Aerodynamic Performance of a Transonic Low Aspect Ratio Turbine Nozzle

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

Turbine Aerodynamics, Pratt & Whitney Canada, Inc., Montreal, Quebec, Canada

W. E. Carscallen

Combustion and Fluids Engineering Laboratory, National Research Council, Ottawa, Ontario, Canada

J. D. McGeachy

Department of Mechanical Engineering, Queen’s University, Kingston, Ontario, Canada

J. Turbomach 115(3), 400-408 (Jul 01, 1993) (9 pages) doi:10.1115/1.2929267 History: Received January 28, 1992; Online June 09, 2008


This paper presents detailed information on the three-dimensional flow field in a realistic turbine nozzle with an aspect ratio of 0.65 and a turning angle of 76 deg. The nozzle has been tested in a large-scale planar cascade over a range of exit Mach numbers from 0.3 to 1.3. The experimental results are presented in the form of nozzle passage Mach number distributions and spanwise distribution of losses and exit flow angle. Details of the flow field inside the nozzle passage are examined by means of surface flow visualization and Schlieren pictures. The performance of the nozzle is compared to the data obtained for the same nozzle tested in an annular cascade and a stage environment. Excellent agreement is found between the measured pressure distribution and the prediction of a three-dimensional Euler flow solver.

Copyright © 1993 by The American Society of Mechanical Engineers
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