Combustor assembly for a turbine engine
AssigneeGeneral Electric Company
InventorsGregory Allen Boardman, Pradeep Naik, Allen Michael Danis
Life of this patent
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Abstract
A rich-quench-lean combustor assembly for a gas turbine engine includes a fuel nozzle and a dome, the fuel nozzle attached to the dome. The combustor assembly additionally includes a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber. Additionally, the liner extends between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and aft end and defines a forward section extending from the quench air jets to the dome. The dome and the forward section of the liner are configured to be cooled substantially by one or both of impingement cooling or convective cooling.
Claims20
A rich-quench-lean combustor assembly for a gas turbine engine defining an axial direction and a circumferential direction, the combustor assembly comprising:
- a fuel nozzle;
- a dome, the fuel nozzle attached to the dome;
- and
- a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber, the liner extending between a forward end and an aft end, the liner comprising a plurality of quench air jets positioned between the forward end and aft end and defining a forward section extending from the quench air jets to the dome, the dome and the forward section of the liner configured to be cooled substantially by one or both of impingement cooling or convective cooling.
A gas turbine engine defining an axial direction and a circumferential direction, the gas turbine engine comprising:
- a compressor section and a turbine section arranged in serial flow order;
- and
- a rich-quench-lean combustor assembly positioned between the compressor section and the turbine section, the combustor assembly comprising:
- a fuel nozzle;
- a dome, the fuel nozzle attached to the dome;
- and
- a liner attached to or formed integrally with the dome, the liner and the dome together defining at least in part a combustion chamber, the liner extending between a forward end and an aft end, the liner comprising a plurality of quench air jets positioned between the forward end and aft end and defining a forward section extending from the quench air jets to the dome, the dome and the forward section of the liner configured to be cooled substantially by one or both of impingement cooling or convective cooling.
Dependencies are inferred from the claim text.