초록 ▼

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, ext

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.

대표청구항 ▼

What is claimed is: 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

What is claimed is: 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. 2. A method in accordance with claim 1 further comprising: channeling airflow from the heat exchanger to an intercooler downstream from the heat exchanger, such that a temperature of the airflow is reduced prior to being directed back toward the turbine. 3. A method in accordance with claim 1 wherein the gas turbine engine includes a high-pressure and a low-pressure compressor, said channeling compressed airflow from the compressor comprises channeling compressed airflow from the low-pressure compressor. 4. A method in accordance with claim 1 wherein said channeling compressed airflow from the compressor to a heat exchanger further comprises channeling airflow to a heat exchanger including at least one of water, steam, and a mixture of water and ammonia circulating therethrough. 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: 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. 6. A cooling system in accordance with claim 5 wherein the gas turbine engine includes a low-pressure compressor and a high-pressure compressor downstream of the low-pressure compressor, said heat exchanger is positioned between the low-pressure compressor and the high-pressure compressor. 7. A cooling system in accordance with claim 5 further comprising an intercooler coupled downstream from said heat exchanger, said intercooler configured to receive airflow from said heat exchanger at a first temperature, and channel the airflow to the compressor at a second temperature that is lower than the first temperature. 8. A cooling system in accordance with claim 7 wherein the gas turbine engine includes a low-pressure compressor and a high-pressure compressor downstream of the low-pressure compressor, said heat exchanger and said intercooler are positioned between the low-pressure compressor and the high-pressure compressor. 9. A cooling system in accordance with claim 5 wherein the heat exchanger working fluid is at least one of water, steam, and a mixture of ammonia and water. 10. A cooling system in accordance with claim 5 wherein said heat exchanger is a heat recovery steam generator. 11. A gas turbine engine comprising: 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. 12. A gas turbine engine in accordance with claim 11 wherein said heat exchanger is a heat recovery steam generator. 13. A gas turbine engine in accordance with claim 11 wherein said chiller is an absorption chiller. 14. A gas turbine engine in accordance with claim 11 wherein said compressor comprises a low-pressure compressor and a high-pressure compressor coupled downstream from said low-pressure compressor, said heat exchanger is coupled in flow communication between said low-pressure compressor and said high-pressure compressor. 15. A cooling system in accordance with claim 11 further comprising an intercooler coupled downstream from said heat exchanger, said intercooler configured to receive airflow from said heat exchanger at a first temperature, and channel the airflow to the compressor at a second temperature that is lower than the first temperature. 16. A gas turbine engine in accordance with claim 15 further comprising an intercooler coupled downstream from said heat exchanger, such that said intercooler receives airflow from said heat exchanger at a first temperature, said intercooler configured to discharge the airflow to said compressor at a second temperature that is lower than the first temperature. 17. A gas turbine engine in accordance with claim 16 wherein said compressor comprises a low-pressure compressor and a high-pressure compressor coupled downstream from said low-pressure compressor, said heat exchanger and said intercooler coupled in flow communication between said low-pressure compressor and said high-pressure compressor. 18. A gas turbine engine in accordance with claim 11 wherein said working fluid is at least one of water, steam, and a mixture of ammonia and water.