IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0754813
(2010-04-06)
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등록번호 |
US-8418468
(2013-04-16)
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발명자
/ 주소 |
- McMahan, Kevin Weston
- Valeev, Almaz
- Wu, Chunyang
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
21 |
초록
▼
A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that i
A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.
대표청구항
▼
1. A combustor section, comprising: a segmented annular quaternary fuel manifold mounted at a location defined axially upstream from a fuel nozzle support relative to a combustor centerline axis, the segmented annular manifold being mounted in a section of a passage through which an oxidizer flows,t
1. A combustor section, comprising: a segmented annular quaternary fuel manifold mounted at a location defined axially upstream from a fuel nozzle support relative to a combustor centerline axis, the segmented annular manifold being mounted in a section of a passage through which an oxidizer flows,the passage being defined such that the oxidizer flows through the passage in a reverse direction radially outwardly of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle support,the segmented annular manifold being located in a section of the passage in which the oxidizer flows in the reverse direction at a local velocity that exceeds oxidizer flow velocities in other sections of the passage,each segment of the manifold being substantially axially aligned with one another and including a body to accommodate fuel internally, the body being formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows, the fuel injection occurring axially upstream of the fuel nozzle support. 2. The combustor section according to claim 1, further comprising a casing and a cap assembly, the casing surrounding the segmented annular manifold and the cap assembly being located radially inwardly of the casing and including the fuel nozzle support, which is provided as one of a plurality of fuel nozzle supports, wherein the section of the passage through which an oxidizer flows is radially interposed between the casing and the cap assembly of a combustor. 3. The combustor section according to claim 2, further comprising an annular baffle extending axially from the cap assembly to surround the plurality of fuel nozzle supports, wherein the section of the passage in which the segmented annular manifold is located is radially interposed between the casing and the baffle. 4. The combustor section according to claim 1, wherein each segment defines an internal volume, and wherein a sum total volume of the segmented manifold accommodates up to about 30% by mass of available fuel of the combustor. 5. The combustor section according to claim 4, wherein an amount of the available fuel accommodated within each segment is one of fixed and actively controlled. 6. The combustor section according to claim 1, wherein the injection holes are perimetrically arrayed at each segment. 7. The combustor section according to claim 1, wherein each of the bodies comprises a segmented ring-shaped casing having first and second opposing sides, at least one of which is tapered. 8. The combustor section according to claim 1, wherein the segmented annular manifold comprises one or more segments that is plural in number such that, for each of the plural manifold segments, one segment is radially outward of another one of the plural manifold segments. 9. The combustor section according to claim 8, wherein the one or more of the segments are fueled independently with differing fuels, diluents, and/or steam. 10. The combustor section according to claim 1, further comprising: at least one fuel source; andat least one supply line coupled to the at least one fuel source by which fuel is supplied from the fuel source to at least one of the segments of the manifold. 11. The combustor section according to claim 1, wherein the axial location upstream from the fuel nozzle support is defined as an axial location that is axially interposed between an axial location of the fuel nozzle support and an axial location at which the air and/or the fuel/air mixture changes from flowing in the reverse direction to flowing in the forward direction. 12. A combustor section, comprising: a casing;a cap assembly, having a fuel nozzle support formed therein, the cap assembly being disposed within the casing to define an annular passage between the casing and the cap assembly through which oxidizer flows in a reverse direction, then in a radially inward direction and then in a forward direction opposite the reverse direction upstream from the fuel nozzle support; anda segmented annular quaternary fuel manifold mounted within a section of the passage at which the oxidizer flows in the reverse direction, the segmented annular manifold being mounted at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis, each of the segments being substantially axially aligned with one another and including a body in which fuel is accommodated and injection holes through which the fuel is injected into the passage section. 