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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January 2013
Research-Article
Active Piezoelectric Vibration Control of Subscale Composite Fan Blades
Benjamin B. Choi,
Andrew J. Provenza,
Nicholas Kray
Nicholas Kray
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Kirsten P. Duffy
Benjamin B. Choi
e-mail: Benjamin.B.Choi@nasa.gov
Andrew J. Provenza
e-mail: Andrew.J.Provenza@nasa.gov
James B. Min
Nicholas Kray
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. Jan 2013, 135(1): 011601 (7 pages)
Published Online: November 21, 2012
Article history
Received:
July 16, 2012
Revision Received:
September 12, 2012
Citation
Duffy, K. P., Choi, B. B., Provenza, A. J., Min, J. B., and Kray, N. (November 21, 2012). "Active Piezoelectric Vibration Control of Subscale Composite Fan Blades." ASME. J. Eng. Gas Turbines Power. January 2013; 135(1): 011601. https://doi.org/10.1115/1.4007720
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