The blade to aerodynamic profile to machine at a flow of fluid, such as a gas turbine engine

摘要

1,070,480. Turbine blades. ROLLS-ROYCE Ltd. Feb.1, 1966, No.4498/66. Heading F1T. Each turbine nozzle guide blade in a gas turbine engine comprises an external wall 20 surrounding an internal liner 16 provided over a major portion thereof with a multiplicity of holes 25 through which cooling air supplied by the engine compressor passes from an inner chamber 17 to a space 21 between the liner and the external wall so as to effect cooling of the wall. The air then flows over radially spaced baffles (32), Fig. 2 (not shown), to leave the blade through one or more apertures 26 at the trailing edge 24. Each blade is mounted in an annular combustion chamber (12), Fig. 1 (not shown), and some of the air from chamber 17 flows directly through radially spaced passages 31 to enter the combustion chamber as dilution air. Very few holes 25 are provided adjacent the radially inner and outer ends of the liner 16.