Investigation of Unsteady Flow Through a Transonic Turbine Stage: Data/Prediction Comparison for Time-Averaged and Phase-Resolved Pressure Data

[+] Author and Article Information
M. G. Dunn

Calspan Corp., Buffalo, NY 14225

W. A. Bennett, R. A. Delaney, K. V. Rao

Allison Gas Turbine Division, General Motors Corporation, Indianapolis, IN 46206-0420

J. Turbomach 114(1), 91-99 (Jan 01, 1992) (9 pages) doi:10.1115/1.2928003 History: Received May 01, 1991; Online June 09, 2008


This paper presents time-averaged and phase-resolved measurements of the surface pressure data for the vane and blade of a transonic single-stage research turbine. The data are compared and contrasted with predictions from an unsteady Euler/Navier–Stokes code. The data were taken in a shock-tunnel facility in which the flow was generated with a short-duration source of heated and pressurized air. Surf ace-mounted high-response pressure transducers were used to obtain the pressure measurements. The turbine was operating at the design flow function, the design stage pressure ratio, and 100 percent corrected speed. A matrix of data was obtained at two vane exit conditions and two vane/rotor axial spacings.

Copyright © 1992 by The American Society of Mechanical Engineers
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