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Research Papers: Gas Turbines: Structures and Dynamics

Mistuned Response Prediction of Dual Flow-Path Integrally Bladed Rotors With Geometric Mistuning

[+] Author and Article Information
Joseph A. Beck

Manufacturing and
Industrial Technologies Division,
Air Force Research Laboratory,
Wright-Patterson AFB, OH 45433
e-mail: Joseph.Beck.8@us.af.mil

Jeffrey M. Brown

Turbine Engine Division,
Air Force Research Laboratory,
Aerospace Systems Directorate,
Wright-Patterson AFB, OH 45433
e-mail: Jeffrey.Brown.70@us.af.mil

Alexander A. Kaszynski

Aerospace Engineer,
Turbine Engine Division,
Air Force Research Laboratory,
Aerospace Systems Directorate,
Wright-Patterson AFB, OH 45433
e-mail: Alex.Kaszynski.ctr@us.af.mil

Joseph C. Slater

Professor
Department of Mechanical
and Materials Engineering,
Wright State University, OH 45435
e-mail: Joseph.Slater@wright.edu

Charles J. Cross

Chief
Turbine Engine Division,
Air Force Research Laboratory,
Aerospace Systems Directorate,
Wright-Patterson AFB, OH 45433
e-mail: Charles.Cross.1@wpafb.af.mil

1Corresponding author.

Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received January 24, 2013; final manuscript received June 28, 2014; published online December 9, 2014. Assoc. Editor: Patrick S. Keogh.

This material is declared a work of the US Government and is not subject to copyright protection in the United States. Approved for public release; distribution is unlimited.

J. Eng. Gas Turbines Power 137(6), 062501 (Jun 01, 2015) (9 pages) Paper No: GTP-13-1023; doi: 10.1115/1.4028795 History: Received January 24, 2013; Revised June 28, 2014; Online December 09, 2014

The geometric mistuning problem is investigated for dual flow-path integrally bladed rotors (DFIBRs) by outlining two methods that explicitly account for blade geometry surface deviations. The methods result in reduced-order models (ROMs) that are a reduced form of a parent Craig–Bampton component mode synthesis (CB-CMS) model. This is accomplished by performing a secondary modal analysis on different degrees of freedom (DOF) of the parent model. The DFIBR is formulated in cyclic symmetry coordinates with a tuned disk and ring and blades with small geometric deviations. The first method performs an eigen-analysis on the constraint DOF that provides a truncated set of interface modes, while the second method includes the disk and ring fixed interface normal mode in the eigen-analysis to yield a truncated set of ancillary modes. Utilization of tuned modes have the benefit of being solved in cyclic symmetry coordinates and only need to be calculated once, which offers significant computational savings for subsequent mistuning studies. Each geometric mistuning method relies upon the use of geometrically mistuned blade modes in the component mode framework to provide an accurate ROM. Forced response results are compared to both the full finite element model (FEM) solutions and a traditional frequency-based approach outlined in a previous effort. It is shown that the models provide highly accurate results with a significant reduction in solution time compared to the full FEM and parent ROM.

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References

Beck, J. A., Slater, J. C., Brown, J. M., Scott-Emuakpor, O. E., and Cross, C. J., 2014, “Dynamic Response Characteristics of Dual Flow-Path Integrally Bladed Rotors,” 52nd Aerospace Sciences Meeting, National Harbor, MD, Jan. 13–17, AIAA Paper No. 2014-0098, pp. 1131–1146. [CrossRef]
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Figures

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Fig. 1

Dual flow-path integrally bladed rotor consists of an inner IBR and an integral outer ring with a second set of blades

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Fig. 2

Partitioned IBR index notation used in the mathematical formulation

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Fig. 3

The ND plot of the DFIBR illustrating the tuned system natural frequencies versus the harmonic index

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Fig. 4

Tuned DFIBR system modes in the frequency range of interest at harmonic index h = 0: (a) system mode 98, (b) system mode 110, and (c) system mode 122

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Fig. 5

MPFs for the EO excitations IC = OC = 0 over an excitation frequency range of 1450–1750 Hz

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Fig. 6

Comparison of predicted mistuned mode 109 against the full FEM solution: (a) inner-blades and (b) outer-blades

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Fig. 7

CCN and CMS blade-to-blade forced response predictions for the mistuned DFIBR compared against full FEM solutions: (a) forced response and (b) blade-to-blade error

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Fig. 8

Interface (CC) and ancillary (CA) reduced ROMs' blade-to-blade forced response predictions for the mistuned DFIBR compared against full FEM solutions: (a) CCT and CCM and (b) CAT and CAM

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Fig. 9

Interface (CC) and ancillary (CA) reduced ROMs' blade-to-blade forced response prediction error for the mistuned DFIBR compared against full FEM solutions

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Fig. 10

ROM peak DFIBR forced response predictions of the inner-blades as compared to the full FEM solution: (a) CMS and CCN and (b) CC- and CA-methods

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