Gas turbine heat exchanger assembly and method for fabricating same
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/10
F02C-007/08
출원번호
US-0902445
(2004-07-29)
등록번호
US-7334411
(2008-02-26)
발명자
/ 주소
Vandermolen,Robert
출원인 / 주소
General Electric Company
대리인 / 주소
Andes,William Scott
인용정보
피인용 횟수 :
5인용 특허 :
4
초록▼
A method for assembling a gas turbine engine includes fabricating a heat exchanger that includes a first manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the manifold inlet, a second quantity of heat exchanger elements coupled
A method for assembling a gas turbine engine includes fabricating a heat exchanger that includes a first manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the manifold inlet, a second quantity of heat exchanger elements coupled in flow communication with the manifold outlet, and a plurality of channels coupled in flow communication with the first and second quantity of heat exchanger elements to facilitate channeling compressor discharge air from the first quantity of heat exchanger elements to the second quantity of heat exchanger elements, and coupling the heat exchanger assembly to the gas turbine engine such that the heat exchanger is positioned substantially concentrically with respect to a gas turbine engine axis of rotation, and such that the heat exchanger is configured to receive compressor discharge air and channel the compressor discharge air to the combustor.
대표청구항▼
What is claimed is: 1. A method for assembling a gas turbine engine including a compressor and a combustor, said method comprising: fabricating a heat exchanger assembly that includes at least one heat exchanger, wherein the heat exchanger includes: a first manifold including an inlet and an outlet
What is claimed is: 1. A method for assembling a gas turbine engine including a compressor and a combustor, said method comprising: fabricating a heat exchanger assembly that includes at least one heat exchanger, wherein the heat exchanger includes: a first manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the manifold inlet; a second quantity of heat exchanger elements coupled in flow communication with the manifold outlet, each of the first and second quantities of heat exchanger elements are each aligned substantially perpendicular to a direction of exhaust flow discharged from the gas turbine engine therebetween, and a plurality of channels coupled in flow communication between the first and second quantity of heat exchanger elements to enable compressor discharge air to be channeled from the first quantity of heat exchanger elements to the second quantity of heat exchanger elements; and coupling the inlet of the heat exchanger assembly to the gas turbine engine such that the heat exchanger is positioned substantially concentrically with respect to an axis of rotation of the gas turbine engine, and such that the heat exchanger receives compressor discharge air; and coupling the exhaust of the heat exchanger assembly to the combustor such that the compressor discharge air is channeled from the heat exchanger assembly to the combustor. 2. A method in accordance with claim 1 wherein fabricating a heat exchanger assembly further comprises fabricating a heat exchanger that includes: a second manifold including an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with the second manifold inlet, a second quantity of heat exchanger elements coupled in flow communication with the second manifold outlet, and a plurality of channels coupled in flow communication between the first and second quantity of second manifold heat exchanger elements enable compressor discharge air to be channeled from the first quantity of heat exchanger elements to the second quantity of heat exchanger elements within the second manifold. 3. A method in accordance with claim 2 wherein fabricating a heat exchanger assembly further comprises fabricating the first and second manifolds as a unitary manifold. 4. A method in accordance with claim 1 wherein coupling the heat exchanger assembly to the gas turbine engine further comprises: coupling an annular heat exchanger to an outer casing; and coupling the outer casing to a rear frame of the gas turbine engine such that the annular heat exchanger is aligned substantially concentrically with an axis of rotation of the gas turbine engine. 5. A method in accordance with claim 1 wherein coupling the heat exchanger assembly to the gas turbine engine further comprises coupling a heat exchanger assembly including a fixed plug nozzle to a rear frame of the gas turbine such that a predetermined quantity of compressor air is channeled through the at least one heat exchanger assembly. 6. A method in accordance with claim 5 wherein coupling a movable apparatus further comprises coupling at least one of a mechanical device, a hydraulic device, and a pneumatic device to the variable plug nozzle to selectively regulate an amount of compressor air channeled through the heat exchanger. 7. A method in accordance with claim 1 wherein coupling the heat exchanger assembly to the gas turbine engine further comprises coupling a heat exchanger assembly including a variable plug nozzle to the gas turbine engine to selectively control an amount of compressor air channeled through the at least one heat exchanger assembly. 8. A method in accordance with claim 7 further comprising coupling a movable apparatus to the variable plug nozzle to selectively control an amount of compressor air channeled through the at least one heat exchanger assembly. 