An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability.
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We claim: 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 a
We claim: 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. 2. The airfoil as defined in claim 1, wherein said flow metering orifice is disposed in a rib extending integrally from a first inner face of the airfoil to an opposite second inner face thereof. 3. The airfoil as defined in claim 2, wherein said at least one metering orifice comprises a plurality of orifices along said rib. 4. The airfoil as defined in claim 2, wherein said rib substantially blocks the internal cooling path immediately upstream of said at least one exit aperture, but for said orifice. 5. The airfoil as defined in claim 4, wherein said rib is divided in a plurality of rib segments co-operating to define a plurality of said metering orifices. 6. The airfoil as defined in claim 5, wherein said metering orifices vary in size from one end of the airfoil to another end thereof. 7. The airfoil as defined in claim 1, wherein the flaw metering structure and the airfoil body are cast as a unitary piece. 8. The airfoil as defined in claim 6, wherein the metering orifices are arranged in order of ascending size from one end of the airfoil to another end thereof. 9. A cooled gas turbine engine airfoil comprising a hollow body defining an internal cooling path through which a cooling fluid is circulated to convectively cool the airfoil, at least one exit aperture through which the cooling fluid leaves the airfoil, the flow of cooling fluid leaving the airfoil being metered by a series of metering orifices defined in a rib structure extending across the cooling path immediately upstream of said at least one exit aperture, the size of the metering orifices relative to said at least one exit aperture being such that said at least one exit aperture plays no metering role on the flow of cooling air flowing therethrough, wherein the rib structure and the hollow body are of unitary construction. 10. The airfoil as defined in claim 9, wherein the metering orifices are sized to be smaller than said at least one exit aperture. 11. The airfoil as defined in claim 9, wherein said rib structure is divided in a plurality of rib segments, each pair of adjacent rib segments defining a said metering orifice. 12. The airfoil as defined in claim 9, wherein said metering orifices have different cross-sectional flow area relative to one another. 13. A casting core for use in the manufacturing of a hollow gas turbine engine airfoil, comprising a solid body adapted to be used for forming an internal geometry of an airfoil having an internal cooling path, a row of primary apertures defined through said solid body, each pair of adjacent primary apertures being spaced by a primary rib forming a corresponding metering aperture in the gas turbine engine airfoil, and a row of secondary apertures through said solid body, each pair of adjacent secondary apertures being spaced by a secondary rib forming a corresponding exit aperture in a trailing edge region of the gas turbine engine airfoil, and wherein the primary ribs are smaller in size than said secondary ribs and said primary ribs are immediately upstream of said secondary ribs, wherein the size of the primary ribs vary depending of the locations thereof along the row of primary apertures. 14. The casting core as defined in claim 13, wherein said solid body includes a trailing edge finger forming a trailing edge passage in the gas turbine engine airfoil, and wherein said rows of primary and secondary apertures are defined in said trailing edge finger and substantially parallel to one another. 15. A method of making an internally cooled airfoil, comprising the steps of: providing an airfoil having an internal cooling path terminating in at least one exit aperture, sizing said exit aperture to permit satisfactory manufacturability, providing a metering rib immediately upstream of the exit aperture with at least one orifice defined therein, siring the at least one orifice to restrict the flow delivered to the at least one exit aperture to thereby meter the overall airflow exiting the airfoil irrespective of the size of the at least one exit aperture. 16. 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 therethrough 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 said flow metering orifice is disposed in a rib extending integrally from a first inner face of the airfoil to an opposite second inner face thereof.
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이 특허에 인용된 특허 (15)
Doughty Roger L. ; Jendrix Richard W., AFT flowing serpentine airfoil cooling circuit with side wall impingement cooling chambers.
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Brown Wesley D. (Jupiter FL) Hall Kenneth B. (Jupiter FL) Kildea Robert J. (North Palm Beach FL), Method of casting to control the cooling air flow rate of the airfoil trailing edge.
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