Methods and apparatus for operating gas turbine engines
First Claim
1. A method for operating a gas turbine engine, including a compressor, a combustor and a turbine, coupled in serial flow arrangement, said method comprising:
- channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating therethrough to transfer heat energy to the working fluid;
channeling the working fluid from the heat exchanger to an inlet chiller;
extracting energy from the working fluid to power the inlet chiller; and
directing airflow entering the gas turbine engine through the inlet chiller such that a temperature of the airflow is reduced prior to the airflow entering the compressor.
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Accused Products
Abstract
A method for operating a gas turbine engine including a compressor, combustor, and turbine is provided that includes channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating within, channeling the working fluid from the heat exchanger to a chiller, extracting energy from the working fluid to power the chiller, and directing airflow entering the gas turbine engine through the inlet chiller such that the temperature of the airflow is reduced prior to the airflow entering the compressor.
17 Citations
18 Claims
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1. A method for operating a gas turbine engine, including a compressor, a combustor and a turbine, coupled in serial flow arrangement, said method comprising:
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channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating therethrough to transfer heat energy to the working fluid;
channeling the working fluid from the heat exchanger to an inlet chiller;
extracting energy from the working fluid to power the inlet chiller; and
directing airflow entering the gas turbine engine through the inlet chiller such that a temperature of the airflow is reduced prior to the airflow entering the compressor. - View Dependent Claims (2, 3, 4)
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5. A cooling system for a gas turbine engine, wherein the gas turbine engine includes at least a compressor and a turbine, said cooling system comprising:
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a heat exchanger coupled downstream from the compressor such that compressed discharge air from the compressor is routed therethrough, said heat exchanger having a working fluid circulating therethrough to transfer heat energy from the compressed discharge air to the working fluid; and
a chiller coupled in flow communication to said heat exchanger, said chiller extracting energy from the working fluid to facilitate reducing a temperature of inlet air channeled to the compressor. - View Dependent Claims (6, 7, 8, 9, 10)
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11. A gas turbine engine comprising:
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a compressor;
a combustor;
a turbine coupled in flow communication with said compressor;
a heat exchanger in flow communication downstream from said compressor to receive compressed discharge air therefrom, said heat exchanger having a working fluid flowing therethrough to extract energy from the discharged air; and
a chiller coupled in flow communication to said heat exchanger, said chiller configured to extract energy from the working fluid to facilitate reducing a temperature of air supplied to said compressor. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18)
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Specification