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US 2014/0338357 A1Published application
Cavity swirl fuel injector for an augmentor section of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsJeffery A. Lovett, Benjamin D. Bellows
Life of this patent
Estimating the term…
Abstract
A fuel injection system for a gas turbine engine includes a fuel nozzle with a fuel injection aperture to inject a fuel jet and a multiple of airflow passages in the fuel nozzle to communicate a multiple of air streams to interact with the fuel jet.
Claims20
A fuel injection system for a gas turbine engine comprising:
- a fuel nozzle with a fuel injection aperture to inject a fuel jet;
- and
- a multiple of airflow passages in said fuel nozzle to communicate a multiple of air streams to interact with said fuel jet.
An augmentor section for a gas turbine engine comprising:
- an augmentor vane within an exhaust gas path of the gas turbine engine;
- a spraybar mounted within said augmentor vane;
- and
- a fuel injector mounted to said spraybar to communicate through said augmentor vane, said fuel injector generates counter-rotating vortices.
1 more element
A method of injecting fuel, comprising:
- directing a fuel jet along an axis;
- directing a first airflow vortices that impinges an edge of the fuel jet and rotates counterclockwise;
- and
- directing a second airflow vortices that impinges an edge of the fuel jet and rotates clockwise.
1 more element
Dependencies are inferred from the claim text.