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Research Papers

A New Reduced Order Modeling for Stability and Forced Response Analysis of Aero-Coupled Blades Considering Various Mode Families

[+] Author and Article Information
María A. Mayorca1

Damian M. Vogt, Torsten H. Fransson

 Royal Institute of Technology, Heat and Power Technology, S-100 44 Stockholm, Sweden

Hans Mårtensson

 VOLVO Aero Corporation, S-461 81 Trollhättan, Sweden

1

Corresponding author.

J. Turbomach 134(5), 051008 (May 08, 2012) (10 pages) doi:10.1115/1.4003830 History: Received November 16, 2010; Revised January 23, 2011; Published May 08, 2012; Online May 08, 2012

This paper presents the description and application of a new method for stability and forced response analyses of aerodynamically coupled blades considering the interaction of various mode families. The method, here referred as multimode least square, considers the unsteady forces due to the blade motion at different modes shape families and calculates the aerodynamic matrixes by means of a least square (L2 ) approximations. This approach permits the prediction of mode families’ interaction with capabilities of structural, aerodynamic and force mistuning. A projection technique is implemented in order to reduce the computational domain. Application of the method on tuned and structural mistuned forced response and stability analyses is presented on a highly loaded transonic compressor blade. When considering structural mistuning the forced response amplitude magnification is highly affected by the change in aerodynamic damping due to mistuning. Analyses of structural mistuning without aerodynamic coupling might result in over-estimated or under-estimated response when the source of damping is mainly aerodynamic. The frequency split due to mistuning can cause that mode families’ interact due to reducing their frequencies separation. The advantage of the present method is that the effect of mode family interaction on aerodynamic damping and forced response is captured not being restricted to single mode families.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Finite Element rotor blade mesh

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Figure 2

Investigated compressor stage

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Figure 3

Tuned stability comparison between lumped mass system (sdof) and the reduced MLS

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Figure 4

Tuned stability comparison between MLS considering only one mode modal forces and the three modes modal forces

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Figure 5

Tuned forced response at different nodal diameters; mode 2

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Figure 6

Tuned forced response at different nodal diameters; mode 3

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Figure 7

Stability analysis of the aerodynamically coupled system; tuned and mistuned; MLS

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Figure 8

Frequency response at different nodal diameter excitation patterns; peak amplitudes highlighted; mode 3; mistuned system; MLS

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Figure 9

Frequency response at different nodal diameter excitation patterns; peak amplitudes highlighted; mode 3; mistuned system; MLS

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Figure 10

Frequency response of different blades due to mistuning; modes 2 and 3; ND2B; MLS

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Figure 11

Amplitude magnification due to mistuning considering aerodynamic coupling; MLS; (a) mode 2 and (b) mode 3

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Figure 12

Amplitude change with aerodynamic damping; MLS

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Figure 13

Frequency response of different blades in close frequency spaced mode families due to mistuning increase; ND2B; MLS

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Figure 14

Absolute amplitude contours of the ±9% mistuned system; ND2B; interaction of mode families 2F and 1T

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