HAL: hal-00243153, version 1

DOI: 10.1115/1.2747641

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Journal of Engineering for Gas Turbines and Power 129, 4 (2007) 1058-1064

Dynamics of Multistage Bladed Disks Systems

Denis Laxalde 1, 2, Jean-Pierre Lombard 2, Fabrice Thouverez 1

(2007-10)

This paper presents a new and original method for dynamical analysis of multistage cyclic structures such as turbomachinery compressors or turbines. Each stage is modeled cyclically by its elementary sector and the interstage coupling is achieved through a cyclic recombination of the interface degrees of freedom. This method is quite simple to set up; it allows us to handle the finite element models of each stage's sector directly and, as in classical cyclic symmetry analysis, to study the nodal diameter problems separately. The method is first validated on a simple case study which shows good agreements with a complete 360 deg reference calculation. An industrial example involving two HP compressor stages is then presented. Then the forced response application is presented in which synchronous engine order type excitations are considered.

1:	Laboratoire de Tribologie et Dynamique des Systèmes (LTDS)
	CNRS : UMR5513 – Ecole Centrale de Lyon – Ecole Nationale d'Ingénieurs de Saint Etienne
2:	SNECMA Siège [Courcouronnes]
	Safran Group

Subject

:

Physics/Mechanics/Vibrations Engineering Sciences/Mechanics/Vibrations Engineering Sciences/Mechanics/Mechanics of the structures Physics/Mechanics/Mechanics of the structures

Keyword(s): discs (structures) – blade – finite element analysis – multi-stage – cyclic symmetry – vibration – compressors – gas turbines

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From: Denis Laxalde <>

Submitted on: Monday, 16 March 2009 18:14:29

Updated on: Monday, 16 March 2009 18:16:55