METHODS AND APPARATUS FOR OPERATING GAS TURBINE ENGINES

• US 20070144176A1
• Filed: 02/11/2005
• Published: 06/28/2007
• Est. Priority Date: 02/11/2005
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Peters, Joseph, Prochaska, James, Joshi, Narendra, Reale, Michael
• Granted Patent: US 7,254,950 B2
• Time in Patent Office: Days
• US Class Current: 60/728
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F05D 2220/60 making use of surplus or waste energy
• CPC Class Codes: Y02E 20/14 Combined heat and power generation [CHP]
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A method for operating a gas turbine engine, including a first compressor, a second compressor, a combustor and a turbine, coupled together in serial flow arrangement, and an intercooler coupled between the first compressor and the second compressor, the intercooler including a first heat exchanger and a second heat exchanger. The method includes channeling compressed airflow from the first compressor to the first heat exchanger, extracting energy from the compressed airflow using a first working fluid flowing through the first heat exchanger to facilitate reducing an operating temperature of the compressed airflow and to facilitate increasing an operating temperature of the first working fluid, and channeling the first working fluid to a process heat exchanger, and channel the compressed airflow form the first heat exchanger to the second compressor.

Claims

1. A method for operating a gas turbine engine, including a first compressor, a second compressor, a combustor and a turbine, coupled together in serial flow arrangement, and an intercooler coupled between the first compressor and the second compressor, the intercooler including a first heat exchanger and a second heat exchanger said method comprising:

channeling compressed airflow from the first compressor to the first heat exchanger;

extracting energy from the compressed airflow using a first working fluid flowing through the first heat exchanger to facilitate reducing an operating temperature of the compressed airflow and to facilitate increasing an operating temperature of the first working fluid;

channeling the first working fluid to a process heat exchanger; and

channeling the compressed airflow from the first heat exchanger to the second compressor.

2. A method in accordance with claim 1 further comprising channeling the first working fluid to the process heat exchanger to facilitate increasing an operating temperature of a process.

3. A method in accordance with claim 1 further comprising:

channeling the compressed airflow discharged from the first heat exchanger to the second heat exchanger;

extracting energy from the compressed airflow discharged from the second heat exchanger using the second working fluid flowing therethrough to facilitate reducing an operating temperature of the airflow discharged from the second heat exchanger; and

channeling the compressed airflow from the second heat exchanger to the second compressor.

4. A method in accordance with claim 1 further comprising regulating the flow of second working fluid through the second heat exchanger to facilitate regulating an operating temperature of the airflow channeled to the second compressor.

5. A method in accordance with claim 4 wherein regulating the flow of second working fluid flowing through the second heat exchanger comprises operating at least one of a bypass valve and a variable speed pump to facilitate regulating the flow of second working fluid through the second heat exchanger.

6. A method in accordance with claim 3 further comprising:

determining a temperature and mass flow rate of the second working fluid; and

utilizing the determined temperature and mass flow rate values to facilitate regulating an operating temperature of the airflow channeled to the second compressor.

7. A method in accordance with claim 3 further comprising regulating an operating temperature of airflow channeled to the second compressor based on a predetermined temperature.

8. An intercooler system for a gas turbine engine that includes at least a first compressor, a second compressor, a combustor, and a turbine, said intercooler system comprising:

an intercooler comprising a first cooling system having a first working fluid flowing therethrough and configured to extract energy from the compressed airflow flowing from the first compressor to facilitate reducing an operating temperature of the compressed airflow and to facilitate increasing an operating temperature of said first working fluid, and to channel the compressed air to the second compressor;

a process heat exchanger configured to receive said first working fluid; and

a control system configured to;

receive an input from at least one of said intercooler system and an operator; and

activate at least one of a valve and a pump based said input.

9. An intercooler system in accordance with claim 8 wherein said process heat exchanger is configured to increase a temperature of a process.

10. An intercooler system in accordance with claim 8 wherein said intercooler further comprises a second cooling system that is different than said first cooling system, said second cooling system is configured to receive the compressed airflow discharged from said first cooling system and extract energy from the compressed airflow using a second working fluid flowing therethrough to facilitate reducing an operating temperature of the airflow discharged from said second cooling system to the second compressor.

11. An intercooler system in accordance with claim 8 wherein said control system is further configured to regulate the flow of said second working fluid through said second cooling system to facilitate regulating an operating temperature of the airflow channeled to the second compressor.

12. An intercooler system in accordance with claim 11 further comprising:

a temperature sensor coupled to said control system and configured to determine an operating temperature of said second working fluid; and

a mass flow sensor coupled to said control system and configured to determine a mass flow rate of said second working fluid.

13. An intercooler system in accordance with claim 12 wherein said control system is configured to utilize the determined second working fluid temperature and mass flow rate to operate at least one of a bypass valve and a variable speed pump to facilitate regulating the flow of said second working fluid through said second heat exchanger.

14. An intercooler system in accordance with claim 10 wherein said first cooling system comprises a first pump coupled in flow communication with a first heat exchanger and said second cooling system comprises a second pump coupled in flow communication with a second heat exchanger.

15. A gas turbine engine assembly comprising:

a first compressor;

a second compressor downstream from said first compressor;

a turbine coupled in flow communication with said second compressor; and

an intercooler system comprising;

an intercooler coupled downstream from said first compressor such that compressed air discharged from said first compressor is routed therethrough, said intercooler comprising a first heat exchanger having a first working fluid flowing therethrough and a second heat exchanger having a second working fluid flowing therethrough, said second heat exchanger is configured to receive the compressed airflow discharged from said first heat exchanger and extract energy from the compressed airflow to facilitate reducing an operating temperature of the airflow discharged from said second heat exchanger to said second compressor.

16. A gas turbine engine assembly in accordance with claim 15 further comprising a process heat exchanger, said first heat exchanger is configured to extract energy from the compressed airflow flowing therethrough to facilitate reducing an operating temperature of the compressed airflow and to facilitate increasing an operating temperature of said first working fluid, said process heat exchanger configured to receive said first working fluid.

17. A gas turbine engine assembly in accordance with claim 16 wherein said process heat exchanger is configured to increase a temperature of a process.

18. A gas turbine engine assembly in accordance with claim 15 further comprising a control system configured to regulate the flow of said second working fluid flowing through said second cooling system to facilitate regulating an operating temperature of the airflow channeled to said second compressor.

19. A gas turbine engine assembly in accordance with claim 18 further comprising:

a temperature sensor coupled to said control system and configured to determine an operating temperature of said second working fluid; and

a mass flow sensor coupled to said control system and configured to determine a mass flow rate of said second working fluid, said control system is configured to utilize the determined second working fluid temperature and mass flow rate to facilitate regulating an operating temperature of the airflow channeled to said second compressor.

20. A gas turbine engine assembly in accordance with claim 15 further comprising:

a first pump coupled in flow communication with said first heat exchanger; and

a second pump coupled in flow communication with said second heat exchanger.