This paper describes an experimental investigation of the use of Gurney flaps to control laminar separation on turbine blades in a linear cascade. Measurements were made at Reynolds numbers (based upon inlet velocity and axial chord) of 28 × 103, 65 × 103 and 167 × 103. The freestream turbulence intensity for all three cases was 0.8%. Laminar separation was present on the suction surface of the Langston blade shape for the two lower Reynolds numbers. In an effort to control the laminar separation, Gurney flaps were added to the pressure surface close to the trailing edge. The measurements indicate that the flaps turn and accelerate the flow in the blade passage toward the suction surface of the neighboring blade thereby eliminating the separation bubble. Five different sizes of Gurney flaps, ranging from 0.6% to 2.7% of axial chord, were tested. The laser thermal tuft technique was used to determine the influence of the Gurney flaps on the location and size of the separation bubble. Additionally, measurements of wall static pressure, profile loss, and blade-exit flow angle were made. The blade pressure distribution indicates that the lift generated by the blade is increased. As was expected, the Gurney flap also produced a larger wake. In practice, Gurney flaps might possibly be implemented in a semi-passive manner. They could be deployed for low Reynolds number operation and then retracted at high Reynolds numbers when separation is not present. This work is important because it describes a successful means for eliminating the separation bubble while characterizing both the potential performance improvement and the penalties associated with this semi-passive flow control technique.
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ASME Turbo Expo 2002: Power for Land, Sea, and Air
June 3–6, 2002
Amsterdam, The Netherlands
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-3610-X
PROCEEDINGS PAPER
Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades
Aaron R. Byerley,
Aaron R. Byerley
U.S. Air Force Academy, Colorado Springs, CO
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Oliver Sto¨rmer,
Oliver Sto¨rmer
Bundesamt fur Wehrtechnik und Beschaffung, Manching, Germany
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James W. Baughn,
James W. Baughn
University of California at Davis, Davis, CA
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Terrence W. Simon,
Terrence W. Simon
University of Minnesota, Minneapolis, MN
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Kenneth W. Van Treuren,
Kenneth W. Van Treuren
Baylor University, Waco, TX
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Jo¨rg List
Jo¨rg List
Bundesamt fur Wehrtechnik und Beschaffung, Manching, Germany
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Aaron R. Byerley
U.S. Air Force Academy, Colorado Springs, CO
Oliver Sto¨rmer
Bundesamt fur Wehrtechnik und Beschaffung, Manching, Germany
James W. Baughn
University of California at Davis, Davis, CA
Terrence W. Simon
University of Minnesota, Minneapolis, MN
Kenneth W. Van Treuren
Baylor University, Waco, TX
Jo¨rg List
Bundesamt fur Wehrtechnik und Beschaffung, Manching, Germany
Paper No:
GT2002-30662, pp. 1191-1199; 9 pages
Published Online:
February 4, 2009
Citation
Byerley, AR, Sto¨rmer, O, Baughn, JW, Simon, TW, Van Treuren, KW, & List, J. "Using Gurney Flaps to Control Laminar Separation on Linear Cascade Blades." Proceedings of the ASME Turbo Expo 2002: Power for Land, Sea, and Air. Volume 5: Turbo Expo 2002, Parts A and B. Amsterdam, The Netherlands. June 3–6, 2002. pp. 1191-1199. ASME. https://doi.org/10.1115/GT2002-30662
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