Research Papers: Gas Turbines: Controls, Diagnostics, and Instrumentation

Active Piezoelectric Vibration Control of Subscale Composite Fan Blades

[+] Author and Article Information
Kirsten P. Duffy

University of Toledo,
Cleveland, OH 44135
e-mail: Kirsten.P.Duffy@nasa.gov

Benjamin B. Choi

e-mail: Benjamin.B.Choi@nasa.gov

Andrew J. Provenza

e-mail: Andrew.J.Provenza@nasa.gov

James B. Min

e-mail: James.B.Min@nasa.gov
NASA Glenn Research Center,
Cleveland, OH 45069

Nicholas Kray

GE Aviation,
Cincinnati, OH 45069
e-mail: Nick.Kray@ge.com

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 16, 2012; final manuscript received September 12, 2012; published online November 21, 2012. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(1), 011601 (Nov 21, 2012) (7 pages) Paper No: GTP-12-1281; doi: 10.1115/1.4007720 History: Received July 16, 2012; Revised September 12, 2012

As part of the Fundamental Aeronautics program, researchers at NASA Glenn Research Center (GRC) are investigating new technologies supporting the development of lighter, quieter, and more efficient fans for turbomachinery applications. High performance fan blades designed to achieve such goals will be subjected to higher levels of aerodynamic excitations which could lead to more serious and complex vibration problems. Piezoelectric materials have been proposed as a means of decreasing engine blade vibration either through a passive damping scheme, or as part of an active vibration control system. For polymer matrix fiber composite blades, the piezoelectric elements could be embedded within the blade material, protecting the brittle piezoceramic material from the airflow and from debris. To investigate this idea, spin testing was performed on two General Electric Aviation (GE) subscale composite fan blades in the NASA GRC Dynamic Spin Rig Facility. The first bending mode (1B) was targeted for vibration control. Because these subscale blades are very thin, the piezoelectric material was surface-mounted on the blades. Three thin piezoelectric patches were applied to each blade—two actuator patches and one small sensor patch. These flexible macro-fiber-composite patches were placed in a location of high resonant strain for the 1B mode. The blades were tested up to 5000 rpm, with patches used as sensors, as excitation for the blade, and as part of open- and closed-loop vibration control. Results show that with a single actuator patch, active vibration control causes the damping ratio to increase from a baseline of 0.3% critical damping to about 1.0% damping at 0 rpm. As the rotor speed approaches 5000 rpm, the actively controlled blade damping ratio decreases to about 0.5% damping. This occurs primarily because of centrifugal blade stiffening, and can be observed by the decrease in the generalized electromechanical coupling with rotor speed.

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Fig. 1

1B mode—modal displacement and strain

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Fig. 2

B mode—modal displacement and strain

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Fig. 3

Sensor and actuator locations

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Fig. 4

Blades with piezoelectric patches

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Fig. 5

Blades in dynamic spin rig facility

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Fig. 6

Off resonance magnetic bearing excitation

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Fig. 7

First bending resonance peaks

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Fig. 8

1B resonance frequency and damping (open circuit, low excitation)

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Fig. 9

1B generalized electromechanical coupling K (low excitation)

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Fig. 10

1B peak resonant sensor strain (open circuit)

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Fig. 11

1B normalized peak resonant sensor strain (open circuit) compared to normalized K

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Fig. 12

1B peak resonant sensor strain with piezoelectric excitation

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Fig. 13

1B normalized peak resonant sensor strain with piezoelectric excitation, compared to normalized K

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Fig. 14

1B peak resonant sensor strain with open loop control at 0 rpm

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Fig. 15

Damping factor for baseline open circuit and actively controlled blades (low excitation)

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Fig. 16

Comparison of average normalized Δζ with normalized K2 (low excitation)

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Fig. 17

Peak resonant sensor strain for baseline open circuit and actively controlled blades

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Fig. 18

Peak resonant sensor strain at 3000 rpm for open circuit and actively controlled blades



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