Symmetric fuel injection for turbine combustor
AssigneeHamilton Sundstrand Corporation
InventorsCarsten Ralf Mehring, James Peffley
Life of this patent
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Abstract
A fuel injection system comprises a combustor liner, an air tube, a fuel manifold and a fuel injector. The combustor liner defines primary and secondary combustion zones. The air tube extends through the combustor liner along an axis to an exit aperture inside the combustor. The fuel manifold is positioned proximate the combustor line to deliver fuel through the air tube to the primary and secondary combustion zones. The fuel injector is coupled to the fuel manifold and positioned to inject the fuel along an axis of the air tube, such that the fuel has a substantially symmetric distribution at the exit aperture.
Claims17
A fuel injection system comprising:
- a combustor liner defining primary and secondary combustion zones;
- an air tube extending through the combustor liner along an axis to an exit aperture inside the combustor, and comprising a fuel tube formed along an inner axial surface of the air tube which forms a boundary for air flow, the fuel tube offset from the axis of the air tube;
- a fuel manifold positioned proximate the combustor liner to deliver fuel through the air tube to the primary and secondary combustion zones;
- and
- a fuel injector coupled to the fuel manifold and positioned to inject the fuel from the fuel tube substantially in a direction parallel to the axis of the air tube, such that the fuel has a substantially symmetric distribution about the axis of the air tube, at the exit aperture.
A combustor for a gas turbine engine, the combustor comprising:
- a combustor liner defining primary and secondary combustion zones;
- an air tube extending through the combustor liner to an exit aperture, the air tube defining an air tube axis for delivery of fuel and air to the primary and secondary combustion zones, and comprising a fuel tube formed along an inner axial surface of the air tube which forms a boundary for air flow, the fuel tube offset from the axis of the air tube;
- a fuel manifold positioned proximate the combustor liner to deliver fuel through the air tube into the primary and secondary combustion zones;
- and
- a fuel injector coupled to the fuel manifold and receiving fuel from the fuel tube and positioned within the air tube to generate a substantially symmetric fuel distribution with respect to the air tube axis at the exit aperture.
A turbojet engine comprising:
- a compressor and a turbine in flow series;
- and
- a combustor positioned between the compressor and the turbine in the flow series, the combustor comprising:
- a liner defining primary and secondary combustion zones;
- an air tube extending radially through the combustor liner to an exit aperture;
- a fuel manifold for delivering fuel to the primary and secondary combustion zones along an axis of the air tube;
- and
- a fuel injector positioned to inject the fuel substantially in a direction parallel to the axis of the air tube and comprising a fuel tube formed along an inner axial surface of the air tube which forms a boundary for air flow, the fuel tube offset from the axis of the air tube, such that the fuel injector generates a substantially symmetric fuel distribution at the exit aperture of the air tube.
Dependencies are inferred from the claim text.