A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly
A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.
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1. A flowsleeve of a gas turbine combustor, the flowsleeve comprising: an annular body including an upstream casing and a downstream casing,the upstream casing defining a first fuel feed, a second fuel feed and a third fuel feed, andthe downstream casing defining a first airway opening and a second
1. A flowsleeve of a gas turbine combustor, the flowsleeve comprising: an annular body including an upstream casing and a downstream casing,the upstream casing defining a first fuel feed, a second fuel feed and a third fuel feed, andthe downstream casing defining a first airway opening and a second airway opening, and a first premixing passage and a second premixing passage,the first airway opening being disposed on a wall forming the first premixing passage, and the second airway opening being disposed on a wall forming the second premixing passage, andthe first fuel feed having a first fuel coupling with the first premixing passage, the second fuel feed having a second fuel coupling with the second premixing passage, the third fuel feed having a third fuel coupling with the first premixing passage and a fourth fuel coupling with the second premixing passage,the first and second premixing passages receive fuel and air, forming a fuel-air mixture, from their respective first, second and third fuel feeds and their respective first and second airway openings. 2. The flowsleeve according to claim 1, wherein the upstream casing and the downstream casing correspondingly define the first, second and third fuel feeds, the first and second airway openings, and the first and second premixing passages, respectively, at multiple circumferential locations. 3. The flowsleeve according to claim 2, wherein the first, second and third fuel feeds are defined at each of the multiple circumferential locations. 4. The flowsleeve according to claim 2, wherein the first and second airway openings and the first and second premixing passages are respectively defined at each of the multiple circumferential locations as respective pairs thereof. 5. The flowsleeve according to claim 1, wherein the first, second and third fuel feeds are oriented along an axial direction and the air provided from the first and second airway openings comprise compressor discharge air and flows through the first and second airway openings in an inward radial direction. 6. The flowsleeve according to claim 1, wherein the downstream casing defines each of the first and second airway openings with an elongate shape, which has an elongate length thereof oriented in a circumferential direction, a width of each of the first and second premixing passages being defined in the circumferential direction and being substantially similar to the elongate length of each of the first and second airway openings, respectively. 7. The flowsleeve according to claim 1, wherein the downstream casing further defines a plenum at a downstream end of the first and second premixing passages. 8. The flowsleeve according to claim 1, further comprising a manifold disposed about the upstream casing to define a fuel inlet coupled to the first, second and third fuel feeds. 9. The flowsleeve according to claim 1, wherein the downstream casing is welded to the upstream casing. 10. A gas turbine combustor, comprising: a first vessel having an upstream end defining a first interior in which combustion occurs and a downstream end defining a second interior through which products of combustion flow;a second vessel configured to be disposed about the downstream end of the first vessel,the second vessel defining a first fuel feed, a second fuel feed and a third fuel feed, a first airway opening and a second airway opening, and a first premixing passage and a second premixing passage,the first airway opening being disposed on a wall forming the first premixing passage, and the second airway opening being disposed on a wall forming the second premixing passage, andthe first fuel feed having a first fuel coupling with the first premixing passage, the second fuel feed having a second fuel coupling with the second premixing passage, the third fuel feed having a third fuel coupling with the first premixing passage and a fourth fuel coupling with the second premixing passage,the first and second premixing passages each having a passage interior in which fuel and air, receivable from the first, second and third fuel feeds and the first and second airway openings, respectively, are combinable to form a fuel-air mixture; andan injector coupled to the first and second premixing passages, and configured to transport the fuel-air mixture to the second interior. 11. The gas turbine combustor according to claim 10, wherein the first vessel and the second vessel define an annulus therebetween, which is traversed by the injector. 12. The gas turbine combustor according to claim 10, wherein the injector is plural in number, the plural injectors being arrayed about the second interior. 13. The gas turbine combustor according to claim 10, wherein each of the first, second and third fuel feeds is oriented along an axial direction and the air provided from the first and second airway openings comprise compressor discharge air and flows through the first and second airway openings in an inward radial direction. 14. The gas turbine combustor according to claim 10, wherein each of the first and second airway openings is defined with an elongate shape, which has an elongate length thereof oriented in a circumferential direction, a width of each of the first and second premixing passages being defined in the circumferential direction and being substantially similar to the elongate length of each of the first and second airway openings, respectively. 15. The gas turbine combustor according to claim 10, wherein the second vessel is formed to define a plenum at a downstream end of the first and second premixing passages, the injector being fluidly coupled to the plenum. 16. The gas turbine combustor according to claim 10, wherein the second vessel comprises: a downstream casing in which the first and second airway openings and the first and second premixing passages are defined;an upstream casing in which the first, second and third fuel feeds are defined; anda manifold disposed about the upstream casing to define a fuel inlet coupled to the first, second and third fuel feeds. 17. The gas turbine combustor according to claim 16, wherein the downstream casing is welded to the upstream casing. 18. A gas turbine combustor, comprising: a first vessel having an upstream end defining a first interior in which combustion occurs and a downstream end defining a second interior through which products of combustion flow;a second vessel configured to be disposed about the downstream end of the first vessel,the second vessel defining at multiple circumferential locations:a first fuel feed, a second fuel feed and a third fuel feed,a first airway opening and a second airway opening,a first premixing passage and a second premixing passage,the first airway opening being disposed on a wall forming the first premixing passage, and the second airway opening being disposed on a wall forming the second premixing passage, andthe first fuel feed having a first fuel coupling with the first premixing passage, the second fuel feed having a second fuel coupling with the second premixing passage, the third fuel feed having a third fuel coupling with the first premixing passage and a fourth fuel coupling with the second premixing passage,wherein each of the first, second, third and fourth fluid couplings being disposed downstream from the first and second airway openings, respectively,each of the first and second premixing passages having a passage interior in which fuel and air, receivable from the first, second and third fuel feeds, respectively, are combinable downstream from the first and second airway openings to form a fuel and air mixture, anda plenum at a downstream end of the premixing passage; andmultiple injectors, each of the multiple injectors being coupled to the plenum and configured to transport the fuel and air mixture to the second interior.
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