Staged fuel and air injection in combustion systems of gas turbines
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F23R-003/34
F01D-005/18
F02C-007/22
F02C-007/12
F23R-003/00
F23R-003/16
F01D-009/02
F01D-009/06
출원번호
US-0978038
(2015-12-22)
등록번호
US-9995221
(2018-06-12)
발명자
/ 주소
Hughes, Michael John
Berry, Jonathan Dwight
출원인 / 주소
General Electric Company
대리인 / 주소
Henderson, Mark E.
인용정보
피인용 횟수 :
0인용 특허 :
18
초록▼
A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath; a compressor discharge cavity; a staged injector; stator blade airfoils extending between inboard and outboard sidewalls; and a first and second coolant flowpath. The first coolant flowpath i
A gas turbine that includes: a combustor coupled to a turbine that together define a working fluid flowpath; a compressor discharge cavity; a staged injector; stator blade airfoils extending between inboard and outboard sidewalls; and a first and second coolant flowpath. The first coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the inboard sidewall; an outtake section including a downstream port connected to the staged injector and an upstream port formed through the outboard sidewall; and a cooling circuit through the airfoil. The second coolant flowpath includes: an intake section connected to the compressor discharge cavity and a downstream port formed through the outboard sidewall; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the inboard sidewall; and a cooling circuit through the airfoil.
대표청구항▼
1. A gas turbine that comprises: a combustor coupled to a turbine that together define a working fluid flowpath, the working fluid flowpath extending aftward along a longitudinal axis from a forward end defined by a forward injector in the combustor, through an interface at which the combustor conne
1. A gas turbine that comprises: a combustor coupled to a turbine that together define a working fluid flowpath, the working fluid flowpath extending aftward along a longitudinal axis from a forward end defined by a forward injector in the combustor, through an interface at which the combustor connects to the turbine, and then through the turbine to an aftward end defined therein;a compressor discharge cavity formed about the working fluid flowpath for receiving a combustor air supply delivered thereto by a compressor;a staged injection system that includes the forward injector and, axially spaced aftward therefrom along the longitudinal axis of the working fluid flowpath, a staged injector;a stator blade positioned within a row of circumferentially spaced stator blades in the turbine, the stator blade comprising an airfoil extending across the working fluid flowpath between an inboard sidewall and an outboard sidewall;fuel directing structure configured to apportion a combustor fuel supply between the forward injector and the staged injector; andair directing structure for apportioning the combustor air supply between the forward injector and the staged injector;wherein the air directing structure includes at least two one-way continuous coolant flowpaths, a first coolant flowpath and a second coolant flowpath;wherein the first coolant flowpath includes: an intake section that comprises an upstream port that is fluidly coupled to the compressor discharge cavity and a downstream port that is formed through the inboard sidewall;an outtake section that comprises a downstream port that is fluidly coupled to the staged injector and an upstream port formed through the outboard sidewall; anda cooling circuit extending through an interior of the airfoil of the stator blade and connecting the intake section to the outtake section, wherein the cooling circuit comprises an upstream end that connects to the downstream port of the intake section and a downstream end that connects to the upstream port of the outtake section;wherein the second coolant flowpath comprises: an intake section that comprises an upstream port that is fluidly coupled to the compressor discharge cavity and a downstream port that is formed through the outboard sidewall;an outtake section that comprises a downstream port that is fluidly coupled to the staged injector and an upstream port formed through the inboard sidewall; anda cooling circuit extending through an interior of the airfoil of the stator blade and connecting the intake section to the outtake section, wherein the cooling circuit comprises an upstream end that connects to the downstream port of the intake section and a downstream end that connects to the upstream port of the outtake section; andwherein the cooling circuits of the first and the second coolant flowpaths together comprise a crisscrossing configuration within the airfoil of the stator blade. 2. The gas turbine according to claim 1, wherein: the row of stator blades comprises a forward most row of stator blades in the turbine;the downstream port of the intake section of the first coolant flowpath and the upstream port of the outtake section of the second coolant flowpath are each formed through the inboard sidewall; andthe downstream port of the intake section of the second coolant flowpath and the upstream port of the outtake section of the first coolant flowpath are each formed through the outboard sidewall. 3. The gas turbine according to claim 2, further comprising a flow annulus surrounding the working fluid flowpath; wherein, positioned within the flow annulus, are a first axial partition and a second axial partition;wherein the intake section of the first coolant flowpath and the outtake section of the second coolant flowpath comprise adjacent axial sections of the flow annulus residing to each side of the first axial partition, the first axial partition configured to fluidly seal each from the other; andwherein the intake section of the second coolant flowpath and the outtake section of the first coolant flowpath comprise adjacent axial sections of the flow annulus residing to each side of the second axial partition, the second axial partition configured to fluidly seal each from the other. 4. The gas turbine according to claim 3, wherein the first axial partition and the second axial partition are positioned within an axial range defined between a leading edge and a trailing edge of the stator blade. 5. The gas turbine according to claim 3, wherein the staged injector intersects the flow annulus so to attain an injection point within the working fluid flowpath; and wherein, relative an axial position of the injection point, a forward annulus section is defined to a forward side of the injection point, and an aftward annulus section is defined to an aftward side of the injection point;further comprising a third axial partition positioned in the flow annulus so to axially coincide with the staged injector;wherein the third axial partition is configured for fluidly sealing the forward annulus section from the aftward annulus section such that: substantially all of the air of the combustor air supply flowing into the forward annulus section is directed to the forward injector; andsubstantially all of the air of the combustor air supply flowing into the aftward annulus section is directed to the staged injector. 