Combustor of a turbomachine including multiple tubular radial pathways arranged at multiple circumferential and axial locations
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/28
F23R-003/32
F23R-003/34
F23R-003/36
F23R-003/54
출원번호
US-0343510
(2012-01-04)
등록번호
US-9134031
(2015-09-15)
발명자
/ 주소
Nadkarni, Vaibhav
출원인 / 주소
General Electric Company
인용정보
피인용 횟수 :
0인용 특허 :
14
초록▼
A combustor of a turbomachine is provided and includes an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed, a ma
A combustor of a turbomachine is provided and includes an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed, a manifold configured to be supplied with fuel and a tubular body defining a pathway along which the air is transmittable in a third direction from the annulus to the interior, the third direction being transverse to the first and second directions. The tubular body includes a sidewall extendible through the manifold. The sidewall defines an injection hole within the manifold by which transmitted air is mixable with the fuel.
대표청구항▼
1. A combustor of a turbomachine, comprising: an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed;a manifold con
1. A combustor of a turbomachine, comprising: an assembly defining an interior and being configured to direct air to flow along an annulus in a first direction about the interior and in a second direction toward the interior, the first and second directions being substantially opposed;a manifold configured to be supplied with fuel; anda tubular body defining a pathway along which the air is transmittable in a third direction from the annulus to the interior, the third direction being transverse to the first and second directions,the tubular body including a sidewall extendible through the manifold, the sidewall defining an injection hole within the manifold by which transmitted air is mixable with the fuel. 2. The combustor according to claim 1, wherein an orientation of the tubular body has an axial component. 3. The combustor according to claim 1, wherein an orientation of the tubular body has a tangential component. 4. The combustor according to claim 1, wherein the tubular body comprises plural tubular bodies. 5. The combustor according to claim 4, wherein the plural tubular bodies are arranged at multiple axial stages. 6. The combustor according to claim 4, wherein the plural tubular bodies are arranged at multiple circumferential locations at one or more of multiple axial stages. 7. A combustor of a turbomachine, comprising: a center body defining an interior;a first vessel disposed about the center body and including a manifold configured to be supplied with a first fluid;a second vessel disposed about the first vessel to define an annulus for a flow of a second fluid in a first axial direction and a region in which the second fluid is redirected to flow toward the interior in a second axial direction opposite the first axial direction; anda tubular body defining a radial pathway along which the second fluid is transmittable from the annulus to the interior of the center body,the tubular body located axially downstream from the region and including a sidewall, which is extendible through the manifold, the sidewall defining an injection hole within the manifold by which the first fluid is mixable with transmitted second fluid. 8. The combustor according to claim 7, wherein the first fluid comprises fuel and the second fluid comprises air. 9. The combustor according to claim 7, further comprising a supply circuit fluidly coupled to the manifold for supplying the first fluid to the manifold. 10. The combustor according to claim 7, further comprising an end cover configured to direct the second fluid from the annulus to the center body. 11. A combustor of a turbomachine, comprising: a center body defining an interior;a first vessel disposed about the center body and including a manifold configured to be supplied with a first fluid;a second vessel disposed about the first vessel to define an annulus for a flow of a second fluid;a tubular body defining a radial pathway along which the second fluid is transmittable from the annulus to the interior of the center body, the tubular body including a sidewall, which is extendible through the manifold, the sidewall defining an injection hole within the manifold by which the first fluid is mixable with transmitted second fluid; andan end cover configured to direct the second fluid from the annulus to the center body, wherein the center body comprises:an aft portion through which the tubular body is extendible; anda forward portion disposed at a forward end of the aft portion and defining a central pathway for a flow of the second fluid from the end cover to the interior of the center body. 12. The combustor according to claim 11, wherein the end cover is further configured to direct the second fluid from the annulus toward the aft portion. 13. The combustor according to claim 11, wherein the aft portion comprises one or more of thermal barrier coating (TBC) and turbulators. 14. The combustor according to claim 11, wherein the aft portion is formed to define effusion holes. 15. The combustor according to claim 11, further comprising a swirler disposed within the forward portion, the forward portion being receptive of the first fluid. 16. The combustor according to claim 7, wherein an orientation of the tubular body has at least one of an axial component and a tangential component. 17. The combustor according to claim 7, wherein the tubular body comprises plural tubular bodies. 18. The combustor according to claim 17, wherein the plural tubular bodies are arranged at multiple axial stages. 19. The combustor according to claim 17, wherein the plural tubular bodies are arranged at multiple circumferential locations at one or more of multiple axial stages. 20. A combustor of a turbomachine, comprising: an end cover;a center body disposed proximate to the end cover and defining an interior;a first vessel disposed about the center body and including a manifold configured to be supplied with a first fluid;a second vessel coupled to the end cover and disposed about the first vessel to define an annulus for sequential flows of a second fluid toward the end cover in a first axial direction, along the end cover in a radial direction and toward the interior of the center body in a second axial direction opposite the first axial direction; anda tubular body defining a radial pathway along which the second fluid is transmittable from the annulus to the interior of the center body,the tubular body including a sidewall, which is extendible through the manifold, the sidewall defining an injection hole within the manifold by which the first fluid is mixable with transmitted second fluid, andthe tubular body being located axially downstream from a region in which the second fluid flows in the radial direction and is directed to flow in the second axial direction.
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