9. A heat exchanger assembly for a gas turbine engine, said heat exchanger assembly comprising: an annular heat exchanger coupled in flow communication to a compressor, said heat exchanger configured to channel compressor discharge air to a combustor, said heat exchanger assembly coupled to said gas turbine engine such that said heat exchanger is substantially concentrically aligned with respect to an axis of rotation of the gas turbine engine, said heat exchanger assembly comprising: a first manifold comprising an inlet and an outlet, wherein said manifold inlet comprises a cross-sectional area that is inversely proportional to a manifold outlet cross-sectional area; a first quantity of heat exchanger elements coupled in flow communication with said manifold inlet; a second quantity of heat exchanger elements coupled in flow communication with said manifold outlet, each of said first quantity and said second quantity of heat exchanger elements are each aligned substantially perpendicular to a direction of exhaust flow discharged from the gas turbine engine therebetween; and a plurality of channels coupled in flow communication between said first and second quantity of heat exchanger elements to enable compressor air to be channeled from said first quantity of heat exchanger elements to said second quantity of heat exchanger elements. 10. A beat exchanger assembly in accordance with claim 9 further comprising: a second manifold comprising an inlet and an outlet, a first quantity of heat exchanger elements coupled in flow communication with said second manifold inlet; a second quantity of heat exchanger elements coupled in flow communication with said second manifold outlet; and a plurality of channels coupled in flow communication between said first and second quantity of second heat exchanger elements to enable compressor discharge air to be channeled from said first quantity of heat exchanger elements to said second quantity of heat exchanger elements within said second manifold. 11. A heat exchanger assembly in accordance with claim 10 wherein said first and second manifolds are fabricated as a unitary manifold. 12. A heat exchanger assembly in accordance with claim 9 further comprising a plug nozzle fixedly secured to a rear frame of said gas turbine engine to facilitate controlling a predetermined amount of compressor air channeled through said heat exchanger. 13. A heat exchanger assembly in accordance with claim 9 further comprising a variable plug nozzle coupled to a gas turbine rear frame, said plug nozzle moveable with respect to said heat exchanger to selectively regulate an amount of compressor air channeled through said heat exchanger. 14. A heat exchanger assembly in accordance with claim 13 further comprising a movable apparatus coupled to said variable plug nozzle to facilitate regulating the amount of compressor air channeled through said heat exchanger. 15. A heat exchanger assembly in accordance with claim 14 wherein said movable apparatus comprises at least one of a mechanical device, a hydraulic device, and a pneumatic device. 16. A heat exchanger assembly in accordance with claim 15 further comprising a drive mechanism coupled to said movable device, said drive mechanism configured to selectively move said plug nozzle to selectively regulate the amount of compressor air channeled through said heat exchanger. 17. A gas turbine engine comprising: a compressor; a combustor downstream from said compressor; a turbine coupled in flow communication with said combustor; and a heat exchanger assembly comprising: an annular heat exchanger coupled in flow communication to a compressor, said heat exchanger configured to channel compressor discharge air to the combustor, said heat exchanger assembly coupled to said gas turbine engine such that said heat exchanger is substantially concentrically aligned with respect to an axis of rotation of the gas turbine engine, said heat exchanger assembly comprising: a first manifold comprising an inlet and an outlet, wherein said manifold inlet comprises a cross-sectional area that is inversely proportional to a manifold outlet cross-sectional area; a first quantity of heat exchanger elements coupled in flow communication with said manifold inlet; a second quantity of heat exchanger elements coupled in flow communication with said manifold outlet, each of said first quantity and said second quantity of heat exchanger elements are each aligned substantially perpendicular to a direction of exhaust flow discharged from said gas turbine engine therebetween; and a plurality of channels coupled in flow communication between said first and second quantity of heat exchanger elements to enable compressor air to be channeled from said first quantity of heat exchanger elements to said second quantity of heat exchanger elements. 18. A gas turbine engine in accordance with claim 17 wherein said heat exchanger assembly further comprises a plug nozzle fixedly secured to a rear frame of said gas turbine engine to facilitate controlling a predetermined amount of compressor air channeled through said heat exchanger. 19. A gas turbine engine in accordance with claim 17 wherein said heat exchanger assembly further comprises a variable plug nozzle coupled to a rear frame of said gas turbine engine, said variable plug nozzle moveable with respect to said heat exchanger to facilitate regulating an amount of compressor discharge air that is channeled through said heat exchanger. 20. A gas turbine engine in accordance with claim 19 wherein said heat exchanger assembly further comprises: a translation apparatus coupled to said plug nozzle to facilitate regulating the amount of compressor air channeled through said heat exchanger; and a drive mechanism coupled to said translation device, said drive mechanism configured to selectively translate said variable plug nozzle to facilitate regulating the amount of compressor air channeled through said heat exchanger.
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이 특허에 인용된 특허 (4)
Hines William R. (Cincinnati OH), Gas-side bypass flow system for the air recuperator of a gas turbine engine.
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