Analysis for predicting adiabatic wall temperatures with single hole coolant injection into a low speed crossflowAssuming the local adiabatic wall temperature equals the local total temperature in a low speed coolant mixing layer, integral conservation equations with and without the boundary layer effects are formulated for the mixing layer downstream of a single coolant injection hole oriented at a 30 degree angle to the crossflow. These equations are solved numerically to determine the center-line local adiabatic wall temperature and the effective coolant coverage area. Comparison of the numerical results with an existing film cooling experiment indicates that the present analysis permits a simplified but reasonably accurate prediction of the centerline effectiveness and coolant coverage area downstream of a single hole crossflow streamwise injection at 30-deg inclination angle.
Document ID
19810045594
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wang, C. R. (NASA Lewis Research Center Cleveland, OH, United States)
Papell, S. S. (NASA Lewis Research Center Cleveland, OH, United States)
Graham, R. W. (NASA Lewis Research Center Cleveland, Ohio, United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
ASME PAPER 81-GT-91
Meeting Information
Meeting: Gas Turbine Conference and Products Show
Location: Houston, TX
Start Date: March 9, 1981
End Date: March 12, 1981
Sponsors: American Society of Mechanical Engineers