An Experimental High-Temperature Turbine (No. 126) Part I.—The Cooling Performance of a Set of Extruded Air-Cooled Turbine Blades Part II.-The Effects of Cooling on the Aerodynamic Performance

摘要

Cooling characteristics are given in terms of the variation of average blade temperature at mid-span with cooling-flow rate, Reynolds number, gas/cooling-air absolute temperature ratio, and, for the rotor, gas-stream incidence. Chordwise and spanwise variations of blade temperature are also presented.nMeasured pressure-drop characteristics indicate that in a gas-turbine engine, with the cooling-air inlet pressure equal to the turbine gas inlet total pressure, cooling flows roughly equal to 1-8 per cent and 3 • 0 per cent of the main gas flow could be passed through the nozzle and rotor blades respectively, giving average relative temperatures at mid-span of approximately 0 • 6 in each instance.