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Adiabatic Effectiveness and Heat Transfer Coefficient on a Film-Cooled Rotating Bladethree-dimensional Navier-Stokes code has been used to compute the adiabatic effectiveness and heat transfer coefficient on a rotating film-cooled turbine blade. The blade chosen is the United Technologies Research Center(UTRC) rotor with five film-cooling rows containing 83 holes, including three rows on the shower head with 49 holes, covering about 86% of the blade span. The mainstream is akin to that under real engine conditions with stagnation temperature 1900 K and stagnation pressure 3 MPa. The blade speed is taken to be 5200 rpm. The adiabatic effectiveness is higher for a rotating blade as compared to that for a stationary blade. Also, the direction of coolant injection from the shower-head holes considerably affects the effectiveness and heat transfer coefficient values on both the pressure and suction surfaces. In all cases the heat transfer coefficient and adiabatic effectiveness are highly three-dimensional in the vicinity of holes but tend to become two-dimensional far downstream.
Document ID
20000033687
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Garg, Vijay K.
(AYT Corp. Cleveland, OH United States)
Date Acquired
August 19, 2013
Publication Date
January 1, 1997
Publication Information
Publication: Numerical Heat Transfer
Publisher: American Society of Mechanical Engineers
Volume: Part A
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
ASME Paper 96-GT-221
Distribution Limits
Public
Copyright
Other

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