The Effects of Bearing Misalignment on the Non-Linear Vibration of Aero-Engine Rotor–Damper Assemblies

This paper presents experimental results on the non-linear vibration response of a rotating assembly comprising a rotor, flexible bearing housing and oil film damper. For the latter, due consideration is given to the effects of oil-supply pressure, film-rupture pressure and end sealing. The results are compared with predictions based on the Harmonic Balance principle described in a complementary paper (1).

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The Efficient Computation of the Vibration Response of an Aero-Engine Rotor-Damper Assembly

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/pime_proc_1994_208_251_02 ◽

1994 ◽

Vol 208 (1) ◽

pp. 41-51 ◽

Cited By ~ 8

Author(s):

M C Levesley ◽

R Holmes

Keyword(s):

Harmonic Balance ◽

Harmonic Balance Method ◽

Vibration Response ◽

Efficient Computation ◽

Linear Vibration ◽

Film Rupture ◽

Aero Engine ◽

Rupture Pressure ◽

The Subject ◽

Engine Rotor

This paper deals with the application of the so-called Harmonic Balance method to the problem of determining the non-linear vibration response of a rotating assembly comprising a rotor, flexible bearing housing and oil film damper. For the latter, due consideration is given to the effects of oil supply pressure, film rupture pressure and end sealing. The paper concludes with some comments on the subject of optimizing a damper to fulfil a given purpose.

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Non-Linear Phenomena in Aero-Engine Rotor Vibration

Proceedings of the Institution of Mechanical Engineers Part A Journal of Power Engineering ◽

10.1243/pime_proc_1989_203_004_02 ◽

1989 ◽

Vol 203 (1) ◽

pp. 25-34 ◽

Cited By ~ 9

Author(s):

R Holmes ◽

M M Dede

Keyword(s):

Frequency Response ◽

Test Facility ◽

Medium Size ◽

Rotor Vibration ◽

Jet Engine ◽

Aero Engine ◽

Non Linear ◽

Rotor Assembly ◽

Twin Rotor ◽

Engine Rotor

This paper describes a test facility which reproduces the essential features of a twin-rotor assembly for a medium-size jet engine. Its purpose is to investigate phenomena experienced in an actual engine, which relate to system non-linearities. These phenomena include subharmonics, combination oscillations and jumps in frequency response. All such phenomena manifested themselves in the test facility and explanations are given as to their cause and possible elimination.

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Non-Linear Vibration Problems Treated by the Averaging Method of W. Ritz. Part 2. Single Degree of Freedom Systems Single Term Approximations

10.21236/ada800270 ◽

1951 ◽

Cited By ~ 3

Author(s):

Karl Klotter

Keyword(s):

Averaging Method ◽

Degree Of Freedom ◽

Linear Vibration ◽

Single Degree Of Freedom ◽

Single Degree ◽

Single Term ◽

Non Linear ◽

Vibration Problems

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An improved dynamic load-strength interference model for the reliability analysis of aero-engine rotor blade system

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410020972898 ◽

2020 ◽

pp. 095441002097289

Author(s):

Bingfeng Zhao ◽

Liyang Xie ◽

Yu Zhang ◽

Jungang Ren ◽

Xin Bai ◽

...

Keyword(s):

Reliability Analysis ◽

Dynamic Load ◽

Rotor Blade ◽

Engineering Application ◽

Weight Ratio ◽

System Component ◽

Aero Engine ◽

Blade System ◽

Improved Model ◽

Engine Rotor

As the power source of an aircraft, aero-engine tends to meet many rigorous requirements for high thrust-weight ratio and reliability with the continuous improvement of aero-engine performance. In this paper, based on the order statistics and stochastic process theory, an improved dynamic load-strength interference (LSI) model was proposed for the reliability analysis of aero-engine rotor blade system, with strength degradation and catastrophic failure involved. In presented model, the “unconventional active” characteristic of rotor blade system, changeable functioning relationships and system-component configurations, was fully considered, which is necessary for both theoretical analysis and engineering application. In addition, to reduce the computation cost, a simplified form of the improved LSI model was also built for convenience of engineering application. To verify the effectiveness of the improved model, reliability of turbojet 7 engine rotor blade system was calculated by the improved LSI model based on the results of static finite element analysis. Compared with the traditional LSI model, the result showed that there were significant differences between the calculation results of the two models, in which the improved model was more appropriate to the practical condition.

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