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

Martel Escobar, Carlos y 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.

Descripción

Título: Maximum mistuning amplification of the forced response vibration of turbomachinery rotors in the presence of aerodynamic damping
Autor/es:
  • Martel Escobar, Carlos
  • Sanchez Alvarez, Jose Joaquin
Tipo de Documento: Artículo
Título de Revista/Publicación: Journal of Sound and Vibration
Fecha: Junio 2017
Volumen: 397
Materias:
Palabras Clave Informales: Bladed-disk vibration; Forced response; Mistuning; Aerodynamic damping; Turbomachinery aeroelasticity
Escuela: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Departamento: Matemática Aplicada a la Ingeniería Aeroespacial
Licencias Creative Commons: Reconocimiento - Sin obra derivada - No comercial

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Resumen

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.

Proyectos asociados

TipoCódigoAcrónimoResponsableTítulo
Gobierno de EspañaDPI2013-46403-RSin especificarSin especificarNuevas técnicas para el análisis de problemas de vibraciones aeromecánicas en turbinas de gas aeronáuticas

Más información

ID de Registro: 50097
Identificador DC: http://oa.upm.es/50097/
Identificador OAI: oai:oa.upm.es:50097
Identificador DOI: 10.1016/j.jsv.2017.02.054
URL Oficial: https://www.sciencedirect.com/science/article/pii/S0022460X17301992
Depositado por: Memoria Investigacion
Depositado el: 07 Feb 2019 13:35
Ultima Modificación: 07 Feb 2019 13:38
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