ICSD 2019

ATTENUATION OF FLOW SEPARATION IN A NACA 8410 TURBINE CASCADE USING GURNEY FLAPS (141563)

DOI :

Abstract : The effect of Gurney Flaps on a NACA 8410 turbine cascade has been numerically studied. The blade angle of the cascade was maintained at 30o throughout the investigation. The Gurney Flaps were located at the trailing edge of the blades at an angular position of 45o with respect to the chord of the blade. The aerodynamic performance of the cascade at different inflow angles was evaluated with two Gurney Flaps of sizes 1% and 2% of the blade chord length. The results showed that, the Gurney Flaps substantially increased the lift produced by the turbine blades by altering the pressure distributions on both the suction and pressure side of the blade. The skin friction distributions on the suction side of the blades depicted a significant delay in the onset of flow separation due to the presence of the Gurney Flap. They also induced a significant increase in the exit Mach number and the flow turning angle under all the inflow angles that were studied.

Pages : 1-8

Downloads : 1

Publication Date :

Modified Date : 2019-04-12

Cite/Export :

T. Nilavarasan , Ganapati N. Joshi , Sunil Chandel , "ATTENUATION OF FLOW SEPARATION IN A NACA 8410 TURBINE CASCADE USING GURNEY FLAPS", IJIERT - International Journal of Innovations in Engineering Research and Technology, ICSD 2019, ISSN : 2394-3696, Page No. 1-8