Heat Transfer Predictions for Two Turbine Nozzle Geometries at High Reynolds and Mach Numbers

[+] Author and Article Information
R. J. Boyle

NASA Lewis Research Center, Cleveland, OH 44135

R. Jackson

DRA Pyestock, Farnborough, Hants, United Kingdom

J. Turbomach 119(2), 270-283 (Apr 01, 1997) (14 pages) doi:10.1115/1.2841110 History: Received February 16, 1995; Online January 29, 2008


Predictions of turbine vane and endwall heat transfer and pressure distributions are compared with experimental measurements for two vane geometries. The differences in geometries were due to differences in the hub profile, and both geometries were derived from the design of a high rim speed turbine (HRST). The experiments were conducted in the Isentropic Light Piston Facility (ILPF) at Pyestock at a Reynolds number of 5.3 x 106 , a Mach number of 1.2, and a wall-to-gas temperature ratio of 0.66. Predictions are given for two different steady-state three-dimensional Navier–Stokes computational analyses. C-type meshes were used, and algebraic models were employed to calculate the turbulent eddy viscosity. The effects of different turbulence modeling assumptions on the predicted results are examined. Comparisons are also given between predicted and measured total pressure distributions behind the vane. The combination of realistic engine geometries and flow conditions proved to be quite demanding in terms of the convergence of the CFD solutions. An appropriate method of grid generation, which resulted in consistently converged CFD solutions, was identified.

Copyright © 1997 by The American Society of Mechanical Engineers
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