Systems and Methods for Gas Turbine Combustors
AssigneeGeneral Electric Company
InventorsJonathan Dwight Berry, Geoffrey David Myers
Life of this patent
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Abstract
A gas turbine system includes a compressor operative to output an airstream and a diffuser having an inlet to receive the airstream and an outlet to output the airstream. The outlet has an area larger than the inlet to diffuse the airstream. The gas turbine system also includes a fuel nozzle operative to receive fuel and emit the fuel in a combustor and at least one bleed duct having an inlet between the compressor and the outlet of the diffuser. The at least one bleed duct is operative to direct bleed air from downstream of the compressor to the fuel nozzle.
Claims19
A gas turbine system comprising:
- a compressor operative to output an airstream;
- a diffuser having an inlet to receive the airstream and an outlet to output the airstream, the outlet having an area larger than the inlet to diffuse the airstream;
- a fuel nozzle operative to receive fuel and emit the fuel in a combustor;
- and
- at least one bleed duct having an inlet between the compressor and the outlet of the diffuser, the at least one bleed duct operative to direct bleed air from downstream of the compressor to the fuel nozzle.
A method for routing bleed air comprising:
- outputting an airstream of compressed air from a compressor;
- diffusing the airstream in a diffuser;
- drawing bleed air from the airstream downstream from the compressor and upstream from an outlet of the diffuser;
- and
- directing the bleed air through a duct to a fuel nozzle.
Dependencies are inferred from the claim text.