Separation control using plasma actuators: Steady flow in low pressure turbines

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Scopus citations

Abstract

A Dielectric Barrier Discharge plasma actuator is operated in flow over the suction surface of a Pack-B Low Pressure Turbine (LPT) airfoil at a Reynolds number of 50,000 (based on exit velocity and suction surface length) and inlet free-stream turbulence intensity of 2.5%. Measurements of total pressure using a glass total-pressure tube are taken. Corrections for streamline displacement due to shear and wall effects are made, and comparisons with previous hot-wire measurements are used to validate data. Measurements from previous work have shown that separation control is possible without stream-wise momentum addition, by adding disturbances that cause transition in the separated shear layer. The present results are from measurements taken using a glass dielectric, with a conventional two-electrode geometry, and a new three-electrode geometry. The region of high momentum flow produced due to the presence of the actuator is found to be above the shear layer, and not at the wall. The near-suction-surface total pressure field in the trailing part of the airfoil passage and its wall-normal gradient are used to demonstrate effective prevention of flow separation using the plasma actuator.

Original languageEnglish (US)
Title of host publicationASME 2011 Turbo Expo
Subtitle of host publicationTurbine Technical Conference and Exposition, GT2011
Pages1869-1878
Number of pages10
EditionPARTS A AND B
DOIs
StatePublished - Dec 1 2011
EventASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011 - Vancouver, BC, Canada
Duration: Jun 6 2011Jun 10 2011

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume5

Other

OtherASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011
Country/TerritoryCanada
CityVancouver, BC
Period6/6/116/10/11

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