13. The combustor section according to claim 12, wherein the casing comprises: first and second flanges; anda quaternary fuel distribution manifold axially interposed between the first and second flanges and substantially axially aligned with the segmented annular manifold, the quaternary fuel distribution manifold being configured to supply fuel to the segmented annular manifold. 14. The combustor section according to claim 13, further comprising at least one or more fuel line flanges, wherein each fuel line flange supplies to one or more of the segments a same or different fuel as another fuel line flange. 15. An annular fuel manifold of a combustor, the combustor including a casing; and a cap assembly disposed within the casing to define an annular passage through which oxidizer flows in a reverse direction, then in a radially inward direction and then in a forward direction opposite the reverse direction upstream from a fuel nozzle support, the annular fuel manifold comprising: a segmented annular body, each body segment being substantially axially aligned with one another, formed to accommodate fuel therein, and formed to define fuel injection holes by which the fuel is injected into a section of the passage at which the oxidizer flows in the reverse direction at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis. 16. The annular fuel manifold according to claim 15, wherein the segmented annular body is segmented into two or more body segments having substantially uniform circumferential lengths and being separated from one another by substantially uniform spacing. 17. The annular fuel manifold according to claim 15, wherein each body segment is coupled to a same or different fuel source as another of the body segments. 18. The annular fuel manifold according to claim 15, wherein the segmented annular body is tapered. 19. The annular fuel manifold according to claim 15, wherein the fuel injection holes are disposed at a downstream portion of the segmented annular body. 20. The annular fuel manifold according to claim 15, wherein the fuel injection holes are arrayed with at least one of substantially uniform and non-uniform spacing along the segmented annular body, and wherein the fuel is injected in radially inward and radially outward directions relative to a combustor centerline axis. 21. The annular fuel manifold according to claim 15, wherein multiple segmented annular fuel manifolds are provided in a gas turbine engine. 22. A combustor section, comprising: a segmented manifold configured for quaternary fuel injection into a combustor, the segmented manifold being mounted at a location defined axially upstream from a fuel nozzle support relative to a combustor centerline axis in a section of a passage through which an oxidizer flows, the passage being defined such that the oxidizer flows through the passage in a reverse direction radially outwardly of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle supporteach segment of the manifold being substantially axially aligned with one another and including a body to accommodate fuel internally,the bodies together defining the segmented manifold having a shape similar to a shape of the passage section at an axial location of the body and wherein each body is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows, the fuel injection occurring axially upstream of the fuel nozzle support. 23. The combustor section according to claim 22, wherein the passage section is annular and the shape of the segmented manifold is annular. 24. The combustor section according to claim 22, wherein the passage section and the shape of each of the bodies in the segmented manifold are angular. 25. The combustor section according to claim 22, wherein the passage section and the shape of each of the bodies in the segmented manifold are rectangular. 26. A combustor section, comprising: a casing;a cap assembly, having a fuel nozzle support formed therein, the cap assembly being disposed within the casing to define a passage between the casing and the cap assembly through which oxidizer flows upstream from the fuel nozzle support, the oxidizer flows through the passage in a reverse direction radially outward of the fuel nozzle support and in a forward direction radially aligned with the fuel nozzle support; anda segmented manifold mounted within a section of the passage at which the oxidizer flows, the segmented manifold being mounted at a location defined axially upstream from the fuel nozzle support relative to a combustor centerline axis, each of the segments being substantially axially aligned with one another and including a body in which fuel is accommodated,the bodies together defining a segmented manifold having a shape similar to a shape of the passage section at an axial location of the body and each body defining injection holes through which the fuel is injected into the passage section, the fuel injection occurring axially upstream of the fuel nozzle support. 27. The combustor section according to claim 26, wherein the passage section is annular and the shape of the segmented manifold is annular. 28. The combustor section according to claim 26, wherein the passage section and the shape of each of the bodies in the segmented manifold are angular. 29. The combustor section according to claim 26, wherein the passage section and the shape of each of the bodies in the segmented manifold are rectangular.
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