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US 8,475,117 B2Granted
Gas turbine compressor and method of operation
AssigneeGeneral Electric Company
InventorPhilip L. Andrew
Life of this patent
Estimating the term…
Abstract
The present application provides a compressor for a gas turbine. The compressor may include a number of rotor wheels positioned about a compressor aft section having a low alloy material, a number of inlet guide vanes positioned about a compressor inlet section, and a wet compression system positioned about the compressor inlet section.
Claims19
A compressor for a gas turbine, comprising:
- a plurality of rotor wheels positioned about a compressor aft section;
- the plurality of rotor wheels comprising a low alloy material;
- a plurality of inlet guide vanes positioned upstream of a compressor inlet section;
- a wet compression system positioned about the compressor inlet section;
- and
- a plurality of stator blades downstream of the plurality of inlet guide vanes.
3 more elements
A method of operating a compressor in varying ambient temperatures so as to maintain a level power output, comprising:
- positioning a plurality of inlet guide vanes in an extended position until a predetermined ambient design condition temperature is reached;
- modulating the plurality of inlet guide vanes to an open position when the ambient temperature exceeds the predetermined ambient design condition temperature;
- and
- operating a wet compression system when the ambient temperature exceeds the predetermined ambient design condition temperature.
1 more element
A compressor for a gas turbine, comprising:
- a plurality of rotor wheels positioned about a compressor aft section;
- the plurality of rotor wheels comprising a plurality of rotor blades;
- a plurality of inlet guide vanes positioned upstream of a compressor inlet section;
- a wet compression system positioned about the compressor inlet section;
- and
- a plurality of stator blades downstream of the plurality of inlet guide vanes.
3 more elements
Dependencies are inferred from the claim text.