转轴-轮盘-裂纹叶片耦合系统的叶尖振动特性

doi:10.7527/S1000-6893.2023.28346

Abstract

Abstract:

Aero-engine blades， subjected to extreme environmental conditions， are susceptible to crack development， which shortens blade life and seriously affects the safe operation of aero-engine. This paper focuses on the shaft-disk-cracked-blade coupling system which is modeled using the mixed strategy of the finite element method and the assumed mode method. The shaft is simulated by finite element method， while the disk and blade are simulated by Kirchhoff plate theory and Timoshenko beam theory. A dynamic model is built based on time-varying loss stiffness caused by the breathing crack which is determined by the time-varying release strain energy. The correctness of the proposed method is confirmed by comparing the natural characteristics and vibration responses of the coupling system. The influences of gravity load， rotor unbalance force and aerodynamic load on vibration characteristics of the blade tip are analyzed， and the impact of different dimensionless crack depths and crack locations on the vibration characteristics of the blade tip are investigated. The research results show that： in a healthy blade， the gravity load can cause the blade to vibrate， and the unbalanced force can induce the static deformation of the blade； under rotation， the cracked blade leads to the bending displacement of the blade tip， which produces an offset， while under the action of aerodynamic load， the breathing crack results in nonlinear vibration of the blade； the amplitude ratio of the constant component to the rotational frequency and the amplitude ratio of the constant component to the aerodynamic excitation frequency are valuable indicators for assessing breathing crack. The modeling method and analysis conclusions in this paper can provide a specific theoretical basis for the fault diagnosis of aero-engine blade crack.

Key words: shaft-disk-cracked-blade, breathing crack, gravity load, rotor unbalance force, aerodynamic load

CLC Number:

V231.96

Zhiyuan WU, Linchuan ZHAO, Ge YAN, Haifeng HU, Zhibo YANG, Wenming ZHANG. Vibration characteristics of blade tip in a shaft⁃disk⁃cracked⁃blade coupling system[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4): 628346-628346.

