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Analysis of mistuned forced response in an axial high-pressure compressor rig with focus on Tyler–Sofrin modes

Published online by Cambridge University Press:  05 April 2019

F. Figaschewsky ,
A. Kühhorn ,
B. Beirow ,
T. Giersch  and
S. Schrape
F. Figaschewsky*
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
A. Kühhorn
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
B. Beirow
Affiliation:
Brandenburg University of Technology Cottbus–Senftenberg, Cottbus, Germany
T. Giersch
Affiliation:
Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany
S. Schrape
Affiliation:
Rolls-Royce Deutschland Ltd & Co KG, Blankenfelde-Mahlow, Germany
*
*felix.figaschewsky@b-tu.de
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Abstract

This paper aims at contributing to a better understanding of the effect of Tyler–Sofrin Modes (TSMs) on forced vibration responses by analysing a 4.5-stage research axial compressor rig. The first part starts with a brief review of the involved physical mechanisms and necessary prerequisites for the generation of TSMs in multistage engines. This review is supported by unsteady CFD simulations of a quasi 2D section of the studied engine. It is shown that the amplitude increasing effect due to mistuning can be further amplified by the presence of TSMs. Furthermore, the sensitivity with respect to the structural coupling of the blades and the damping as well as the shape of the expected envelope is analysed.

The second part deals with the Rotor 2 blisk of the research compressor rig. The resonance of a higher blade mode with the engine order of the upstream stator is studied in two different flow conditions realised by different variable stator vane (VSV) schedules which allows to separate the influence of TSMs from the impact of mistuning. A subset of nominal system modes representation of the rotor is used to describe its mistuned vibration behaviour, and unsteady CFD simulations are used to characterise the present strength of the TSMs in the particular operating conditions. Measured maximum amplitude vs blade pattern and frequency response functions are compared against the predictions of the aeromechanical models in order to assess the strength of the TSMs as well as its influence on vibration levels.

Keywords

MistuningForced responseTyler–Sofrin modes
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1261 , March 2019 , pp. 356 - 377
Copyright
© Royal Aeronautical Society 2019 

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