Measurement and Calculation of Nozzle Guide Vane End Wall Heat Transfer

[+] Author and Article Information
N. W. Harvey, M. G. Rose

Turbine Engineering, Aerothermal Methods, Rolls-Royce plc, Derby, United Kingdom

J. Coupland

Aerothermal Methods, Rolls-Royce plc, Derby, United Kingdom

T. V. Jones

University of Oxford, Department of Engineering Science, Derby, United Kingdom

J. Turbomach 121(2), 184-190 (Apr 01, 1999) (7 pages) doi:10.1115/1.2841300 History: Received February 01, 1998; Online January 29, 2008


A three-dimensional steady viscous finite volume pressure correction method for the solution of the Reynolds-averaged Navier–Stokes equations has been used to calculate the heat transfer rates on the end walls of a modern High Pressure Turbine first-stage stator. Surface heat transfer rates have been calculated at three conditions and compared with measurements made on a model of the vane tested in annular cascade in the Isentropic Light Piston Facility at DERA, Pyestock. The NGV Mach numbers, Reynolds numbers, and geometry are fully representative of engine conditions. Design condition data have previously been presented by Harvey and Jones (1990). Off-design data are presented here for the first time. In the areas of highest heat transfer, the calculated heat transfer rates are shown to be within 20 percent of the measured values at all three conditions. Particular emphasis is placed on the use of wall functions in the calculations with which relatively coarse grids (of around 140,000 nodes) can be used to keep computational run times sufficiently low for engine design purposes.

Copyright © 1999 by The American Society of Mechanical Engineers
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