Investigation of a Rotor Bearing Assembly Incorporating a Squeeze-Film Damper Bearing

Holmes, R.; Dogan, M.

doi:10.1243/jmes_jour_1982_024_026_02

Cited by 23 publications

(8 citation statements)

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“…For such unsupported SFDs, the size, shape and mean position (within the clearance) of the calculated journal orbit are particularly sensitive to the assumed value of the oil-film rupture pressure p c , which was constant at absolute zero in the predictions, as in reference [5]. In reference [9], the value of p c used to calculate the vibration was based on measurements of the dynamic pressure within the oil film and was found to vary with the operating conditions. Figure 7 shows the stable orbital motion at the dampers in the region of the first bounce critical speed for U 1 ¼ 0 kgm and U 2 ¼ 10:74610 À 4 kgm.…”

Section: Resultsmentioning

confidence: 99%

“…The calculation of Q xi and Q yi requires the numerical spatial integration of the instantaneous pressure distribution within SFD i as explained in references [5,6] and [9]. The pressure distribution used in this work was given by the short bearing solution to the Reynolds equation and was truncated at a minimum pressure of À 101:325610 3 Pa (gauge) (i.e.…”

Section: Analytical Modellingmentioning

confidence: 99%

“…In practice, a support structure (engine casing) will have some flexibility at the bearing housings, the degree of which depending on the application [8]. There are many gas turbine applications, such as military aeroengines [8,9], where this flexibility is such that the first two undamped critical speeds of the combined rotorsupport structure essentially define 'bounce modes'. In these modes the rotor does not bend to any significant degree while the housings show appreciable dynamic deflection.…”

Section: Introductionmentioning

confidence: 99%

“…x and y modal coordinates of the support structure, for mode number r (m kg 0.5 ) Q xi , Q yi Cartesian squeeze-film damper forces on J i (N) R bearing bore radius (m) R NN ðoÞ, R NU ðoÞ receptance matrices [equations ( 8)] R R PQ ðoÞ receptance matrix [equation (9)] t time (s)…”

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confidence: 99%

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The prediction of the non-linear dynamics of a squeeze-film damped aero-engine rotor housed in a flexible support structure

Bonello

Brennan

Holmes

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper shows how the non-linear dynamics of a rotor running in unsupported squeeze-film dampers (SFDs) housed in a flexible support structure can be efficiently modelled using an integrated analytical technique and a standard model for the SFDs. A test rig that reproduces, to a limited extent, the essential dynamic features of an aero-engine gas turbine is considered and the aim of the analysis is to assess the ability to predict and interpret the observed non-linear vibrations as indicated by amplitude-speed plots, frequency spectra, orbital motion plots and Poincare´maps. The solution process starts with the application of a fast harmonic balance method that uses receptance functions to determine periodic solutions. A modal-based approach is then used for the analysis of the stability and bifurcation of these solutions, as well as the analysis of aperiodic motion. The simulation correctly predicts the overall performance, including subharmonic motion, combination frequencies and subcritical superharmonic resonances.

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Section: Resultsmentioning

confidence: 99%

Section: Analytical Modellingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

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The prediction of the non-linear dynamics of a squeeze-film damped aero-engine rotor housed in a flexible support structure

Bonello

Brennan

Holmes

2004

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The use of the incompressible Reynolds equation means that the effects of compressibility due to air entrainment are not accounted for. Variable cavitation pressure is often observed in experiments [5,12], suggesting that air entrainment and therefore cavitation is dependent upon the bearing dynamics. Although attempts have been made to account for compressibility of the fluid film e.g.…”

Section: Introductionmentioning

confidence: 99%

An Investigation Into Two Alternative Approaches for the Identification of SFD Bearings for Aeroengine Analysis

Groves

Bonello

2011

Volume 6: Structures and Dynamics, Parts a and B

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Identification techniques provide a means of efficiently implementing complex nonlinear bearing models in practical turbomachinery applications. This paper considers both identification from an advanced numerical model and identification from experimental tests. Identification from numerical models is essential at the design stage, where rapid simulation of the dynamic performance of a variety of designs is required. Experimental identification is useful to capture effects that are difficult to model (e.g. geometric imperfections, compressibility and its effect on cavitation). With regard to identification from a numerical model, it was shown in a previous paper that the numerical solution of the incompressible Reynolds equation may be replicated using Chebyshev polynomial fits. Tests were performed on a simple rotor-bearing configuration incorporating an advanced numerical bearing model. The identified model was found to be able to match the accuracy of the numerical solution to the Reynolds equation while requiring a fraction of the computation time. In the present work the SFD identification scheme is applied to a realistically-sized representative wholeaeroengine model. It is shown that using recently introduced nonlinear solvers combined with the identified high accuracy bearing models it is possible to run full engine rotor-dynamic simulations, in both the time and frequency domains, at a fraction of the previous computational cost. One major drawback of the Chebyshev technique is that it is not amenable to experimental identification of actual bearings. For this reason, a second identification approach, involving the use of neural networks, is considered in this paper. A test rig that enables empirical identification of SFD forces has been constructed and details of the building and operation of the test rig is presented. The method used to ascertain the training data required by the neural network identification scheme, is also described. Downloaded From: http://proceedings.asmedigitalcollection.asme.org/ on 03/30/2015 Terms of Use: http://asme.org/terms y J J J J J y

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Classification of Orbits of Rotor Supported on Squeeze Film Damper by Supervised Learning Method

Kumar,

Tiwari,

Singh

2023

Mechanisms and Machine Science

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Investigation of a Rotor Bearing Assembly Incorporating a Squeeze-Film Damper Bearing

Cited by 23 publications

References 1 publication

The prediction of the non-linear dynamics of a squeeze-film damped aero-engine rotor housed in a flexible support structure

The prediction of the non-linear dynamics of a squeeze-film damped aero-engine rotor housed in a flexible support structure

An Investigation Into Two Alternative Approaches for the Identification of SFD Bearings for Aeroengine Analysis

Classification of Orbits of Rotor Supported on Squeeze Film Damper by Supervised Learning Method

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