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RESEARCH PAPERS

Streakline Flow Visualization of Discrete Hole Film Cooling for Gas Turbine Applications

[+] Author and Article Information
R. S. Colladay

Turbomachinery Fundamentals Section, NASA-Lewis Research Center, Cleveland, Ohio

L. M. Russell

NASA-Lewis Research Center, Cleveland, Ohio

J. Heat Transfer 98(2), 245-250 (May 01, 1976) (6 pages) doi:10.1115/1.3450526 History: Received March 03, 1976; Online August 11, 2010

Abstract

Film injection from discrete holes in a three row staggered array with 5-dia spacing was studied for three hole angles: (1) normal, (2) slanted 30 deg to the surface in the direction of the mainstream, and (3) slanted 30 deg to the surface and 45 deg laterally to the mainstream. The ratio of the boundary layer thickness-to-hole diameter and the Reynolds number were typical of gas turbine film cooling applications. Results from two different injection locations are presented to show the effect of boundary layer thickness on film penetration and mixing. Detailed streaklines showing the turbulent motion of the injected air were obtained by photographing very small neutrally-buoyant helium filled “soap” bubbles which follow the flow field. Unlike smoke, which diffuses rapidly in the high turbulent mixing region associated with discrete hole blowing, the bubble streaklines passing downstream injection locations are clearly identifiable and can be traced back to their point of ejection.

Copyright © 1976 by ASME
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