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Research Papers: Gas Turbines: Structures and Dynamics

Traveling Wave Excitation: A Method to Produce Consistent Experimental Results

[+] Author and Article Information
Geofrey S. Cox

Major, United States Air Force
Department of Aeronautics and Astronautics,
Air Force Institute of Technology,
Wright-Patterson AFB, OH 45433
e-mail: geofrey.cox@afit.edu

Anthony N. Palazotto

Distinguished Professor
of Aeronautical Engineering
Department of Aeronautics and Astronautics,
Air Force Institute of Technology,
Wright-Patterson AFB, OH 45433
e-mail: anthony.palazotto@afit.edu

Jeffrey M. Brown

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

Tommy J. George

Engine Integrity,
Turbine Engine Division,
Air Force Research Laboratory,
Wright-Patterson AFB, OH 45433
e-mail: tommy.george@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 April 19, 2014; final manuscript received May 4, 2014; published online June 27, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(12), 122502 (Jun 27, 2014) (8 pages) Paper No: GTP-14-1203; doi: 10.1115/1.4027744 History: Received April 19, 2014; Revised May 04, 2014

This paper describes the experimental framework to establish consistent, repeatable results associated with a traveling wave excitation system. The experiment is employed to ascertain the forced response and mistuning patterns for rotors. Several items attributing to existing experimental inconsistencies were identified and their effects were realized during this research. These experimental items were signal input locations, response measurement locations, and rotor alignment position. Accounting for these experimental variables, this paper develops a process which enables consistent rotor forced response results, independent of its orientation on the test stand.

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References

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Figures

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Fig. 1

Zero engine order excitation

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Fig. 2

One engine order excitation

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Fig. 3

Rotor mounting configuration

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Fig. 4

Typical blade actuator and laser locations

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Fig. 5

Rotor actuator ring

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Fig. 6

Actuator ring center

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Fig. 7

Rotor scan point variables

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Fig. 8

Natural frequency response magnitude plots for the initial and repositioned rotor

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Fig. 9

CDF versus response magnitude for the initial and second rotor positions

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Fig. 10

New techniques: natural frequency response magnitude plots for the initial and repositioned rotor

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Fig. 11

CDF versus response magnitude for the initial and second rotor positions using the new techniques

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