System and method for gas turbine inlet air heating
AssigneeGeneral Electric Company
InventorsJianmin Zhang, James Patrick Tomey
Life of this patent
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Abstract
In one embodiment of the present disclosure, a gas turbine system for part load efficiency improvement and anti-icing within the inlet and at the compressor inlet is described. The system includes a gas turbine having a compressor which receives inlet-air. A direct-contact heat exchanger heats the inlet-air before the inlet-air flows through the inlet and to the compressor. Heating the inlet-air reduces an output of the gas turbine and extends the turndown range, and avoids ice-forming conditions within the inlet and at the compressor inlet bellmouth. The direct-contact heat exchanger may also be configured to act as an evaporative cooler, air chiller, or use liquid dessicant.
Claims20
A gas turbine system for part load efficiency improvement and anti-icing within the inlet and at the compressor inlet comprising:
- a gas turbine comprising a compressor, which receives inlet-air;
- and
- a direct-contact heat exchanger, the direct-contact heat exchanger being configured to heat the inlet-air before the inlet-air flows to the compressor, wherein heating the inlet-air can prevent ice formation within the inlet system, reduces an output of the gas turbine, and extends the turndown range.
A method of controlling a gas turbine system operation for part load efficiency improvement and anti-icing within the inlet and at the compressor inlet, the method comprising:
- utilizing a direct-contact heat exchanger to heat inlet-air before the inlet-air flows to a gas turbine inlet or to a gas turbine compressor;
- feeding the gas turbine compressor the heated inlet-air;
- and
- wherein the heated inlet-air reduces an output of the gas turbine and extends the turndown range.
Dependencies are inferred from the claim text.