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US 6,935,117 B2Granted
Turbine engine fuel injector
AssigneeUnited Technologies Corporation
InventorCurtis C. Cowan
Life of this patent
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Abstract
A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.
Claims12
A fuel injector for a gas turbine engine comprising:
- a mounting flange;
- a stem extending from a proximal portion at the mounting flange to a distal portion;
- a nozzle proximate the stem distal portion;
- a first passageway along and through the stem and extending from a first inlet to a first outlet at the nozzle, the first outlet comprising a first plurality of apertures injecting gasified fuel;
- a second passageway along and through the stem and extending from a second inlet to a second outlet at the nozzle, the second outlet comprising a second plurality of apertures injecting liquid fuel, generally radially inboard of the first plurality of apertures;
- and
- a third passageway along and through the stem and extending from a third inlet to a third outlet at the nozzle, the third outlet comprising at least one third aperture injecting liquid fuel, generally radially inboard of the first plurality of apertures;
- said first, second, and third passageways in fluid communication with one or more liquid fuel tanks;
- said gas turbine engine being mounted on an aircraft to produce thrust.
6 more elements
Dependencies are inferred from the claim text.