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US 8,037,689 B2Granted
Turbine fuel delivery apparatus and system
AssigneeGeneral Electric Company
InventorsSergey Adolfovich Oskin, Mark Allan Hadley, Joel Meador Hall, Sergey Konstantinovich Yerokhin, Sergey Anatolievich Meshkov
Life of this patent
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Abstract
A fuel nozzle for a turbine is disclosed. The fuel nozzle includes a housing, a plurality of fuel passages disposed within the housing, and a plurality of air passages disposed within the housing. A total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.
Claims21
A fuel nozzle for a turbine, the fuel nozzle comprising:
- a housing;
- a plurality of fuel passages disposed within the housing, each fuel passage having an opening, whereby fuel flows through each of the fuel passages and each of the respective openings in predominantly axial and circumferential directions;
- and
- a plurality of air passages disposed within the housing, each air passage having an opening, whereby air flows through each of the air passages and each of the respective openings in predominantly axial and circumferential directions,
- wherein each fuel passage of the plurality of fuel passages is disposed between two consecutive air passages of the plurality of air passages, and
- wherein a total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.
3 more elements
A combustor for a turbine, the combustor comprising:
- an outer liner and an inner liner defining a combustion chamber therebetween;
- and
- a plurality of fuel nozzles in fluid communication with the combustion chamber;
- wherein each fuel nozzle of the plurality of fuel nozzles comprises:
- a housing;
- a plurality of fuel passages disposed within the housing, each fuel passage having an opening, whereby fuel flows through each of the fuel passages and each of the respective openings in predominantly axial and circumferential directions;
- and
- a plurality of air passages disposed within the housing, each air passage having an opening, whereby air flows through each of the air passages and each of the respective openings in predominantly axial and circumferential directions,
- wherein each fuel passage of the plurality of fuel passages is disposed between two consecutive air passages of the plurality of air passages, and
- wherein a total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages.
7 more elements
A fuel nozzle for a turbine, the fuel nozzle comprising:
- a housing;
- a plurality of fuel passages disposed circumferentially within the housing, each fuel passage having an opening, whereby fuel flows through each of the fuel passages and each of the respective openings in predominantly axial and circumferential directions;
- and
- a plurality of air passages disposed circumferentially within the housing, each air passage having an opening, whereby air flows through each of the air passages and each of the respective openings in predominantly axial and circumferential directions,
- wherein a total flow area of the plurality of fuel passages is substantially equal to a total flow area of the plurality of air passages,
- wherein each fuel passage of the plurality of fuel passages is disposed between two consecutive air passages of the plurality of air passages;
- and
- wherein each air passage of the plurality of air passages is disposed adjacent to and between two fuel passages of the plurality of fuel passages, thereby providing an adjacent alternating arrangement of each air passage of the plurality of air passages and each fuel passage of the plurality of fuel passages.
5 more elements
Dependencies are inferred from the claim text.