Self-oscillating fuel injection jets
AssigneeGeneral Electric Company
InventorRonald Scott Bunker
Life of this patent
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Abstract
A combustor structure includes a combustor fuel-air mixing apparatus having a mainstream airflow region. One or more concavities are disposed within the mainstream airflow region of the fuel-air mixing apparatus. At least one fuel injection hole is disposed within an upstream base region of at least one concavity. Passing a stream of air through the main airflow region causes fuel injected into the upstream base region of at least one concavity to passively mix with a naturally oscillating vortex of air within the concavity.
Claims2
A fuel injector for use in a combustor section of a gas turbine engine, comprising:
- a body having a hub that extends circumferentially around a central axis;
- a plurality of angled vanes for pre-mixing the air and fuel, each vane extending from the hub to an outer annular shroud and are arranged in a circumferential direction on the hub around the central axis, each vane having a root portion located radially near the hub and a tip portion located radially near the outer annular shroud, each vane having a leading edge and a trailing edge extending between the root portion and the tip portion, each vane being angled relative to the central axis to impart a rotational component of motion to incoming air that enters the fuel injector;
- and
- at least one concavity disposed on at least one of the plurality of angled vanes, the at least one concavity having a substantially spherical cross-sectional shape and including a discrete fuel hole disposed in an upstream base region of the at least one concavity for injection of fuel into a mainstream of air flowing within the at least one concavity,
- wherein the at least one concavity provides enhanced fuel-air mixing.
A gas turbine system, comprising:
- a gas turbine engine including a compressor section and a combustor section having a plurality of combustor cans;
- a turbine section coupled to the compressor section;
- an exhaust section for channeling exhaust gases from the gas turbine engine;
- and
- a fuel injector for injecting a fuel-air mixture into the combustor section, said fuel injector comprising:
- a body having a hub that extends circumferentially around a central axis;
- a plurality of angled vanes for pre-mixing the air and fuel, each vane extending from the hub to an outer annular shroud and are arranged in a circumferential direction on the hub around the central axis, each vane having a root portion located radially near the hub and a tip portion located radially near the outer annular shroud, each vane having a leading edge and a trailing edge extending between the root portion and the tip portion, each vane being angled relative to the central axis to impart a rotational component of motion to incoming air that enters the fuel injector;
- and
- at least one concavity disposed on at least one of the plurality of angled vanes, the at least one concavity having a substantially spherical cross-sectional shape and including a discrete fuel hole disposed in an upstream base region of the at least one concavity for injection of fuel into a mainstream of air flowing within the at least one concavity,
- wherein the at least one concavity provides enhanced fuel-air mixing.
Dependencies are inferred from the claim text.