0
research-article

Effect of Internal Crossflow Velocity on Film Cooling Effectiveness – Part I: Axial Shaped Holes

[+] Author and Article Information
John W. McClintic

The University of Texas at Austin 204 E. Dean Keeton St, Austin, TX 78712
johnwmcclintic@gmail.com

Joshua B. Anderson

The University of Texas at Austin 204 E. Dean Keeton St, Austin, TX 78712
mranderson@utexas.edu

David G. Bogard

The University of Texas at Austin 204 E. Dean Keeton St, Austin, TX 78712
dbogard@mail.utexas.edu

Thomas E. Dyson

GE Global Research Center 1 Research Circle, Schenectady, NY 12309
dyson@ge.com

Zachary D. Webster

GE Aviation 1 Neumann Way, Cincinnati, OH 45125
zachary.webster@ge.com

1Corresponding author.

ASME doi:10.1115/1.4037997 History: Received August 18, 2017; Revised September 05, 2017

Abstract

The effect of feeding shaped film cooling holes with an internal crossflow is not well understood. Previous studies have shown internal crossflow reduces film cooling effectiveness from axial shaped holes, but little is known about the mechanisms governing this effect. It was recently shown that the crossflow-to-mainstream velocity ratio is important, but only a few of these crossflow velocity ratios have been studied. This effect is of concern because gas turbine blades typically feature internal passages that feed film cooling holes in this manner. In this study, film cooling effectiveness was measured for a single row of axial shaped cooling holes fed by an internal crossflow with crossflow-to-mainstream velocity ratio varying from 0.2-0.6 and jet-to-mainstream velocity ratios varying from 0.3-1.7. Experiments were conducted in a low speed flat plate facility at coolant-to-mainstream density ratios of 1.2 and 1.8. It was found that film cooling effectiveness was highly sensitive to crossflow velocity at higher injection rates, while it was much less sensitive at lower injection rates. Analysis of the jet shape and lateral spreading found that certain jet characteristic parameters scale well with the crossflow-to-coolant jet velocity ratio, demonstrating that the crossflow effect is governed by how coolant enters the film cooling holes.

Copyright (c) 2017 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Tables

Errata

Discussions

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.

Related Journal Articles
Related eBook Content
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