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Research Papers: Gas Turbines: Structures and Dynamics

Modified Modal Domain Analysis of a Bladed Rotor Using Coordinate Measurement Machine Data on Geometric Mistuning

[+] Author and Article Information
Vinod Vishwakarma

Department of Mechanical and
Nuclear Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: vinod.vish@gmail.com

Alok Sinha

Department of Mechanical and
Nuclear Engineering,
The Pennsylvania State University,
University Park, PA 16802
e-mail: axs22@psu.edu

Yasharth Bhartiya

ANSYS, Inc.,
Canonsburg, PA 15317
e-mail: yasharth@gmail.com

Jeffery M. Brown

Air Force Research Laboratory,
Wright-Patterson AFB, OH 45433
e-mail: jeffrey.brown.70@us.af.mil

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received May 13, 2014; final manuscript received June 17, 2014; published online November 11, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 137(4), 042502 (Apr 01, 2015) (8 pages) Paper No: GTP-14-1236; doi: 10.1115/1.4028615 History: Received May 13, 2014; Revised June 17, 2014; Online November 11, 2014

Modified modal domain analysis (MMDA), a reduced order modeling technique, is applied to a geometrically mistuned integrally bladed rotor to obtain its natural frequencies, mode shapes, and forced response. The geometric mistuning of blades is described in terms of proper orthogonal decomposition (POD) of the coordinate measurement machine (CMM) data. Results from MMDA are compared to those from the full (360 deg) rotor Ansys model. It is found that the MMDA can accurately predict natural frequencies, mode shapes, and forced response. The effects of the number of POD features and the number of tuned modes used as bases for model reduction are examined. Results from frequency mistuning approaches, fundamental mistuning model (FMM) and subset of nominal modes (SNM), are also generated and compared to those from full (360 deg) rotor Ansys model. It is clearly seen that FMM and SNM are unable to yield accurate results whereas MMDA yields highly accurate results.

Copyright © 2015 by ASME
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References

Figures

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Fig. 1

Singular values for integrally bladed rotor geometric mistuning

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Fig. 2

POD features for geometric mistuning of integrally bladed rotor

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Fig. 3

Nodal diameter map of rotor with each blade having “average” geometry

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Fig. 4

Frequency deviations from MMDA (3, 6, and 9 PODs)

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Fig. 5

Frequency deviations from MMDA (12, 15, and 17 PODs)

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Fig. 6

MAC for MMDA modes (0, 3, 6, and 9 PODs)

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Fig. 7

MAC for MMDA modes (12, 15, and 17 PODs)

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Fig. 8

Frequency deviation comparison (SNM and FMM))

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Fig. 9

MAC values for SNM modes (first and second families)

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Fig. 10

MAC values for FMM modes (first and second families)

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Fig. 11

Forced harmonic response comparison (family 1)

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Fig. 12

Forced harmonic response comparison (family 2)

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Fig. 13

Monte Carlo simulation with 500 permutations of blades (MMDA)

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Fig. 14

Monte Carlo simulation with 500 permutations of blades (SNM)

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Fig. 15

NPMA for each permutation of blades

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