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US 8,136,359 B2Granted
Gas turbine fuel nozzle having improved thermal capability
AssigneePower Systems Mfg., LLC
InventorsPeter Stuttaford, Paul Economo, Khalid Oumejjoud, Max Dufflocq, Hany Rizkalla
Life of this patent
Estimating the term…
Abstract
Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.
Claims12
A fuel nozzle for a gas turbine engine comprising:
- an inner tubular member coaxial with a centerline, the inner tubular member having a centermost passage;
- an intermediate tubular member surrounding the inner tubular member and having a corrugated bellows portion, the intermediate tubular member and inner tubular member forming a secondary passage therebetween;
- an outer tubular member surrounding the intermediate tubular member such that the outer tubular member and the intermediate tubular member form an outer passage therebetween;
- a plurality of injectors extending radially outward from the outer passage;
- and,
- a base coupled to at least the outer tubular member and the intermediate tubular member, the base comprises a plurality of feed holes oriented at an angle relative to the centerline and extending to a surface of the base within the gas turbine combustor for directing compressed air received from within a gas turbine combustor directly to the secondary passage so as to elevate a temperature of the intermediate tubular member to reduce thermal gradients in the fuel nozzle.
3 more elements
A gas turbine combustor comprising:
- a combustion liner having a center axis;
- a cap assembly positioned adjacent the combustion liner, the cap assembly having a central opening located along the center axis and a plurality of openings located in an annular array about the center axis;
- an end cover positioned adjacent the cap assembly, the end cover having a plurality of fuel nozzles fixed to the end cover with each fuel nozzle corresponding to an opening, such that a first fuel nozzle is positioned along the center axis and a plurality of second fuel nozzles are positioned in an annular array about the center axis;
- wherein the first fuel nozzle comprises a solid inner tubular member having a centermost passage, a solid outer tubular member surrounding the inner tubular member thereby forming an outer passage between the inner tubular member and the outer tubular member, a plurality of fuel injectors extending radially outward from the outer passage, and a base coupled to the inner and outer tubular member and having openings for directing compressed air from within the combustion liner directly to the centermost passage so as to elevate a temperature of the inner tubular member;
- and,
- wherein the plurality of second fuel nozzles comprises an inner tubular member located coaxial with a centerline, the inner tubular member having a centermost passage, an intermediate tubular member surrounding the inner tubular member, the secondary tubular member having a cylindrical portion and a corrugated bellows portion forming a secondary passage between the inner tubular member and intermediate tubular member, an outer tubular member surrounding the secondary tubular member and forming an outer passage between the intermediate tubular member and the outer tubular member, a plurality of fuel injectors extending radially outward from the outer passage, and a base coupled to at least the outer tubular member and the intermediate tubular member and having a plurality of feed holes oriented at an angle relative to the centerline and extending to a surface of the base within the gas turbine combustor for directing compressed air from within the combustion liner directly to the intermediate tubular member for elevating a temperature of the intermediate tubular member.
3 more elements
Dependencies are inferred from the claim text.