Simulation of Three-Dimensional Viscous Flow Within a Multistage Turbine

[+] Author and Article Information
J. J. Adamczyk

NASA Lewis Research Center, Cleveland, OH 44135

M. L. Celestina, T. A. Beach

Sverdrup Technologies, Inc., NASA Lewis Research Center Group, Cleveland, OH 44135

M. Barnett

United Technologies Research Center, Hartford, CT 06108

J. Turbomach 112(3), 370-376 (Jul 01, 1990) (7 pages) doi:10.1115/1.2927669 History: Received January 25, 1989; Online June 09, 2008


This work outlines a procedure for simulating the flow field within multistage turbomachinery, which includes the effects of unsteadiness, compressibility, and viscosity. The associated modeling equations are the average passage equation system, which governs the time-averaged flow field within a typical passage of a blade row embedded within a multistage configuration. The results from a simulation of a low aspect ratio stage and one-half turbine will be presented and compared with experimental measurements. It will be shown that the secondary flow field generated by the rotor causes the aerodynamic performance of the downstream vane to be significantly different from that of an isolated blade row.

Copyright © 1990 by The American Society of Mechanical Engineers
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