Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping

Martel Escobar, Carlos and Sanchez Alvarez, Jose Joaquin (2017). Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping. "Journal of Sound and Vibration", v. 397 ; pp. 108-122. ISSN 0022-460X. https://doi.org/10.1016/j.jsv.2017.02.054.

Description

Title: Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping
Author/s:
  • Martel Escobar, Carlos
  • Sanchez Alvarez, Jose Joaquin
Item Type: Article
Título de Revista/Publicación: Journal of Sound and Vibration
Date: June 2017
Volume: 397
Subjects:
Freetext Keywords: Bladed-disk vibration; Forced response; Mistuning; Aerodynamic damping; Turbomachinery aeroelasticity
Faculty: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Department: Matemática Aplicada a la Ingeniería Aeroespacial
Creative Commons Licenses: Recognition - No derivative works - Non commercial

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Abstract

Mistuning can dangerously increase the vibration amplitude of the forced response of a turbomachinery rotor. In the case of damping coming from aerodynamic effects the situation is more complicated because the magnitude of the damping changes for the different travelling wave modes of the system. This damping variability modifies the effect of mistuning, and it can even result in a reduction of the mistuned forced response amplitude below that of the tuned case (this is not possible in the usual case of constant material damping). In this paper the Asymptotic Mistuning Model (AMM) methodology is used to analyze this situation. The AMM is a reduced order model that is systematically derived from the mistuned bladed disk full model using a perturbative procedure based on the small size of the mistuning and the damping. The AMM allows to derive a very simple expression for an upper bound of the maximum amplification factor of the vibration amplitude that the system can experience (an extension of the well known Whitehead 1966 result to include the effect of non-uniform aerodamping). This new upper bound gives information on the mechanisms involved in the amplification/reduction of the mistuned response: (i) the number of modes participating in the response, and (ii) the ratio between the aerodamping of the directly forced mode and that of the of the rest of the modes. A FEM of a mistuned bladed disk is also used to verify the AMM predictions for several different forcing configurations, and both results show a very good quantitative agreement.

Funding Projects

TypeCodeAcronymLeaderTitle
Government of SpainDPI2013-46403-RUnspecifiedUnspecifiedNuevas técnicas para el análisis de problemas de vibraciones aeromecánicas en turbinas de gas aeronáuticas
Universidad Politécnica de MadridGI1514120024UnspecifiedUnspecifiedUnspecified

More information

Item ID: 50097
DC Identifier: http://oa.upm.es/50097/
OAI Identifier: oai:oa.upm.es:50097
DOI: 10.1016/j.jsv.2017.02.054
Official URL: https://www.sciencedirect.com/science/article/pii/S0022460X17301992
Deposited by: Memoria Investigacion
Deposited on: 07 Feb 2019 13:35
Last Modified: 25 Mar 2019 14:02
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