A comparison of modal analyses of foil-air bearing rotor systems using two alternative linearisation methods. (1st May 2022)

• Record Type: Journal Article
• Authors: Bonello, Philip; Pourashraf, Talieh
• Is Part Of: Mechanical systems and signal processing. Volume 170(2022)
• Publication Date: 2022-05-01
• Subjects: Foil-air bearings -- Nonlinear analysis -- Linearisation -- Modal analysis -- Stability analysis; DOF Degrees-of-freedom -- EO Engine Order -- EPM Extended Perturbation Method -- FAB Foil-Air Bearing -- FLE/CTE Free Leading Edge/Clamped Trailing Edge -- LFCM Linear Force Coefficients Method -- MAC Modal Assurance Criterion -- OIS Onset of Instability Speed -- RE Reynolds Equation -- SEC Static Equilibrium Configuration -- SEFM Simple Elastic Foundation Model -- TNDA Transient Nonlinear Dynamic Analysis -- FD Finite Difference -- FE Finite Element; Structural dynamics -- Periodicals; Vibration -- Periodicals; Constructions -- Dynamique -- Périodiques; Vibration -- Périodiques; Structural dynamics; Vibration; Periodicals; 621
• DOI: 10.1016/j.ymssp.2021.108714
• Languages: English
• ISSNs: 0888-3270

Abstract

Highlights: A novel robust method is presented for stability and modal analysis using LFCM. Also applicable to advanced foil models e.g. which consider top foil detachment. First-ever verification of modal analysis by LFCM against direct linearisation. Results do not exhibit systematic error in LFCM as foil compliance increases. Two cases identified where LFCM free vibration analysis gives misleading results. Abstract: When applied to the free vibration (modal) analysis of foil-air bearing rotor systems, the classical linear force coefficients method (LFCM) can be regarded as an indirect form of linearisation that eliminates the air film and foil state variables. Research into its accuracy has been limited to its predictive ability for the instability onset speed compared against the low amplitude response of the nonlinear system. Two recent studies highlighted issues that artificially inflated the method discrepancies reported previously. This paper verifies the LFCM on a series of cases and identifies indisputable ones where it gives misleading results. A novel robust procedure is devised for the LFCM computation of Campbell diagrams and modal stability plots. A first-ever study of the accuracy of the LFCM's modal analysis capability is carried out using as benchmark the recently developed direct linearisation method. In contradiction to a recent study, the LFCM results did not exhibit a systematic error as the foil compliance increases, though it is not excluded that such an error may occur in other situations. The two cases identified where the LFCM gave misleading predictions relate to pad flutter with top foil detachment and half engine order whirl modes attributed to the air film.