Influence of Rotor Blade Aerodynamic Loading on the Performance of a Highly Loaded Turbine Stage

[+] Author and Article Information
S. H. Moustapha

Pratt & Whitney Canada Inc., Longueuil, Canada

U. Okapuu

Turbine Aerodynamics, Pratt & Whitney Canada Inc., Longueuil, Canada

R. G. Williamson

Gas Dynamics Laboratory, National Research Council, Canada

J. Turbomach 109(2), 155-161 (Apr 01, 1987) (7 pages) doi:10.1115/1.3262078 History: Received January 10, 1986; Online November 09, 2009


This paper describes the performance of a highly loaded single-stage transonic turbine with a pressure ratio of 3.76 and a stage loading factor of 2.47. Tests were carried out with three rotors, covering a range of blade Zweifel coefficient of 0.77 to 1.18. Detailed traversing at rotor inlet and exit allowed an assessment of rotor and stage performance as a function of blade loading under realistic operating conditions. The effect of stator endwall contouring on overall stage performance was also investigated using two different contours with the same vane design.

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