Research Papers

Analysis of the Effect of Multirow and Multipassage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration—Part II: Effects of Additional Structural Mistuning

[+] Author and Article Information
Johann Gross

Institute of Aircraft Propulsion Systems,
University of Stuttgart,
Stuttgart 70174, Germany
e-mail: johann.gross@ila.uni-stuttgart.de

Malte Krack

Institute of Aircraft Propulsion Systems,
University of Stuttgart,
Stuttgart 70174, Germany
e-mail: malte.krack@ila.uni-stuttgart.de

Harald Schoenenborn

MTU Aero Engines AG Munich,
Munich 80995, Germany
e-mail: Harald.Schoenenborn@mtu.de

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 21, 2017; final manuscript received November 6, 2017; published online February 28, 2018. Editor: Kenneth C. Hall.

J. Turbomach 140(5), 051005 (Feb 28, 2018) (9 pages) Paper No: TURBO-17-1127; doi: 10.1115/1.4038869 History: Received August 21, 2017; Revised November 06, 2017

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, which in conjunction with relative rotation of neighboring blade rows, give rise to dynamic forcing of the blades. In addition to those two mechanisms, the so-called Tyler–Sofrin (or scattered or spinning) 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 I of the paper, a study of these effects is performed on the basis of a quasi-three-dimensional multirow and multipassage compressor configuration. Part II 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 (FE) 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 multistage 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 © 2018 by ASME
Topics: Excitation , Blades , Disks
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Fig. 3

Upper subfigure: dispersion diagram of rotor 2; lower subfigure: zoom into mode F1

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Fig. 2

Finite element model rotor 2

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Fig. 1

Variation of excitation force rotor 2

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Fig. 4

Aerodynamic influence coefficients

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Fig. 5

Comparison of parent FE model versus ROM for FRF @ EO5

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Fig. 7

Amplification factor excitation mistuning: (a) no aerocoupling and (b) with aerocoupling

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Fig. 6

Amplification factor FM: (a) no aerocoupling and (b) with aerocoupling

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Fig. 8

Comparison of AFs @ STD = 10% and 50% EM and varying FM

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Fig. 9

Amplification factor FM @ 50% excitation mistuning: (a) no aerocoupling and (b) with aerocoupling

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Fig. 10

Amplification factor of EM @ 2% STD FM: (a) no aerocoupling and (b) with aerocoupling

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Fig. 11

Sections @2% FM without aerodynamic coupling

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Fig. 12

Mistuning pattern 469—maximum

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Fig. 13

Mistuning pattern 421—minimum

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Fig. 14

Amplification factor excitation mistuning for maximum and minimum pattern




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