Combustor assembly for a turbine engine
AssigneeGeneral Electric Company
InventorsGregory Allen Boardman, Pradeep Naik, Allen Michael Danis
Life of this patent
Estimating the term…
Abstract
A rich-quench-lean combustor assembly for a gas turbine engine includes a liner extending between a forward end and an aft end. The liner includes a plurality of quench air jets positioned between the forward end and the aft end. The combustor assembly additionally includes a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber. A fuel nozzle is attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5.
Claims26
A rich-quench-lean combustor assembly for a gas turbine engine defining an axial direction, the combustor assembly comprising:
- a 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 the aft end;
- a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber;
- and
- a fuel nozzle attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5,
- wherein the plurality of quench air jets comprise a plurality of primary stage air jets and a plurality of secondary stage air jets, the plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction, at least one of the plurality of primary stage air jets defines an inlet having a generally elliptical shape, and at least one of the plurality of secondary stage air jets is an elongated slot.
(canceled)
A gas turbine engine defining an axial direction 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 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 the aft end;
- a dome attached to or formed integrally with the liner, the dome and the liner together defining at least in part a combustion chamber;
- and
- a fuel nozzle attached to the dome, the fuel nozzle configured as a premix fuel nozzle for providing a substantially homogenous mixture of fuel and air to the combustion chamber, the mixture of fuel and air having an equivalence ratio of at least 1.5,
- wherein the plurality of quench air jets comprise a plurality of primary stage air jets and a plurality of secondary stage air jets, the plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction, at least one of the plurality of primary stage air jets defines on inlet having a generally elliptical shape, and at least one of the plurality of secondary stage air jets is on elongated slot.
A method for operating a combustor assembly of a gas turbine engine, the combustor assembly comprising a liner attached to or formed integrally with a dome, the liner comprising a plurality of quench air jets and the dome comprising a fuel nozzle attached thereto, the method comprising:
- providing a substantially homogenous mixture of fuel and air having an equivalence ratio of at least about 1.5 through the fuel nozzle to a combustion chamber defined at least in part by the dome and the liner;
- and
- providing the combustion chamber with a quench airflow through the plurality of quench air jets of the liner at a location downstream from the fuel nozzle,
- wherein the plurality of quench air jets comprise a plurality of primary stage air jets and a plurality of secondary stage air jets, the plurality of primary stage air jets are each spaced from the plurality of secondary stage air jets along the axial direction, at least one of the plurality of primary stage air jets defines an inlet having a generally elliptical shape, and at least one of the plurality of secondary stage air jets is an elongated slot.
Dependencies are inferred from the claim text.