[특허]Extruded fluid manifold for gas turbomachine combustor casing

General Electric Company

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특허 상세정보

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Extruded fluid manifold for gas turbomachine combustor casing

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-001/00
미국특허분류(USC)	060/752;
출원번호	US-0791341 (2010-06-01)
등록번호	US-8590315 (2013-11-26)
발명자 / 주소	Overby, Brandon Taylor Seale, Jason Allen Ucok, Ibrahim
출원인 / 주소	General Electric Company
대리인 / 주소	Cantor Colburn LLP
인용정보	피인용 횟수 : 1 인용 특허 : 4

초록
▼

A turbomachine includes a compressor, a turbine, and a combustor operatively coupled to the compressor and the turbine. The combustor includes a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage. The combustor casing includes an extruded fluid manifold mounted to the outer surface. The extruded fluid manifold includes first and second walls integrally formed with a third, connecting, wall. The first wall includes a first mounting element and the second wall includes a second mounting element. The first mounting element extends axially along the combustor casing away from the first wall and the second mounting element extends axially along the combustor casing away from the second wall and the first mounting element. The extruded fluid manifold is joined to the outer surface of the combustor casing through the first and second mounting elements.

대표
청구항
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1. A turbomachine comprising: a compressor;a turbine; anda combustor operatively coupled to the compressor and the turbine, the combustor including a combustor casing having a flange, an outer surface and an inner surface that defines an internal passage, the flange extending radially outwardly from the outer surface of the casing, the combustor casing including an extruded fuel manifold mounted to the outer surface, the extruded fuel manifold including first and second walls integrally formed with a third, connecting, wall, the first wall including a first mounting element and the second wall including a second mounting element, the first mounting element extending axially along the combustor casing away from the first wall and the second mounting element extending axially along the combustor casing away from the second wall and the first mounting element, the extruded fuel manifold being joined to the outer surface of the combustor casing through the first and second mounting elements, the extruded fuel manifold defining a fluid plenum that extends radially about the combustor casing, wherein the extruded fuel manifold includes an anti-corrosive layer that is non-reactive with fuel. 2. The turbomachine according to claim 1, wherein the anti-corrosive layer comprises stainless steel. 3. The turbomachine according to claim 1, wherein the anti-corrosive layer comprises a steel alloy including chromium. 4. The turbomachine according to claim 1, wherein the extruded fuel manifold includes at least one mounting member, the at least one mounting member extending axially outward from one of the first and second walls at the third wall. 5. The turbomachine according to claim 4, wherein the at least one mounting member is substantially co-planar with the third wall. 6. The turbomachine according to claim 4, further comprising: a bridge member extending between the at least one mounting member and the flange, the bridge member, defining, at least in part, a passage that extends about the combustor casing. 7. The turbomachine according to claim 1, wherein the extruded fuel manifold includes a first extrusion section and a second extrusion section, the first extrusion section being joined to the second extrusion section to form the extruded fluid manifold. 8. The turbomachine according to claim 1, further comprising: at least one fluid passage formed in the combustor casing, the at least one fluid passage fluidly coupling the fluid plenum and the internal passage. 9. The turbomachine according to claim 1, further comprising: a fuel inlet member mounted to the extruded fuel manifold, the fuel inlet member being fluidly connected to the fluid plenum. 10. A turbomachine combustor casing comprising: a flange, an outer surface and an inner surface that defines an internal passage, the flange extending radially outwardly from the outer surface of the casing; andan extruded fuel manifold mounted to the outer surface, the extruded fuel manifold including first and second walls integrally formed with a third, connecting, wall, the first wall including a first mounting element and the second wall including a second mounting element, the first mounting element extending axially along the combustor casing away from the first wall and the second mounting element extending axially along the combustor casing away from the second wall and the first mounting element, the extruded fuel manifold being joined to the outer surface of the combustor casing through the first and second mounting elements, the extruded fuel manifold defining a fuel plenum that extends radially about the combustor casing, wherein the extruded fuel manifold includes an anti-corrosive layer that is non-reactive with fuel. 11. The turbomachine combustor casing according to claim 10, wherein the anti-corrosive layer comprises at least one of stainless and a steel alloy including chromium. 12. The turbomachine combustor casing according to claim 10, wherein the extruded fuel manifold includes at least one mounting member, the at least one mounting member extending axially outward from one of the first and second walls at the third wall. 13. The turbomachine combustor casing according to claim 12, wherein the at least one mounting member is substantially co-planar with the third wall. 14. The turbomachine combustor casing according to claim 12, further comprising: a bridge member extending between the at least one mounting member and the flange, the bridge member, defining, at least in part, a passage that extends about the combustor casing. 15. The turbomachine combustor casing according to claim 10, wherein the extruded fuel manifold includes a first extrusion section and a second extrusion section, the first extrusion section being joined to the second extrusion section to form the extruded fuel manifold. 16. The turbomachine combustor casing according to claim 10, further comprising: at least one fluid passage formed in the combustor casing, the at least one fluid passage fluidly coupling the fuel plenum and the internal passage. 17. A method of forming a turbomachine combustor casing having an outer surface and an inner surface that defines an internal passage, a flange extending radially outwardly from the outer surface of the casing, the method comprising: extruding a fuel manifold having first and second walls integrally formed with a third wall, each of the first, second and third walls including an anti-corrosive layer, wherein a first mounting element is formed with the first wall, the first mounting element extending outward from an end portion of the first wall spaced from the third wall, and a second mounting element is formed with the second wall, the second mounting element extending outward from an end portion of the second wall spaced from the third wall, the second mounting element extending in a direction opposite the first mounting element; andmounting the fuel manifold to the outer surface of the casing through the first and second mounting elements, the first, second, and third walls forming a fuel plenum.

이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 1

Lin, Dechao; Kottilingam, Srikanth Chandrudu; Diao, Xiaoxue; Thomas, Nicholas. Component, gas turbine component and method of forming. USP20181110119473.

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Extruded fluid manifold for gas turbomachine combustor casing

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이 특허에 인용된 특허 (4)

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Extruded fluid manifold for gas turbomachine combustor casing

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이 특허에 인용된 특허 (4)

이 특허를 인용한 특허 피인용횟수: 1

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IPC 상세정보(version : 201201)

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