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Control of Tip-Clearance Flow in a Low Speed Axial Compressor Rotor With Plasma Actuation

[+] Author Affiliations
Giridhar Jothiprasad, Robert C. Murray, Katherine Essenhigh, Grover A. Bennett, Seyed Saddoughi

GE Global Research, Niskayuna, NY

Aspi Wadia, Andrew Breeze-Stringfellow

GE Aviation, West Chester, OH

Paper No. GT2010-22345, pp. 161-172; 12 pages
doi:10.1115/GT2010-22345
From:
  • ASME Turbo Expo 2010: Power for Land, Sea, and Air
  • Volume 7: Turbomachinery, Parts A, B, and C
  • Glasgow, UK, June 14–18, 2010
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-4402-1 | eISBN: 978-0-7918-3872-3
  • Copyright © 2010 by ASME

abstract

This research investigates different dielectric barrier discharge (DBD) actuator configurations for affecting tip leakage flow and suppressing stall inception. Computational investigations were performed on a low-speed rotor with a highly loaded tip region that was responsible for stall-onset. The actuator was mounted on the casing upstream of the rotor leading edge. Plasma injection had a significant impact on the predicted tip-gap flow and improved stall margin. The effect of changing the actuator forcing direction on stall margin was also studied. The improvement in stall margin was closely correlated with a reduction in loading parameter that quantifies mechanisms responsible for end-wall blockage generation. The actuation reduced end-wall losses by increasing the static pressure of tip-gap flow emerging from blade suction-side. Lastly, an approximate speed scaling developed for the DBD force helped estimate force requirements for stall enhancement of transonic rotors.

Copyright © 2010 by ASME

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