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US 2011/0030375 A1Published application
Aerodynamic pylon fuel injector system for combustors
AssigneeGeneral Electric Company
InventorRonald Scott Bunker
Life of this patent
Estimating the term…
Abstract
A combustor system includes a pylon fuel injection system coupled to a combustion chamber and configured to inject fuel to the combustion chamber. The pylon fuel injection system includes a plurality of radial elements, each radial element having a plurality of first Coanda type fuel injection slots. A plurality of transverse elements are provided to each radial element. Each transverse element includes a plurality of second Coanda type fuel injection slots.
Claims22
A combustor system comprising:
- a combustion chamber;
- a pylon fuel injection system coupled to the combustion chamber and configured to inject fuel to the combustion chamber, the pylon fuel injection system comprising:
- a plurality of radial elements, each radial element comprising a plurality of first Coanda type fuel injection slots;
- and
- a plurality of transverse elements provided to each radial element, wherein each transverse element comprises a plurality of second Coanda type fuel injection slots.
2 more elements
A gas turbine system comprising:
- at least one compressor configured to generate compressed air,
- a first combustor coupled to the at least one compressor and configured to receive the compressed air from the compressor and a fuel and combust a mixture of the air and the fuel to generate a first combustion gas;
- a first turbine coupled to the first combustor and configured to expand the first combustion gas;
- a second combustor coupled to the first turbine;
- a pylon fuel injection system comprising a plurality of radial elements and a plurality of transverse elements provided to each radial element, wherein the aerodynamic pylon injection system is configured to inject the fuel to the second combustor;
- wherein the second combustor is configured to combust a mixture of the fuel and the expanded first combustion gas to generate a second combustion gas;
- a second turbine coupled to the second combustor and configured to expand the second combustion gas.
4 more elements
Dependencies are inferred from the claim text.