Film Cooling of a Turbine Blade With Injection Through Two Rows of Holes in the Near-Endwall Region

[+] Author and Article Information
R. J. Goldstein, P. H. Chen

Mechanical Engineering Department, University of Minnesota, Minneapolis, MN 55455

J. Turbomach 109(4), 588-593 (Oct 01, 1987) (6 pages) doi:10.1115/1.3262152 History: Received February 19, 1987; Online November 09, 2009


Measurements of film cooling on a simulated turbine blade are conducted using a mass transfer technique. Under the influence of the endwall, dramatic changes of film cooling performance occur on the convex surface of the blade as compared to the region where the flow is two dimensional. The result is a triangular region, where coolant is swept away from the surface by the three-dimensional vortex-driven flow present between adjacent blades. In order to predict the area of this unprotected region, the influences of several parameters including density ratio, blowing rate, and number of rows of injection holes are studied. The presence of the endwall affects the film cooling performance on the concave surface only slightly.

Copyright © 1987 by ASME
Your Session has timed out. Please sign back in to continue.






Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In