Systems and methods for a gas turbine combustor having a bleed duct
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.
Claims16
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;
- at least one bleed duct having a first and a second inlet between the compressor and the outlet of the diffuser, the second inlet located upstream of the first inlet, and the at least one bleed duct operative to direct bleed air from downstream of the compressor directly to the fuel nozzle;
- a first vortex cavity at the first inlet of the bleed duct operative to draw compressed air from the at least one airstream in the diffuser;
- and
- a second vortex cavity at the second inlet, the first and second vortex cavities arranged such that bleed air from each of the first and second vortex cavities flows into the same bleed duct prior to flowing 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;
- directing the bleed air through a bleed duct directly to a fuel nozzle, the bleed duct comprising a first inlet and a second inlet located upstream of the first inlet;
- drawing, with a first vortex cavity located at the first inlet upstream from an outlet of the diffuser, bleed air from the airstream downstream from the compressor and upstream from the outlet of the diffuser;
- drawing, with a second vortex cavity located at the second inlet of the bleed duct, bleed air from the airstream downstream from the compressor;
- and
- combining the bleed air from the first vortex cavity with the bleed air from the second vortex cavity.
Dependencies are inferred from the claim text.