Patent ID: 7278826
Filing Date: 2007-10-09
Classification: F01D,F05D,Y02T,Y10T

Abstract:
1. An airfoil for a gas turbine engine, the airfoil comprising an airfoil body having an internal cooling path, at least one exit aperture through which cooling air leaves the airfoil, and at least one flow metering orifice defined upstream of the at least one exit aperture, the cooling air passing through the at least one flow metering orifice before leaving through the at least one exit aperture, the at least one flow metering orifice being sized to meter the cooling air passing theretbrough to obtain a desired flow, the at least one exit aperture being sized such as to let the desired flow therethrough and out of the airfoil without restriction, wherein the at least one flow metering orifice includes a plurality of metering orifices having a first total cross-section, the at least one exit apertures includes a plurality of exit apertures having a second total cross-section larger than the first total cross-section, and a number of flow metering orifices being at least twice as large as a number of exit apertures.