Figures/Tables 19

Fig.1

Fig.2

Fig.3

Fig.4

Fig.5

Fig.6

Table 1

Fig.7

Fig.8

Table 2

Fig.9

Fig.10

Fig.11

Fig.12

Fig.13

Fig.14

Fig.15

Fig.16

Fig.17

References 31

1	WANG W M， ZHANG X L， HU D F， et al. A novel none once per revolution blade tip timing based blade vibration parameters identification method［J］. Chinese Journal of Aeronautics， 2020， 33（7）： 1953-1968.
2	ZHANG X D， XIONG Y W， HUANG X， et al. Dynamic characteristics analysis of 3D blade tip clearance for turbine blades with typical cracks［J］. International Journal of Aerospace Engineering， 2022， 2022： 1-17.
3	ZENG J， CHEN K K， MA H， et al. Vibration response analysis of a cracked rotating compressor blade during Run-up process［J］. Mechanical Systems and Signal Processing， 2019， 118： 568-583.
4	CHEN Z S， SHENG H， XIA Y M， et al. A comprehensive review on blade tip timing-based health monitoring： status and future［J］. Mechanical Systems and Signal Processing， 2021， 149： 107330.
5	YANG L H， MAO Z， WU S M， et al. Steady-state coupling vibration analysis of shaft-disk-blade system with blade crack［J］. Nonlinear Dynamics， 2021， 105（1）： 61-98.
6	CHIU Y J， HUANG S C. The influence of a cracked blade on rotor’s free vibration［J］. Journal of Vibration and Acoustics， 2008， 130（5）： 1.
7	刘美茹，朱靖，梁恩波，等. 基于叶尖定时的航空发动机压气机叶片振动测量［J］. 航空动力学报， 2019， 34（9）： 1895-1904.
	LIU M R， ZHU J， LIANG E B， et al. Vibration measurement on compressor rotor blades of aero-engine based on tip-timing［J］. Journal of Aerospace Power， 2019， 34（9）： 1895-1904 （in Chinese）.
8	刘美茹，郜伟强，范毅，等. 叶尖定时技术在转子叶片故障排除中的应用［J］. 航空动力学报， 2022， 37（12）： 2818-2829.
	LIU M R， GAO W Q， FAN Y， et al. Application of blade tip timing technology in rotor blade fault elimination［J］. Journal of Aerospace Power， 2022， 37（12）： 2818-2829 （in Chinese）.
9	XU H L， CHEN Z S， XIONG Y P， et al. Nonlinear dynamic behaviors of rotated blades with small breathing cracks based on vibration power flow analysis［J］. Shock and Vibration， 2016， 2016： 1-11.
10	XIE J S， ZI Y Y， ZHANG M Q， et al. A novel vibration modeling method for a rotating blade with breathing cracks［J］. Science China Technological Sciences， 2019， 62（2）： 333-348.
11	YANG L H， YANG Z S， MAO Z， et al. Dynamic characteristic analysis of rotating blade with transverse crack—Part I： Modeling， modification， and validation［J］. Journal of Vibration and Acoustics， 2021， 143（5）： 051010.
12	LIU C， JIANG D X. Crack modeling of rotating blades with cracked hexahedral finite element method［J］. Mechanical Systems and Signal Processing， 2014， 46（2）： 406-423.
13	ZHAO C G， ZENG J， MA H， et al. Dynamic analysis of cracked rotating blade using cracked beam element［J］. Results in Physics， 2020， 19： 103360.
14	KUANG J H， HUANG B W. The effect of blade crack on mode localization in rotating bladed disks［J］. Journal of Sound and Vibration， 1999， 227（1）： 85-103.
15	HUANG B W， KUNG H K， KUANG J H. Stability in a twisted periodic blade system with cracks［J］. AIAA Journal， 2006， 44（7）： 1436-1444.
16	HUANG B W. Effect of number of blades and distribution of cracks on vibration localization in a cracked pre-twisted blade system［J］. International Journal of Mechanical Sciences， 2006， 48（1）： 1-10.
17	JUNG C， SAITO A， EPUREANU B I. Detection of cracks in mistuned bladed disks using reduced-order models and vibration data［J］. Journal of Vibration and Acoustics， 2012， 134（6）： 061010.
18	MA H， LU Y， WU Z Y， et al. A new dynamic model of rotor-blade systems［J］. Journal of Sound and Vibration， 2015， 357： 168-194.
19	SHE H X， LI C F， TANG Q S， et al. The investigation of the coupled vibration in a flexible-disk blades system considering the influence of shaft bending vibration［J］. Mechanical Systems and Signal Processing， 2018， 111： 545-569.
20	MA H， YIN F L， WU Z Y， et al. Nonlinear vibration response analysis of a rotor-blade system with blade-tip rubbing［J］. Nonlinear Dynamics， 2016， 84（3）： 1225-1258.
21	YANG T R， MA H， QIN Z Y， et al. Coupling vibration characteristics of the shaft-disk-drum rotor system with bolted joints［J］. Mechanical Systems and Signal Processing， 2022， 169： 108747.
22	吴志渊，闫寒，吴林潮，等. 旋转裂纹叶片-弹性轮盘耦合系统振动特性［J］. 航空学报， 2022， 43（9）： 625442.
	WU Z Y， YAN H， WU L C， et al. Vibration characteristics of rotating cracked-blade-flexible-disk coupling system［J］. Acta Aeronautica et Astronautica Sinica， 2022， 43（9）： 625442 （in Chinese）.
23	ZHAO S N， ZHANG X N， ZHANG S G， et al. A unified modeling approach for rotating flexible shaft-disk systems with general boundary and coupling conditions［J］. International Journal of Mechanical Sciences， 2022， 218： 107073.
24	WU Z Y， YAN H， ZHAO L C， et al. Axial-bending coupling vibration characteristics of a rotating blade with breathing crack［J］. Mechanical Systems and Signal Processing， 2023， 182： 109547.
25	DADO M H F， ABUZEID O. Coupled transverse and axial vibratory behaviour of cracked beam with end mass and rotary inertia［J］. Journal of Sound and Vibration， 2003， 261（4）： 675-696.
26	WU M C， HUANG S C. On the vibration of a cracked rotating blade［J］. Shock and Vibration， 1998， 5（5-6）： 317-323.
27	HOU Y H， CAO S Q， KANG Y H， et al. Dynamics analysis of bending–torsional coupling characteristic frequencies in dual-rotor systems［J］. AIAA Journal， 2022， 60（10）： 6020-6035.
28	MOHAMED M E， BONELLO P. The efficient inclusion of rotation-induced inertia effects in a shaft-blisk assembly model using zero-speed modes［J］. Journal of Sound and Vibration， 2020， 479： 115357.
29	WU Z Y， YAN H， ZHAO L C， et al. Influences of blade crack on the coupling characteristics in a bladed disk with elastic support［J］. Aerospace Science and Technology， 2023， 133： 108135.
30	SHE H X， LI C F. Analytical interpretation and numerical simulation on the dynamic coupling of a flexible cyclic blades-disk-shaft system［J］. Applied Mathematical Modelling， 2022， 112： 726-748.
31	CHEN S Y， YANG Y M， HU H F， et al. Blind interpolation for multi-frequency blade tip timing signals［J］. Mechanical Systems and Signal Processing， 2022， 172： 108946.

