Publication Date:
2016-06-07
Description:
The primary basis for heat transfer analysis of turbine airfoils is experimental data obtained in linear cascades. A detailed set of heat transfer coefficients was obtained along the midspan of a stator and a rotor in a rotating turbine stage. The data are to be compared to standard analyses of blade boundary layer heat transfer. A detailed set of heat transfer coefficients was obtained along the midspan of a stator located in the wake of a full upstream turbine stage. Two levels of inlet turbulence (1 and 10 percent) were used. The analytical capability will be examined to improve prediction of the experimental data.
Keywords:
FLUID MECHANICS AND HEAT TRANSFER
Type:
NASA. Lewis Research Center Turbine Engine Hot Section Technology, 1984; 8 p
Format:
application/pdf