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US 8,474,266 B2Granted
System and method for a gas turbine combustor having a bleed duct from a diffuser to a fuel nozzle
AssigneeGeneral Electric Company
InventorsJonathan Dwight Berry, Geoffrey David Myers
Life of this patent
Estimating the term…
Abstract
A gas turbine system comprising, a diffuser operative to diffuse an airstream output from a compressor, a fuel nozzle operative to receive fuel and emit the fuel in a combustor, and at least one bleed duct operative to direct bleed air from down stream of the combustor to the fuel nozzle.
Claims18
A gas turbine system comprising:
- a compressor operative to output an airstream;
- an outer casing defining a diffuser located downstream of the compressor;
- a fuel nozzle connected to a combustor operative to receive fuel and emit the fuel in the combustor;
- 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;
- and
- a bracket mounted to a mounting portion of the outer casing configured to support the combustor, the at least one bleed duct defined by a channel through the outer casing to the bracket and through the bracket to the fuel nozzle.
3 more elements
A method for routing bleed air in a gas turbine system, comprising:
- outputting an airstream of compressed air from a compressor;
- diffusing the airstream in a diffuser, the diffuser defined by an outer casing of the gas turbine system;
- 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 bleed duct to a fuel nozzle connected to a combustor, the bleed duct defined by a channel extending through the outer casing and a bracket mounted to a mounting portion of the outer casing and configured to support the combustor.
2 more elements
Dependencies are inferred from the claim text.