模态分析技术在航空发动机振动故障分析中的应用.第四届全国振动理论及应用学术会议论文集,河南郑州,1990年4月:541～548.
[3] Graziano Curti, Francesco A.Raffa, and Furio Vatta.Steady-State Unbalance Response of Continuous Rotors on Ansotropic Supports.The 1993 ASME Design Technical Conferences 14th BIENNIAL Conference on Mechanical Vibration and Naoise, DE-Vol.60, Vibration of Rotating Systems, ALBUQUERQUE, NEW MEXICO ,September 19,1993:27～34.
[4]孟光.转子动力学研究的回顾与展望.振动工程学报,2002年3月,15(1)
[5]欧园霞,李彦.子结构传递矩阵法、有限元素法、模态综合法应用于转子动力特性计算时的对比分析.全国第三届转子动力学学术讨论会论文集,山东青岛,1992年10月:47～53.
[6]郭力.子结构传递矩阵法、有限元素法和模态综合法应用于转子动力特性计算时的对比分析.Power System Engineering,1999年3月.
[7] Gu Jialiu. An Improved Transfer Matrix-Direction Integration Method for Rotordynamics, Tans.ASME, Journal of Vibration, Acoustics, Stress, and Reliability in Design,Vol.108,April 1986,182～188
[8]顾家柳等.转子动力学[M].北京:国防工业出版社,1985.
[9]欧园霞,李平.用模态综合法分析发动机整机振动特性.航空动力学报,1987年7月,第2卷第3期:209～214.
[10]欧园霞,李彦.转子动力特性计算中常用方法的对比分析.航空动力学报,1994,第9卷第2期.
[11]华明达,李其汉.复杂转子——支承——机匣系统的动力特性分析.全国第三届转子动力学学术讨论会论文集,山东,青岛,1992年10月:1～6.
[12]苏民,戴远建.复杂转子整机振动计算.热能动力工程,1988年11月,第3卷第6期:46～50.
[13] Zheng Zhao-chang et al. The Complex Modal Analysis for the large Rotor-Bearing -Foundation-System. The 1987 ASME Design Technology Conferences 11th BIENNIAL Conference on Mechanical Vibration and Noise , Boston, MASSACHUSETS, September 27, 1987:391～397.
[14] Verhoeven J .Excitation Force Identification of Rotating Machines Using Operational RotorAmplitude Data And Analytical Synthesized Transfer Functions, The 1987 ASEM Design Technology Conferences 11th BIENNIAL Conference on Mechanical Vibration and Noise, Boston, MASSACHUSETS, September 27.1987:207～214.
[15] Duhl R, L: Dynamics of Distributed Parameter Turbo rotor Systems: Transfer Matrix and Finite Element Techniques, Ph.D. Tesis, Cornell University, Ithaca N.Y.Jan.1970.
[16] H.D. Nelson, J.M. Mc Vaugh: The Dynamics of Rotor-Bearing Systems Using Finite Elements, J. of Eng. for Indus. Trans. ASME vol.98,No.2,May 1976:593～600.
[17] R. Gasch: Vibration of Large Turbo-Rotors in Fluid-Film Bearing on An Elastic Foundation, J. of Sound and Vib.vol.47, No.1,1976:53～73.
[18] E,S. Zorzi, H.D .Nelson. Finite Element Simulation of Rotor Bearing Systems with Internal Damping, J. of Eng, for Power,ASME,vol.99,No.1,Jan 1977:71～76.
[19] H.D. Nelon: A Finite Rotating Shaft Element using Timoshenko Beam Theory, J.of Mech. Des. Trans. ASME, vol. 102, oct. 1980:793～803.
[20] H.Nevzat ozguven, Z Levent ozkan. Whirl Speeds and Unbalance Response of Multi bearing Rotors using Finite Element, J. of Vib. Acoustics, Stress and Reliability in Des.Trans.ASME,vol.106, No.1, Jan.1984:72～79.
[21] E. Hashish, T. S. Sankar: Finite Element and Modal Analyses of Rotor-Bearing Systems Under Stochastic Loading Conditions, Ibid. vol.106, No.1, Jan. 1984:80～89.
[22]付才高,郑大平.航空发动机设计手册(第十九册):转子动力学及整机振动.航空工业出版社,2000年:60～61,150～158.
[23]李智炜,杨伸纪.航空发动机支承系统的动柔度系数矩阵及其测量.航空动力学报.1988,第3卷第1期:73～75.
[24]吕和祥.发动机机匣、支板系统结构动力分析.航空动力学报,1994,第9卷第2期.
[25]高金海,洪杰.航空发动机整机动力特性建模技术研究.战术导弹技术,2006年5月:29～35.
[26]洪杰,王华.转子支承动刚度对转子动力特性的影响分析.航空发动机,2008,3,34(1)
[27]李玲玲,王克明.某型航空发动机后支承动刚度的有限元计算.沈阳航空工业学院学报,2007,24(3).
[28]闻邦春,顾家柳,夏松波等.高等转子动力学——理论、技术与应用[M].北京:机械工业出版社,2000.
[29]钟一鄂等.转子动力学[M].北京:清华大学出版社,1984:3～17.
[30]陈萌等.航空发动机整机有限元模型转子动力学分析.北京航空航天大学学报,2007年月,第33卷第9期:1013～1016.
[31]孙红岩.利用有限元进行转子系统的动力学分析[硕士论文].西安:西安建筑科技大学,2008.6.
[32] Wettergren H L. Dynamics Instability of Composite Rotors. Proceeding of The 4th International Conference on Rotor dynamics, IFToMM, Chicago, USA, 1994:287～292.
[33]陈萌,洪杰.基于实体单元的转子动力特性计算方法.北京航空航天大学学报,2007,33(1).
[34] Gunter E J et al. Dynamics Characteristics of a Two-Spool Gas Turbine Helicopter Engine. Proceedings of The Conference on Stability and Dynamics Response of Rotors with Squeeze Film Bearings, Charlottesville, USA, 1979.
[35] Vance J M. Rotor dynamics of Turbo machinery. New York: John Wiley & Sons ,1988.
[36] H.D. Nelson, Rotor dynamic modeling and analysis procedures: a review. JSME International Journal, Series C 41 (1998) 1～12.
[37]刘铁牛,吴江宁.航空发动机系统的动力分析.航空动力学报,1994年,第9卷第2期.
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