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US 2025/0027649 A1Published application
Staged blade injector
AssigneeRtx Corporation
InventorGregory Boardman
Life of this patent
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Abstract
A blade fuel injector for a gas turbine engine, including: a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings; and a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.
Claims20
A blade fuel injector for a gas turbine engine, comprising:
- a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings;
- and
- a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.
A combustor for a gas turbine engine, comprising:
- a plurality of pilot fuel injectors;
- a plurality of blade fuel injectors, each blade fuel injector comprising:
- a mixer, the mixer having a first set of openings located on opposite sides of the mixer and a second set of openings located below the first set of openings;
- and
- a blade injector, the blade injector having a plurality of atomizers, wherein some of the first set of openings align with the plurality of atomizers.
2 more elements
Dependencies are inferred from the claim text.