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ANALYSIS OF THE EFFECT OF MULTI-ROW AND MULTI-PASSAGE AERODYNAMIC INTERACTION ON THE FORCED RESPONSE VARIATION IN A COMPRESSOR CONFIGURATION - PART 2: EFFECTS OF ADDITIONAL STRUCTURAL MISTUNING

[+] Author and Article Information
Johann Gross

Institute of Aircraft Propulsion Systems, University of Stuttgart, Stuttgart, Germany
johann.gross@ila.uni-stuttgart.de

Malte Krack

Institute of Aircraft Propulsion Systems, University of Stuttgart, Stuttgart, Germany
malte.krack@ila.uni-stuttgart.de

Harald Schoenenborn

MTU Aero Engines AG, Munich, Germany
harald.schoenenborn@mtu.de

1Corresponding author.

ASME doi:10.1115/1.4038869 History: Received August 21, 2017; Revised November 06, 2017

Abstract

The prediction of aerodynamic blade forcing is a very important topic in turbomachinery design. Usually, the wake from the upstream blade row and the potential field from the downstream blade row are considered as the main causes for excitation, give rise to dynamic forcing of the blades. In addition, so-called Tyler-Sofrin modes, which refer to the acoustic interaction with blade rows further up- or downstream, may have a significant impact on blade forcing. In particular, they lead to considerable blade-to-blade variations of the aerodynamic loading. In part 1 a study of these effects is performed on the basis of a quasi 3D compressor configuration.

Part 2 of the paper proposes a method to analyze the interaction of the aerodynamic forcing asymmetries with the already well-studied effects of random mistuning stemming from blade-to-blade variations of structural properties. Based on a finite element model of a sector, the equations governing the dynamic behavior of the entire bladed disk can be efficiently derived using substructuring techniques. The disk substructure is assumed as cyclically symmetric, while the blades exhibit structural mistuning and linear aeroelastic coupling. In order to avoid the costly multi-stage analysis, the variation of the aerodynamic loading is treated as an epistemic uncertainty, leading to a stochastic description of the annular force pattern. The effects of structural mistuning and stochastic aerodynamic forcing are first studied separately and then in a combined manner for a blisk of a research compressor without and with aeroelastic coupling.

Copyright (c) 2017 by ASME
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