Boundary-Layer Transition and Separation Near the Leading Edge of a High-Speed Turbine Blade

[+] Author and Article Information
H. P. Hodson

Whittle Laboratory, Cambridge University Engineering Department, Cambridge, England

J. Eng. Gas Turbines Power 107(1), 127-134 (Jan 01, 1985) (8 pages) doi:10.1115/1.3239672 History: Received January 12, 1984; Online October 15, 2009


The state of the boundary layers near the leading edge of a high-speed turbine blade has been investigated, in cascade, using an array of surface-mounted, constant-temperature, hot-film anemometers. The measurements are interpreted with the aid of inviscid and viscous prediction codes. The effects of Reynolds number, compressibility, incidence, and free-stream turbulence are described. In all cases, the initial development of the boundary layers was extremely complex and, even at design conditions, separation and reattachment, transition and relaminarization were found to occur.

Copyright © 1985 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.

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