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US 10,830,445 B2Granted
Liquid fuel nozzles for dual fuel combustors
AssigneeGeneral Electric Company
InventorsBorys Shershnyov, Geoffrey David Myers, Alexey Yurievich Gerasimov, Michael Draisey
Life of this patent
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Abstract
A nozzle for a combustor is disclosed. The nozzle may include a main fuel passage (202), a number of radial fuel ports (206) in communication with the main fuel passage, a prefilmer surface (212) in communication with the radial fuel ports, and a main purge air passage (218) in communication with the radial fuel ports and the prefilmer surface.
Claims20
A liquid fuel nozzle for a dual fuel combustor, the nozzle comprising:
- an axial centerline, wherein a radial direction extends outwardly from, and perpendicular to, the axial centerline;
- a main fuel passage;
- a main purge air passage disposed outward along the radial direction from the main fuel passage, the main purge air passage comprising a first outlet and a plurality of second outlets;
- a prefilmer surface diverging outward along the radial direction from a first end to a second end, wherein the first outlet is proximate the first end and the plurality of second outlets are proximate the second end;
- a radial lip spaced apart from the prefilmer surface, wherein the radial lip extends beyond the first outlet and the first end and terminates at a free end;
- a plurality of radial fuel ports positioned axially between the first outlet and the radial lip, wherein the plurality of radial fuel ports extend between the main fuel passage and the main purge air passage, wherein the radial lip is configured to direct a flow of liquid fuel exiting the radial fuel ports into the prefilmer surface.
3 more elements
A gas turbine engine, comprising:
- a compressor;
- a turbine;
- and
- a combustor disposed downstream from the compressor and upstream from the turbine, the combustor including a nozzle disposed within the combustor, the nozzle comprising:
- an axial centerline, wherein a radial direction extends outwardly from, and perpendicular to, the axial centerline;
- a main fuel passage;
- a main purge air passage disposed outward along the radial direction from the main fuel passage, the main purge air passage comprising a first outlet and a plurality of second outlets;
- a prefilmer surface diverging outward along the radial direction from a first end to a second end, wherein the first outlet is proximate the first end and the plurality of second outlets are proximate the second end;
- a radial lip spaced apart from the prefilmer surface, beyond the first outlet and the first end and terminates at a free end;
- a plurality of radial fuel ports positioned axially between the first outlet and the radial lip, wherein the plurality of radial fuel ports extend between the main fuel passage and the main purge air passage, wherein the radial lip is configured to direct a flow of liquid fuel exiting the radial fuel ports into the prefilmer surface.
7 more elements
Dependencies are inferred from the claim text.