6. The gas turbine according to claim 1, further comprising a flow annulus surrounding the working fluid flowpath; wherein a flowpath wall defines the working fluid flowpath, the flowpath wall having a hot side, which faces the working fluid flowpath, and, opposite the hot side, a cold side, which faces the flow annulus; andwherein an annulus wall surrounds and is offset from the flowpath wall so to form the flow annulus therebetween, the annulus wall having a hot side, which faces the flow annulus, and a cold side, which fluidly communicates with the compressor discharge cavity. 7. The gas turbine according to claim 6, wherein the upstream port of the intake sections of the first coolant flowpath and the second coolant flowpath comprises openings formed through corresponding sections of the annulus wall for allowing a portion of the combustor air supply entry into the intake sections; and wherein the openings are configured for metering the portion of the combustor air supply flowing to the staged injector relative a remaining portion of the combustor air supply flowing to the forward injector. 8. The gas turbine according to claim 7, wherein: within the turbine: the flowpath wall comprises an inboard flowpath wall that defines an inboard boundary of the working fluid flowpath and an outboard flowpath wall that defines an outboard boundary of the working fluid flowpath; andthe flow annulus comprises an inboard flow annulus and an outboard flow annulus, and the annulus wall comprises an inboard annulus wall and an outboard annulus wall, wherein the inboard sidewall and the outboard sidewall comprise, respectively, axial sections of the inboard flowpath wall and the outboard flowpath wall;the inboard annulus wall is offset from the inboard flowpath wall so to form the inboard flow annulus therebetween; andthe outboard annulus wall is offset from the outboard flowpath wall so to form the outboard flow annulus therebetween; andwithin the combustor: the flowpath wall comprises an inner radial wall; andthe annulus wall comprises an outer radial wall formed about the inner radial wall, the inner radial wall and the outer radial wall concentrically arranged about the longitudinal axis of the working fluid flowpath. 9. The gas turbine according to claim 8, further comprising a first axial partition and a second axial partition positioned within the flow annulus, wherein the first axial partition is positioned within the inboard flow annulus and the second axial partition is positioned within the outboard flow annulus; wherein: the intake section of the first coolant flowpath and the outtake section of the second coolant flowpath comprise adjacent axial sections of the inboard flow annulus residing to each side of the first axial partition, the first axial partition configured to fluidly seal each from the other; andthe intake section of the second coolant flowpath and the outtake section of the first coolant flowpath comprise adjacent axial sections of the flow annulus residing to each side of the second axial partition, the second axial partition configured to fluidly seal each from the other. 10. The gas turbine according to claim 9, wherein the first axial partition and the second axial partition are each positioned within an axial range defined between a leading edge and a trailing edge of the stator blade. 11. The gas turbine according to claim 10, wherein: the intake section of the first coolant flowpath resides to an aftward side of the first axial partition and the outtake section of the second coolant flowpath resides to a forward side of the first axial partition; andthe intake section of the second coolant flowpath resides to an aftward side of the second axial partition and the outtake section of the first coolant flowpath resides to a forward side of the second axial partition. 12. The gas turbine according to claim 10, wherein the staged injector is positioned within the combustor, the staged injector being formed through the inner radial wall for enabling injection of a fuel and air mixture into the working fluid flowpath. 13. The gas turbine according to claim 10, wherein the staged injector is positioned within the turbine. 14. The gas turbine according to claim 13, wherein the airfoil comprises integrally formed sidewalls, in which an inboard sidewall defines an inboard boundary of the working fluid flowpath and an outboard sidewall defines an outboard boundary of the working fluid flowpath; and wherein the staged injector is formed through at least one of the inboard sidewall and the outboard sidewall. 15. The gas turbine according to claim 14, wherein the sidewalls of the stator blade are elongated forward such that each extends to the interface between the combustor and the turbine. 16. The gas turbine according to claim 10, further comprising: surface ports formed through an outer surface of the airfoil of the stator blade; andconnector channels branching from at least one of the cooling circuits of the first coolant flowpath and the second coolant flowpath for fluidly coupling the surface ports to at least one of the cooling circuits. 17. The gas turbine according to claim 10, wherein: the upstream port of the intake section of the first coolant flowpath comprises impingement ports formed through the inboard annulus wall, each of the impingement ports configured for training an impinged jet of the air entering the inboard flow annulus therethrough against the cold side of the inboard flowpath wall; andthe upstream port of the intake section of the second coolant flowpath comprises impingement ports formed through the outboard annulus wall, each of the impingement ports configured for training an impinged jet of the air entering the outboard flow annulus therethrough against the cold side of the outboard flowpath wall. 18. The gas turbine according to claim 10, wherein the staged injector includes a first staged injector and a second staged injector, both of which reside in the turbine such that the first staged injector is formed through the outboard flowpath wall and the second staged injector is formed through the inboard flowpath wall. 19. The gas turbine according to claim 18, wherein the first staged injector and the second staged injector each comprises a nozzle extending through the flow annulus between the flow annulus wall and the flowpath wall; wherein the downstream port of the outtake section of the first coolant flowpath comprises an opening in the nozzle of the first staged injector, and the downstream port of the outtake section of the second coolant flowpath comprises an opening in the nozzle of the second staged injector; andwherein the outboard annulus wall corresponding to the outtake section of the first coolant flowpath comprises separating structure that fluidly isolates flow therethrough from flow in compressor discharge cavity, and the inboard annulus wall corresponding to the outtake section of the second coolant flowpath comprises separating structure that fluidly isolates flow therethrough from flow in the compressor discharge cavity. 20. The gas turbine according to claim 10, wherein the staged injector is axially spaced forward a predetermined distance relative to the stator blade; and wherein the predetermined distance that the staged injector is spaced forward relative to the stator blade comprises one based on a residence criteria concerning a minimum time the fuel injected by the staged injector preferably resides in the working fluid flowpath before reaching the stator blade during an anticipated operating condition.
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