Fuel nozzle for a gas turbine engine and method for fabricating the same
First Claim
1. A method for fabricating a secondary fuel nozzle assembly, said method comprising:
- providing a nozzle portion defining a passageway configured to supply fuel;
operatively coupling at least one peg in fuel flow communication with the passageway, the at least one peg extending radially outward from the nozzle portion and defining at least one opening configured to direct a flow of fuel in a substantially upstream direction; and
positioning a disc about the nozzle portion upstream of the at least one peg, the disc positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization.
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Accused Products
Abstract
A method for fabricating a secondary fuel nozzle assembly includes providing a nozzle portion defining a passageway configured to supply fuel. At least one peg is operatively coupled in fuel flow communication with the passageway. The at least one peg extends radially outward from the nozzle portion and defines at least one opening configured to direct a flow of fuel in a substantially upstream direction. A disc is positioned about the nozzle portion upstream of the at least one peg. The disc is positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization.
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Citations
19 Claims
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1. A method for fabricating a secondary fuel nozzle assembly, said method comprising:
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providing a nozzle portion defining a passageway configured to supply fuel; operatively coupling at least one peg in fuel flow communication with the passageway, the at least one peg extending radially outward from the nozzle portion and defining at least one opening configured to direct a flow of fuel in a substantially upstream direction; and positioning a disc about the nozzle portion upstream of the at least one peg, the disc positioned in communication with the at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization. - View Dependent Claims (2, 3, 4, 5)
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6. A secondary fuel nozzle assembly comprising:
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a nozzle portion; at least one peg extending radially outward from said nozzle portion, said at least one peg defining at least one opening configured to direct a flow of fuel in a substantially upstream direction; and a disc positioned about said nozzle portion upstream of said at least one peg, said disc positioned in flow communication with the said at least one opening and configured to interfere with the flow of fuel to facilitate fuel atomization. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13)
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14. A combustor assembly for use with a gas turbine engine, said combustor assembly comprising:
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a combustor liner defining a primary combustion zone and a secondary combustion zone, said combustor liner configured to direct a flow of combustion gases substantially in a downstream direction; a primary fuel nozzle assembly extending into said primary combustion zone; and a secondary fuel nozzle assembly extending through said primary combustion zone and into said secondary combustion zone, said secondary fuel nozzle assembly comprising; a nozzle portion; at least one peg extending radially outward from said nozzle portion, said at least one peg defining at least one opening configured to direct a flow of fuel in an upstream direction opposing the downstream direction; and a disc positioned about said nozzle portion upstream of said at least one peg, said disc configured to interfere with the flow of fuel to facilitate fuel atomization. - View Dependent Claims (15, 16, 17, 18, 19)
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Specification