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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Tyler, J. M. , and Sofrin, T. G. , 1962, “ Axial Flow Compressor Noise Studies,” SAE Paper No. 620532.
Schoenenborn, H. , 2017, “Analysis of the Effect of Multi-Row and Multi-Passage Aerodynamic Interaction on the Forced Response Variation in a Compressor Configuration—Part 1: Aerodynamic Excitation,” ASME Paper No. GT2017-63018.
Schrape, S. , Giersch, T. , Nipkau, J. , Stapelfeldt, S. , and Mück, B. , 2015, “ Tyler-Sofrin Modes in Axial High Pressure Compressor Forced Response Analyses,” 14th International Symposium on Unsteady Aerodynamics, Aeroacoustics and Aeroelasticity of Turbomachines (ISUAAAT), Stockholm, Sweden, Sept., pp. S2–S3.
Castanier, M. , and Pierre, C. , 2006, “ Modeling and Analysis of Mistuned Bladed Disk Vibration: Status and Emerging Directions,” J. Propul. Power, 22(2), pp. 384–396. [CrossRef]
Salas, M. G. , Bladh, R. , Martensson, H. , Petrie-Repar, P. , Fransson, T. , and Vogt, M. , 2016, “Forced-Response Analysis of a Mistuned Compressor Blisk Comparing Three Different Reduced Order Model Approaches,” ASME Paper No. GT2016-57902.
Kahl, G. , 2002, “Aeroelastic Effects of Mistuning and Coupling in Turbomachinery Bladings,” Doctoral thesis, Universität Hannover, Hannover, Germany.
He, Z. , Epureanu, C. , and Pierre, C. , 2007, “ Fluid-Structural Coupling Effects on the Dynamics of Mistuned Bladed Disks,” AIAA J., 45(3), pp. 552–561. [CrossRef]
Bleeg, J. M. , Yang, M. , and Eley, J. A. , 2007, “Aeroelastic Analysis of Rotors With Flexible Disks and Alternate Blade Mistuning,” ASME Paper No. GT2007-27227.
Yang, G. H. , Wang, A. L. , and Cao, X. H. , 2012, “ A New Mistuning Form in Periodic Structure—Force Mistuning,” Adv. Mater. Res., 562–564, pp. 2092–2096. [CrossRef]
Schoenenborn, H. , Retze, U. , Ziller, G. , and Waniczek, P. , 2010, “Experimental and Analytical Mistuning Analysis of a Blisk at Lab Conditions and Under Rig Conditions Using Tip Timing,” ASME Paper No. GT2010-22447.
Ernst, M. , Michel, A. , and Jeschke, P. , 2009, “Analysis of Rotor-Stator-Interaction and Blade-to-Blade Measurements in a Two Stage Axial Flow Compressor,” ASME Paper No. GT2009-59371.
Carta, F. O. , 1967, “ Coupled Blade-Disk-Shroud Flutter Instabilities in Turbojet Engine,” ASME J. Eng. Power, 89(3), pp. 419–426. [CrossRef]
May, M. , Mauffrey, Y. , and Sicot, F. , 2011, “ Numerical Flutter Analysis of Turbomachinery Bladings Based on Time-Linearized, Time-Spectral and Time-Accurate Simulations,” 15th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2011), Paris, France, June 27–30.
Bladh, R. , Castanier, M. P. , and Pierre, C. , 2001, “ Component-Mode-Based Reduced Order Modeling Techniques for Mistuned Bladed Disks—Part I: Theoretical Models,” ASME J. Eng. Gas Turbines Power, 123(1), pp. 89–99. [CrossRef]
Craig, R. R. , and Bampton, M. C. C. , 1968, “ Coupling of Substructures for Dynamics Analyses,” AIAA J., 6(7), pp. 1313–1319. [CrossRef]
de Klerk, D. , Rixen, D. J. , and Voormeeren, S. N. , 2008, “ General Framework for Dynamic Substructuring: History, Review and Classification of Techniques,” AIAA J., 46(5), pp. 1169–1181. [CrossRef]
Castanier, M. , Tan, Y. , and Pierre, C. , 2001, “ Characteristic Constraint Modes for Component Mode Synthesis,” AIAA J., 39(6), pp. 1182–1187. [CrossRef]
Geradin, M. , and Rixen, D. J. , 2015, Mechanical Vibrations—Theory and Application to Structural Dynamics, 3rd ed., Wiley, London.
Castanier, M. P. , and Pierre, C. , 1997, “ Consideration on the Benefits of Intentional Blade Mistuning for the Forced Response of Turbomachinery Rotors,” Analysis and Design Issues for Modern Aerospace Vehicles, Vol. AD-55, G. J. Simitses , ed., American Society of Mechanical Engineers, New York, pp. 419–425.
Bladh, R. , Pierre, C. , Castanier, M. P. , and Kruse, M. J. , 2002, “ Dynamic Response Predictions for a Mistuned Industrial Turbomachinery Rotor Using Reduced-Order Modeling,” ASME J. Eng. Gas Turbines Power, 124(2), pp. 311–324. [CrossRef]
Choi, B.-K. , Lentz, J. , Rivas-Guerra, A. J. , and Mignolet, M. P. , 2003, “ Optimization of Intentional Mistuning Patterns for the Reduction of the Forced Response Effects of Unintentional Mistuning: Formulation and Assessment,” ASME J. Eng. Gas Turbines Power, 125(1), pp. 131–140. [CrossRef]
Whitehead, D. S. , 1966, “ Effect of Mistuning on the Vibration of Turbomachine Blades Induced by Wakes,” J. Mech. Eng. Sci., 8(1), pp. 15–21. [CrossRef]
Crawley, E. F. , and Hall, K. C. , 1985, “ Optimization and Mechanisms of Mistuning in Cascades,” ASME J. Eng. Gas Turbines Power, 107(2), pp. 418–426. [CrossRef]
Kaza, K. , and Kielb, R. E. , 1982, “ Flutter and Response of a Mistuned Cascade in Incompressible Flow,” AIAA J., 20(8), pp. 1120–1127. [CrossRef]
Kielb, R. E. , Griffin, J. H. , Feiner, D. M. , and Miyakozawa, T. , 2004, “Flutter of Mistuned Bladed Disks and Blisks With Aerodynamic and FMM Structural Coupling,” ASME Paper No. GT2004-54315.
Ottarsson, G. , and Pierre, C. , 1995, “ On the Effects of Interblade Coupling on the Statistics of Maximum Forced Response Amplitudes in Mistuned Bladed Disks,” AIAA Paper No. AIAA-1995-1494-CP.
Wei, S.-T. , and Pierre, C. , 1990, “ Statistical Analysis of the Forced Response of Mistuned Cyclic Assemblies” AIAA J., 28(5), pp. 861–868. [CrossRef]


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Fig. 1

Variation of excitation force rotor 2

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Fig. 2

Finite element model rotor 2

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Fig. 3

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

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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. 6

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

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Fig. 7

Amplification factor excitation mistuning: (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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