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Research Papers

Mistuned Higher-Order Mode Forced Response of an Embedded Compressor Rotor—Part II: Mistuned Forced Response Prediction

[+] Author and Article Information
Jing Li

Department of Mechanical Engineering
and Materials Science,
Duke University,
Durham, NC 27708
e-mail: jing.li3@ge.com

Nyansafo Aye-Addo

Department of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: payeaddo@purdue.edu

Robert Kielb

Professor
Department of Mechanical Engineering
and Materials Science,
Duke University,
Durham, NC 27708
e-mail: rkielb@duke.edu

Nicole Key

Professor
Department of Mechanical Engineering,
Purdue University,
500 Allison Road,
West Lafayette, IN 47907
e-mail: nkey@purdue.edu

1Corresponding author.

2Present address: GE Global Research Center, 1 Research Circle, Niskayuna, NY 12309.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received November 7, 2017; final manuscript received November 16, 2017; published online December 20, 2017. Editor: Kenneth Hall.

J. Turbomach 140(3), 031006 (Dec 20, 2017) (11 pages) Paper No: TURBO-17-1210; doi: 10.1115/1.4038519 History: Received November 07, 2017; Revised November 16, 2017

This paper is the second part of a two-part paper that presents a comprehensive study of the higher-order mode (HOM) mistuned forced response of an embedded rotor blisk in a multistage axial research compressor. The resonant response of the second-stage rotor (R2) in its first chordwise bending (1CWB) mode due to the second harmonic of the periodic passing of its neighboring stators (S1 and S2) is investigated computationally and experimentally at three steady loading conditions in the Purdue three-stage compressor research facility. A nonintrusive stress measurement system (NSMS, or blade tip-timing) is used to measure the blade vibration. Two reduced-order mistuning models of different levels of fidelity are used, namely, the fundamental mistuning model (FMM) and the component mode mistuning (CMM), to predict the response. Although several modes in the 1CWB modal family appear in frequency veering and high modal density regions, they do not heavily participate in the response such that very similar results are produced by the FMM and the CMM models of different sizes. A significant response amplification factor of 1.5–2.0 is both measured and predicted, which is on the same order of magnitude of what was commonly reported for low-frequency modes. In this study, a good agreement between predictions and measurements is achieved for the deterministic analysis. This is complemented by a sensitivity analysis which shows that the mistuned system is highly sensitive to the discrepancies in the experimentally determined blade frequency mistuning.

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References

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Figures

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Fig. 1

(a) Schematic of the P3S compressor flow path and blading, (b) R2 Campbell diagram, and (c) P3S compressor map

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Fig. 2

Six identified frequency mistuning patterns for PE

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Fig. 6

Predicted normalized aerodynamic modal forces representing change in stiffness (real part) and damping (imaginary part) of the system due to air

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Fig. 3

(a) Nominal blade frequency mistuning pattern and (b) its spatial harmonic contents

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Fig. 4

R2 frequency versus nodal diameter map (top) and zoom-in on the 1CWB modal family (bottom)

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Fig. 5

Distribution of frequency and fractional blade strain energy for the 1CWB family of modes

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Fig. 7

Predicted tuned and mistuned (by FMM and CMM) aeroelastic eigenvalues at PE

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Fig. 8

Predicted tuned and mistuned (by FMM) aeroelastic eigenvalues for LL, PE, and HL

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Fig. 9

Comparison between predicted and identified mistuned aeroelastic eigenvalues for LL, PE, and HL

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Fig. 13

Predicted (by FMM and CMM) and measured maximum and mean response curves at PE

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Fig. 14

Predicted mean and maximum response curves at PE using CMM models of different sizes

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Fig. 15

Predicted and measured tuned, mean, and maximum response curves for LL (top) and HL (bottom)

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Fig. 16

Predicted and measured individual blade maximum response amplitude distribution (normalized by the mean) for LL, PE, and HL

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Fig. 17

Predicted q¯mean/q¯tuned ratio as a function of (a) frequency mistuning percentage SD and (b) percentage SD divided by the structural coupling parameter, for 1T/44EO and 1CWB/88EO mistuned responses of the rotor blisk at PE

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Fig. 10

An example of mistuned forced response result

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Fig. 11

Predicted and measured (a) q¯tuned, (b) q¯N,avg, (c) q¯mean, and (d) q¯max amplitudes for LL, PE, and HL

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Fig. 12

Predicted and measured (a) q¯max/q¯mean, (b) q¯mean/q¯tuned, (c) q¯max/q¯tuned (amplification factor), and (d) q¯max/q¯N,avg ratios for LL, PE, and HL

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Fig. 18

Predicted and measured (a) q¯max/q¯mean, (b) q¯mean/q¯tuned, (c) q¯max/q¯tuned (amplification factor), and (d) q¯max/q¯N,avg ratios for LL, PE, and HL including results of the computational sensitivity analysis

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Fig. 19

Predicted and measured individual blade maximum response amplitude distributions at LL (top), PE (middle), and HL (bottom) including results of the computational sensitivity analysis

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