Laminar and transitional boundary layer structures in accelerating flow with heat transfer
Abstract
The accurate prediction of heat transfer coefficients on cooled gas turbine blades requires consideration of various influence parameters. The present study continues previous work with special efforts to determine the separate effects of each of several parameters important in turbine flow. Heat transfer and boundary layer measurements were performed along a cooled flat plate with various freestream turbulence levels (Tu = 1.6-11 percent), pressure gradients (k = 0-6 x 10 to the -6th), and cooling intensites (1.0-0.53). Whereas the majority of previously available results were obtained from adiabatic or only slightly heated surfaces, the present study is directed mainly toward application on highly cooled surfaces as found in gas turbine engines.
- Publication:
-
31st International Gas Turbine Conference and Exhibit
- Pub Date:
- June 1986
- Bibcode:
- 1986gatu.conf.....R
- Keywords:
-
- Boundary Layer Transition;
- Gas Turbine Engines;
- Heat Transfer;
- Laminar Boundary Layer;
- Surface Cooling;
- Turbine Blades;
- Flat Plates;
- Heat Transfer Coefficients;
- Pressure Gradients;
- Reynolds Number;
- Turbulent Boundary Layer;
- Wall Flow;
- Fluid Mechanics and Heat Transfer