The aerothermal performance of a typical turbine blade three-pass turbulated cooling circuit geometry was investigated in a 10X plexiglass test model. The model closely duplicated the blade’s leading edge, midchord, and trailing edge cooling passage geometries. Steady-state heat transfer coefficient distributions along the blade pressure side wall (convex surface) of the cooling circuit passages were measured with a thin-foil heater and a liquid crystal temperature sensor assembly. The heat transfer experiments were conducted on rib-roughened channels with staggered turbulators along the convex and concave surfaces of the cooling passages. Midchannel axial velocity and turbulence intensity measurements were taken by hot-wire anemometry at each passage end of the three-pass cooling circuit to characterize and relate the local thermal performance to the turbulence intensity levels. The near-atmospheric experimental data are compared with results of a Computational Fluid Dynamics (CFD) analysis at the operating internal environment for a 1X rotating model of the blade cooling circuit and other turbulator channel geometry heat transfer data investigations. The comparison between the measurements and analysis is encouraging. Differences with other heat transfer data appear reasonably understood and explainable.
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January 1994
Research Papers
Heat Transfer and Turbulence in a Turbulated Blade Cooling Circuit
N. Abuaf,
N. Abuaf
Corporate Research & Development, General Electric Company, Schenectady, NY 12301
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D. M. Kercher
D. M. Kercher
GE Aircraft Engines, Lynn, MA 01910
Search for other works by this author on:
N. Abuaf
Corporate Research & Development, General Electric Company, Schenectady, NY 12301
D. M. Kercher
GE Aircraft Engines, Lynn, MA 01910
J. Turbomach. Jan 1994, 116(1): 169-177 (9 pages)
Published Online: January 1, 1994
Article history
Received:
February 17, 1992
Online:
June 9, 2008
Citation
Abuaf, N., and Kercher, D. M. (January 1, 1994). "Heat Transfer and Turbulence in a Turbulated Blade Cooling Circuit." ASME. J. Turbomach. January 1994; 116(1): 169–177. https://doi.org/10.1115/1.2928272
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