METHOD OF OPERATING A GAS TURBINE AND GAS TURBINE

• US 20130074511A1
• Filed: 09/06/2010
• Published: 03/28/2013
• Est. Priority Date: 09/07/2009
• Status: Abandoned Application

• Current Assignee: Shell Oil Company (Shell Plc)
• Original Assignee: Shell Oil Company (Shell Plc)
• Inventors: Tanaeva, Irina, Snoeks, Edwin
• Application Number:
  US13/394,188
• Publication Number:
  US 20130074511A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F01D 15/005 Adaptations for refrigeration plants
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F25J 1/0022 Hydrocarbons, e.g. natural gas
• CPC Class Codes: F25J 1/0052 by vaporising a liquid refrigerant stream
• CPC Class Codes: F25J 1/0055 originating from an incorporated cascade
• CPC Class Codes: F25J 1/0214 as a dual level refrigeration cascade with at least one MCR cycle
• CPC Class Codes: F25J 1/0216 using a C3 pre-cooling cycle
• CPC Class Codes: F25J 1/0236 providing refrigeration for different processes treating not the same feed stream
• CPC Class Codes: F25J 1/0283 Gas turbine as the prime mechanical driver
• CPC Class Codes: F25J 1/0292 Refrigerant compression by cold or cryogenic suction of the refrigerant gas

Abstract

A gas turbine system comprises a gas turbine having a low pressure compression stage and a high pressure compression stage, a combustion chamber, and an expansion stage connected to the combustion chamber. The low pressure compression stage and the high pressure compression stage are connected with each other via an intercooling stage, wherein the low pressure compressed air stream from the low pressure compression stage is chilled to an intercooling temperature that is lower than the ambient temperature of the air source from which the air stream was supplied to the low pressure compression stage of the gas turbine.

Claims

1. A method of operating a gas turbine, comprising at least the steps of:

providing a gas turbine having a low pressure compression stage, a high pressure compression stage, a combustion chamber, and an expansion stage;

taking in an air inlet stream with the gas turbine from an air source which is at an ambient temperature;

compressing the air inlet stream in the low pressure compression stage to provide a low pressure compressed air stream;

passing the low pressure compressed air stream to the high pressure compression stage via an intercooling stage;

cooling the low pressure compressed air stream against ambient in an intercooling ambient cooler in the intercooling stage thereby providing an ambient-cooled compressed air stream;

chilling the ambient-cooled compressed air stream in the intercooling stage to an intercooling temperature that is lower than the ambient temperature;

compressing the chilled low pressure compressed air stream coming from the intercooling stage in the high pressure compression stage to provide a high pressure air stream;

passing the high pressure air stream to the combustion chamber and producing a combusted stream by allowing the high pressure air stream to oxidize a fuel stream;

expanding the combusted stream in the expansion stage; and

driving the low pressure compression stage and the high pressure compression stage with mechanical power from the expansion stage.

2. The method according to claim 1, further comprising chilling the air inlet stream to an inlet temperature that is below the ambient temperature.

3. The method according to claim 1, wherein said chilling of the low pressure compressed air stream in the intercooling stage consumes cooling duty from a refrigerant being circulated in a refrigerant circuit.

4. The method according to claim 3, wherein said consuming of cooling duty from the refrigerant being circulated in the refrigerant circuit by the chilling of the low pressure compressed air stream comprises heat exchanging the refrigerant being circulated in the refrigerant circuit with a thermal transfer fluid stream to provide a chilled thermal transfer fluid stream, and heat exchanging the chilled thermal transfer fluid stream with the low pressure compressed air stream.

5. The method according to claim 4, wherein the thermal transfer fluid is circulated in a closed thermal transfer fluid circuit, and selected from the group consisting of:

water and a glycol.

6. The method according to claim 4, wherein the thermal transfer fluid is provided in the form of an ambient fluid stream.

7. The method according to claim 1, wherein the gas turbine drives a first compressor, which is an external compressor, and wherein the first compressor compresses a first suction stream to produce a first discharge stream.

8. The method according to claim 7, wherein the first suction stream is a refrigerant stream.

9. The method according to claim 1, wherein the gas turbine drives a first compressor, which is an external compressor, and wherein the first compressor compresses a first suction stream to produce a first discharge stream, wherein the first suction stream is comprises refrigerant from the refrigerant circuit.

10. A method of cooling a hydrocarbon feed stream to produce an at least partially liquefied hydrocarbon stream, comprising at least the steps of:

(a) circulating at least one refrigerant stream comprising a refrigerant in a refrigerant circuit, said circulating comprising compressing the refrigerant in at least a first compressor and expanding the refrigerant stream;

(b) driving the first compressor with a gas turbine;

(c) heat exchanging a hydrocarbon feed stream against at least a part of the refrigerant stream to provide an at least partially liquefied hydrocarbon stream; and

(d) operating the gas turbine with the method according to any one of the preceding claims.

11. The method according to claim 10, wherein said at least partially liquefied hydrocarbon stream is a fully liquefied hydrocarbon stream.

12. A gas turbine system comprising:

a as turbine comprising a low pressure compressor, a high pressure compressor, a combustion chamber, and an expansion stage using an expansion turbine;

a first air inlet into the gas turbine for taking in an air inlet stream from an air source at an ambient temperature;

a low pressure compressed air stream outlet from the gas turbine whereby the low pressure compression stage connects the first air inlet and the low pressure compressed air stream outlet;

an intercooling stage for producing an intercooled air stream from the low pressure compressed air stream, which intercooling stage is arranged to receive the low pressure compressed air stream passing through the low pressure compressed air stream outlet, the intercooling stage comprising an ambient cooler for cooling the low pressure compressed air stream against ambient thereby providing an ambient-cooled compressed air stream, followed by a heat exchanger arranged to chill the ambient-cooled compressed air stream to a temperature that is lower than the ambient temperature to produce the intercooled air stream;

a second air inlet into the gas turbine for taking in the intercooled air stream from the intercooling stage, whereby the combustion chamber is connected to the second air inlet via the high pressure compressor and to the expansion turbine;

a fuel stream inlet into the as turbine for allowing a fuel stream into the combustion chamber; and

first and second mechanical drive shafts connecting the expansion stage with the low pressure compressor and with the high pressure compressor.

13. The apparatus according to claim 12, wherein the first and second mechanical drive shafts connect the expansion turbine in the expansion stage with the low pressure compressor and with the high pressure compressor.