Fuel nozzle for a turbine combustor, and methods of forming same
AssigneeGeneral Electric Company
InventorsPraveen Babulal Jain, Narayan Subramanian
Life of this patent
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Abstract
A fuel nozzle for a turbine engine includes a primary fuel passageway for supplying fuel to a plurality of radially extending fuel injectors arranged around the exterior of the fuel nozzle. A secondary fuel passageway couples an upstream end of the primary fuel passageway to a downstream end of the primary fuel passageway. The secondary fuel passageway acts as a resonator tube to help reduce oscillations in the fuel flowing through the primary fuel passageway.
Claims20
A fuel nozzle for a turbine engine, comprising:
- an exterior wall;
- a plurality of radially extending fuel injectors formed on the exterior wall and extending outward away from the exterior wall, where at least one fuel delivery port is formed on each fuel injector;
- a generally annular shaped primary fuel passageway formed inside the exterior wall and configured to deliver fuel to the fuel injectors;
- and
- a secondary fuel passageway located closer to a central longitudinal axis of the fuel nozzle than the primary fuel passageway, wherein the secondary fuel passageway receives fuel from a first portion of the primary fuel passageway and delivers fuel back into a second portion of the primary fuel passageway at a location that is downstream from the first portion and upstream of the radially extending fuel injectors.
A fuel nozzle for a turbine engine, comprising:
- an exterior wall;
- a plurality of radially extending fuel injectors formed on the exterior wall and extending outward away from the exterior wall, where at least one fuel delivery port is formed on each fuel injector;
- a plurality of primary fuel passageways that extend down a length of the nozzle, wherein the primary fuel passageways are positioned along an inner side of the exterior wall, and wherein the primary fuel passageways deliver fuel to the fuel injectors;
- and
- a plurality of secondary fuel passageways, wherein each secondary fuel passageway is located closer to a central longitudinal axis of the fuel nozzle than the primary fuel passageways, and wherein each secondary fuel passageway receives fuel from a first portion of a corresponding primary fuel passageway and delivers fuel back into a second portion of its corresponding primary fuel passageway at a location that is downstream from the first portion and upstream of the radially extending fuel injectors.
A method of forming a fuel nozzle for a turbine engine, comprising:
- forming a plurality of radially extending fuel injectors that extend outward from an exterior wall, where at least one fuel delivery port is formed on each fuel injector;
- forming at least one primary fuel passageway along an inner side of the exterior wall, wherein the at least one primary fuel passageway delivers fuel to at least one of the fuel injectors;
- and
- forming at least one secondary fuel passageway on a portion of the fuel nozzle that is located closer to a central longitudinal axis of the fuel nozzle than a corresponding primary fuel passageway, wherein each at least one secondary fuel passageway receives fuel from a first portion of a corresponding primary fuel passageway and delivers fuel back into a second portion of the corresponding primary fuel passageway at a location that is downstream from the first portion and upstream of the radially extending fuel injectors.
Dependencies are inferred from the claim text.