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US 10,330,320 B2Granted
Circumferentially and axially staged annular combustor for gas turbine engine
AssigneeUnited Technologies Corporation
InventorTimothy S. Snyder, III
Life of this patent
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Abstract
A combustor section for a gas turbine engine includes an outer wall assembly and an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween. A forward fuel injection system is in communication with the combustion chamber. A downstream fuel injection system is in communication with the combustion chamber through the outer wall assembly and a swirl mixer system in communication with the combustion chamber through the inner wall assembly.
Claims13
A combustor section for a gas turbine engine comprising:
- an outer wall assembly;
- an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween;
- a forward fuel injection system in communication with the annular combustion chamber, the forward fuel injection system including a plurality of forward fuel injectors;
- a downstream fuel injection system in communication with the annular combustion chamber through the outer wall assembly, the downstream fuel injection system including a plurality of downstream fuel injectors, wherein one of the plurality of downstream fuel injectors is circumferentially aligned with one of the plurality of forward fuel injectors relative to an axis of the gas turbine engine, and wherein another one of the plurality of downstream fuel injectors is circumferentially aligned between a circumferential adjacent pair of the plurality of forward fuel injectors relative to the axis;
- and
- a swirl mixer system in communication with the annular combustion chamber through the inner wall assembly.
3 more elements
A combustor section for a gas turbine engine comprising:
- an outer wall assembly;
- an inner wall assembly inboard of the outer wall assembly to define an annular combustion chamber therebetween;
- a forward fuel injection system in communication with the annular combustion chamber;
- a downstream fuel injection system in communication with the annular combustion chamber through the outer wall assembly;
- and
- a swirl mixer system in communication with the annular combustion chamber through the inner wall assembly;
- wherein the downstream fuel injection system includes a multiple of first downstream fuel nozzles that alternate with a multiple of second downstream fuel nozzles;
- wherein each of the multiple of first downstream fuel nozzles is operable to generate a first main zone within the annular combustion chamber, and each of the multiple of second downstream fuel nozzles is operable to generate a second main zone within the annular combustion chamber;
- and
- wherein the swirl mixer system includes a multiple of swirlers, and each of the swirlers is configured to generate a quench zone directed circumferentially between each first main zone and each associated second main zone.
7 more elements
Dependencies are inferred from the claim text.