[특허]Cooled gas turbine engine component

Rolls-Royce North American Technologies Inc.

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Cooled gas turbine engine component

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-005/18 F01D-025/12
출원번호	US-0141912 (2013-12-27)
등록번호	US-9874110 (2018-01-23)
발명자 / 주소	Vandervaart, Peter C. Rhodes, Jeffrey F. Kwon, Okey Heffernan, Tab M.
출원인 / 주소	Rolls-Royce North American Technologies Inc.
대리인 / 주소	Barnes & Thornburg LLP
인용정보	피인용 횟수 : 0 인용 특허 : 74

초록

A gas turbine component having a cooling passage is disclosed. In one form, the passage is oriented as a turned passage capable of reversing direction of flow, such as a turned cooling hole. The gas turbine engine component can include a layered structure having cooling flow throughout a region of the component. The cooling hole can be in communication with a space in the layered structure. The gas turbine engine component can be a cast article where a mold can be constructed to produce the cooling hole having a turn.

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1. An apparatus comprising: a cooled gas turbine engine component having a leading edge, a trailing edge spaced apart from the leading edge, and a midspan located between the leading edge and the trailing edge, the component including an inner wall that defines a plenum and an outer wall arranged around the inner wall;a first internal passage located between the inner wall and the outer wall and used for conveyance of a cooling fluid, the first internal passage fluidly connected to the plenum on a suction side of the component near the midspan;a first cooling hole extending between the inner wall and outer wall and having a first end oriented to receive cooling fluid from the first internal passage and a second end having an outlet formed in a suction side of the component near the leading edge and being capable of discharging the cooling fluid from the gas turbine engine component, the first cooling hole having opposing sides routed along a curvilinear path, anda second internal passageway located between the inner wall and the outer wall and used for conveyance of a cooling fluid and a second cooling hole located between the inner wall and the outer wall, the second internal passage fluidly connected to the plenum on the suction side of the component near the midspan, and the second cooling hole having a first end oriented to receive cooling fluid from the second internal passage and a second end having an outlet formed in a pressure side of the component near the trailing edge. 2. The apparatus of claim 1, wherein the first internal passage includes a plurality of pedestals, and wherein the first cooling hole is substantially free of pedestals. 3. The apparatus of claim 1, wherein the first cooling hole includes a bend that reverses direction of the cooling fluid. 4. The apparatus of claim 1, wherein the cooled gas turbine engine component further includes a casting mold having a core shaped to form the gas turbine component as a result of a casting operation, the casting mold including a space bound by a first side and a second side configured to produce a portion of the gas turbine engine component, a cooling hole core disposed in the space and configured to provide the cooling hole having an upstream end and a downstream end, the cooling hole core having a curvilinear shape along its length as it extends between the first side and second side. 5. The apparatus of claim 4, wherein the cooling hole core is located on an airfoil portion of the casting mold. 6. The apparatus of claim 5, wherein the cooling hole core is turned to reverse a direction as it extends between the first side and the second side, and wherein the cooling hole core is located at a leading edge region of the airfoil portion. 7. The apparatus of claim 4, which further includes a mold passage portion coupled with the cooling hole core, the mold passage portion having a plurality of pedestal core portions. 8. The apparatus of claim 7, wherein the cooling hole core includes a plurality of cooling hole cores. 9. The apparatus of claim 4, wherein the casting mold is a free-form fabricated processed component, and wherein the cooling hole core is substantially free of support members; and wherein the cooling hole core includes a plurality of cooling hole cores, and wherein the plurality of cooling hole cores includes staggered outlets. 10. The apparatus of claim 1, wherein the second internal passage includes a plurality of pedestals and the second cooling hole is substantially free of pedestals. 11. A method comprising: free form fabricating a gas turbine engine component core having an inner surface and an outer surface representing a cooling space of a cast gas turbine engine component, the fabricating including;building a core portion representing an internal flow space of the gas turbine engine component;forming a first cooling hole core fused with the core portion and having a first end and a second end and a bend intermediate the first and second ends, the first end of the first cooling hole core coupled with the core portion at a leading edge of the core portion;forming a second cooling hole core fused with the core portion and having a first end and a second end, the first end of the second cooling hole core coupled with the core portion at a trailing edge of the core portion on a pressure side of the core portion; andwherein the gas turbine engine component is a cooled turbine airflow member, and the fabricating further includes forming a first internal passage core that extends from a midspan of the core portion toward the leading edge of the core portion and forming a second internal passage core that extends from the midspan of the core portion on a suction side of the core portion toward the trailing edge of the core portion, the first internal passage core is coupled with the second end of the first cooling hole core, and the second internal passage core is coupled with the second end of the second cooling hole core. 12. The method of claim 11, wherein the free-form fabricating includes rigidizing a binder material that includes particulates, and wherein the bend is oriented to reverse direction of the cooling hole core. 13. The method of claim 11, wherein the fabricating includes developing a refractory mold having portions oriented to create a multi-walled, cooled gas turbine engine component, and wherein the cooling hole core includes a circular cross section. 14. A method comprising: providing a cooling fluid to a cooled gas turbine engine component;flowing a first portion of the cooling fluid through an inner space of the gas turbine engine component from a suction side of the component near a midspan of the component toward a leading edge of the component;directing the first portion of the cooling fluid from the inner space to a turned cooling hole of the gas turbine engine component, the turned cooling hole formed in the suction side of the component near the leading edge;ejecting the first portion of the cooling fluid out of the turned cooling hole, andflowing a second portion of the cooling fluid from the suction side of the component near the midspan of the component toward a trailing edge of the component;directing the second portion of the cooling fluid along a contour of the component; andejecting the second portion of the cooling fluid out of a pressure side of the component near the trailing edge. 15. The method of claim 14, wherein the flowing the first portion of the cooling fluid includes conveying the cooling fluid between an inner wall and an outer wall oriented to follow an exterior contour of the gas turbine engine component, the inner wall and outer wall defining the inner space, and further including delivering cooling fluid to a plenum of the cooled gas turbine engine component, and wherein the conveying includes routing the cooling fluid around pedestals disposed between the inner wall and the outer wall. 16. The method of claim 14, wherein the directing the first portion of the cooling fluid leads to reversing a direction of flow of the first portion of the cooling fluid as a result of the turned cooling hole.

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Cooled gas turbine engine component

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Cooled gas turbine engine component

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