阶次	固有频率/Hz				误差1/%	误差2/%	误差3/%	振型描述
阶次	本文方法	有限元模型	文献［18］方法	文献［18］试验	误差1/%	误差2/%	误差3/%	振型描述
1	117.43	117.38	117.40		0.04	0.03		扭转模态
2	132.89	132.92	132.90	129.30	-0.02	-0.01	2.78	俯仰模态
3	132.89	132.92	132.90	129.30	-0.02	-0.01	2.78	与第2阶模态正交
4	265.20	264.55	269.60	258.00	0.25	-1.63	2.79	轮盘的摆动模态
5	265.20	264.55	269.60	258.00	0.25	-1.63	2.79	与第4阶模态正交
6	364.58	373.02	364.70	361.30	-2.26	-0.03	0.91	叶片弯曲主导模态
7	365.27	373.72	365.40	364.70	-2.26	-0.04	0.16	叶片弯曲主导模态
8	365.27	373.72	365.40	368.00	-2.26	-0.04	-0.74	与第7阶模态正交
9	370.59	379.14	370.70	372.00	-2.26	-0.03	-0.38	叶片弯曲主导模态
10	1 037.87	1 030.70	1 026.90		0.70	1.07		靠近轴承1的轴段弯曲
11	1 037.87	1 030.70	1 026.90		0.70	1.07		与第10阶模态正交
12	1 856.89	1 824.80	1 839.10		1.76	0.97		靠近轴承2的轴段弯曲
13	1 856.89	1 824.80	1 839.10		1.76	0.97		与第12阶模态正交

阶次	本文方法/Hz	有限元模型/Hz	误差/%
1	117.42	117.38	0.03
2	132.89	132.92	-0.02
3	132.89	132.92	-0.02
4	265.20	264.55	0.25
5	265.20	264.55	0.25
6	（358.02）	（368.38）	-2.81
7	（364.83）	（373.27）	-2.26
8	365.27	373.72	-2.26
9	（369.72）	（378.37）	-2.29
10	1 037.87	1 030.70	0.70
11	1 037.87	1 030.70	0.70
12	1 856.89	1 824.80	1.76
13	1 856.89	1 824.80	1.76

[1]	ZHANG Zhe, WANG Hanping, JIN Wendong, ZHANG Baozhen, CHENG Mengwen. Fast analysis method of deflection efficiency for thrust axial-symmetric vectoring exhaust nozzle [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 224429-224429.
[2]	WANG Kelei, ZHOU Zhou, ZHU Xiaoping, GUO Jiahao, FAN Zhongyun. Reconstruction design of propeller induced flow-field based on aerodynamic loading distributions [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(1): 123118-123118.
[3]	WANG Liangquan, XU Guohua, SHI Yongjie, XIA Runze. Influence of higher harmonic control on airload and acoustics of rotor blade-vortex interaction [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(7): 520847-520847.
[4]	TAN Jianfeng. Influence of helicopter rotor on tail rotor unsteady aerodynamic loads [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3228-3240.
[5]	LIU Zhou, YANG Yunjun, ZHOU Weijiang, GONG Anlong. Study of Unsteady Separation Flow Around Airfoil at High Angle of Attack Using Hybrid RANS-LES Method [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(2): 372-380.
[6]	Song Xizhen;Zhou Sheng;Li Qiushi. Way of Improving Aerodynamic Load Coefficient of Transonic Axial Fan Rotor [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2009, 30(1): 12-20.
[7]	DENG Li-dong;LI Tian;XUE Xiao-chun. CALCULATION METHOD ABOUT NONLINEAR FLIGHT LOADS OF AIRCRAFT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2002, 23(4): 317-320.
[8]	Li Zhaoguang. A STUDY ON FLIGHT LOADS FOR UNSYMMETRICAL POWER MANEUVER [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 41-45.
[9]	Hu Changrong. THE OPTIMIZATION OF LOAD EQUATION DURING AIRCRAFT FLIGHT LOAD MEASUREMNT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 102-105.
[10]	Sun Jianhua;Qu Shihong. ASTUDY ON FLIGHT LOAD ESTIMATION OF AIRCRAFT STRUCTURAL COMPONENTS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 106-108.
[11]	SunJianhua;QuShihong. A STUDY ON A PARAMETRIC IDENTIFICATION METHOD OF FLIGHT LOAD [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 109-112.
[12]	Hu Changrong. THE OPTIMIZATION OF LOAD EQUATION DURING AIRCRAFT FLIGHT LOAD MEASUREMNT [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 102-105.
[13]	Sun Jianhua;Qu Shihong. ASTUDY ON FLIGHT LOAD ESTIMATION OF AIRCRAFT STRUCTURAL COMPONENTS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 106-108.
[14]	SunJianhua;QuShihong. A STUDY ON A PARAMETRIC IDENTIFICATION METHOD OF FLIGHT LOAD [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 1(1): 109-112.
[15]	Wang Zhongyan. THE INFLUENCE OF AIRPLANE CONTROL SYSTEM PROPERTIES ON THE MANEUVER LOADS [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1994, 15(1): 27-31.

Vibration characteristics of blade tip in a shaft⁃disk⁃cracked⁃blade coupling system

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 19

References 31

Related Articles 15

Recommended Articles

Metrics

Comments