Abstract

Computations of flow and heat transfer for a film-cooled high pressure gas turbine rotor blade geometry are presented with an assessment of several turbulence models. Details of flow and temperature field predictions in the vicinity of cooling holes are examined. It is demonstrated that good predictions can be obtained when spurious turbulence energy production by the turbulence model is prevented.

Issue Section:
Technical Papers
Keywords:
gas turbines, film flow, cooling, heat transfer, rotors, turbulence, modelling
Topics:
Cooling, Film cooling, Suction, Turbulence, Pressure, Heat transfer, Flow (Dynamics), Temperature, Blades, Heat transfer coefficients
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Copyright © 2002
 by ASME
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