Compressor Blade Boundary Layers: Part 2—Measurements With Incident Wakes

[+] Author and Article Information
Y. Dong

Gas Turbine Engineering Division, Ruston Gas Turbines Ltd., Lincoln LNG 7AA, United Kingdom

N. A. Cumpsty

Department of Engineering, Whittle Laboratory, University of Cambridge, Cambridge, CB3 ODY, United Kingdom

J. Turbomach 112(2), 231-240 (Apr 01, 1990) (10 pages) doi:10.1115/1.2927637 History: Received January 04, 1989; Online June 09, 2008


This paper follows directly from Part 1 by the same authors and describes measurements of the boundary layer on a supercritical-type compressor blade with wakes from a simulated moving upstream blade row convected through the passage. (The blades and the test facilities together with the background are described in Part 1). The results obtained with the wakes are compared to those with none for both low and high levels of inlet turbulence. The transition process and boundary layer development are very different in each case, though the overall momentum thickness at the trailing edge is fairly similar. None of the models for transition is satisfactory when this is initiated by moving wakes.

Copyright © 1990 by The American Society of Mechanical Engineers
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.

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