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美国政府科技报告
>Engine Investigation of an Air-Cooled Turbine Rotor Blade Incorporating Impingement-Cooled Leading Edge, Chordwise Passages, and a Slotted Trailing Edge
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Engine Investigation of an Air-Cooled Turbine Rotor Blade Incorporating Impingement-Cooled Leading Edge, Chordwise Passages, and a Slotted Trailing Edge
Experimental temperatures are presented for an air-cooled turbine rotor blade tested in an engine. The data were obtained for turbine stator inlet temperatures from 2000 to 2500 F and for turbine-inlet gas pressures from 32 to 46 psia. Average and local in an engine. The data were obtained for turbine stator inlet temperatures from 2000 to 2500 F and for turbine-inlet gas pressures from 32 to 46 psia. Average and local blade heat-transfer data are correlated. Potential allowable increases in gas temperature are also discussed. (Author)
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