Rotor Shaft Cooling

• US 20180202360A1
• Filed: 01/18/2017
• Published: 07/19/2018
• Est. Priority Date: 01/18/2017
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Mukhopadhyay, Debabrata, Jain, Sanjeev Kumar, Soundiramourty, Sendilkumaran, Mavuri, Rajesh, Tyagi, Jagdish Prasad
• Granted Patent: US 10,641,174 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/24 Casings modified for heating or cooling F01D25/14; Casing parts, e.g. diaphragms, casing fastenings casings for rotary machines or engines in general F16M ; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045
• CPC Class Codes: F01D 5/085 cooling fluid circulating inside the rotor
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 7/28 Arrangement of seals
• CPC Class Codes: F05D 2240/60 Shafts
• CPC Class Codes: F05D 2260/213 by the provision of a heat exchanger within the cooling circuit
• CPC Class Codes: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Abstract

A gas turbine casing with an internal heat exchange system. The gas turbine extends between an inlet section and an exhaust section and defines a downstream direction from the inlet section to the exhaust section. The casing includes a forward end, an aft end downstream of the forward end, a first exterior surface facing radially outward, a second exterior surface facing radially inward, and an internal body at least partially defined between the first exterior surface and the second exterior surface. The heat exchange system includes an inlet and an outlet formed in an exterior surface of the casing proximate the aft end, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

Claims

1. A casing for a gas turbine, the gas turbine extending between an inlet section and an exhaust section and defining a downstream direction from the inlet section to the exhaust section, the casing comprising:

a forward end;

an aft end downstream of the forward end;

a first exterior surface facing radially outward;

a second exterior surface opposing the first exterior surface, the second exterior surface facing radially inward;

an internal body at least partially defined between the first exterior surface and the second exterior surface; and

a heat exchange system comprising an inlet formed in one of the first exterior surface and the second exterior surface proximate the aft end of the casing, an outlet formed in one of the first exterior surface and the second exterior surface proximate the aft end of the inner casing, a supply bore extending upstream from the inlet through the interior body of the casing, and a return bore extending downstream to the outlet through the interior body of the casing.

2. The casing of claim 1, wherein the heat exchange system further comprises a plenum defined within the body of the casing proximate to the forward end of the casing.

3. The casing of claim 2, wherein the supply bore extends from the inlet to the plenum.

4. The casing of claim 2, wherein the return bore extends from the plenum to the outlet.

5. A gas turbine extending between an inlet section and an exhaust section and defining a downstream direction from the inlet section to the exhaust section, the gas turbine further comprising:

a compressor;

a turbine section, the exhaust section downstream of the turbine section;

a plurality of combustors disposed downstream from the compressor and upstream from the turbine;

a rotor shaft extending between the turbine section and the compressor;

a casing between the rotor shaft and the plurality of combustors;

a high pressure packing seal between the rotor shaft and the inner casing;

a heat exchange system defined in the casing, the heat exchange system comprising an inlet formed in the casing proximate an aft end of the casing, an outlet formed in the casing proximate the aft end of the casing, a supply conduit extending through the casing upstream from the inlet, and a return conduit extending through the casing downstream to the outlet; and

a cooling fluid source in fluid communication with at least one of the inlet and the outlet;

wherein the rotor shaft is in thermal communication with the heat exchange system of the casing.

6. The gas turbine of claim 5, wherein the heat exchange system further comprises a plenum defined within the casing proximate to a forward end of the inner casing.

7. The gas turbine of claim 6, wherein the supply conduit extends from the inlet to the plenum.

8. The gas turbine of claim 6, wherein the return conduit extends from the plenum to the outlet.

9. The gas turbine of claim 5, wherein the cooling fluid source is a cooling air system configured to provide cooling air from an intermediate stage of the compressor to the turbine section, the cooling air system in fluid communication with the inlet of the heat exchange system and in fluid communication with the outlet of the heat exchange system.

10. The gas turbine of claim 9, wherein the cooling air system comprises a first conduit extending between the intermediate stage of the compressor and the turbine section, a second conduit extending between the first conduit and the inlet of the heat exchange system and a third conduit extending between the outlet of the heat exchange system and the first conduit.

11. The gas turbine of claim 5, wherein the cooling fluid source is a heat recovery steam generator for recovering heat from the exhaust section and the cooling fluid is steam, the heat recovery steam generator in fluid communication with the inlet of the heat exchange system and in fluid communication with the outlet of the heat exchange system.

12. The gas turbine of claim 5, wherein the cooling fluid source is an external blower.

13. A method of cooling a rotor shaft of a gas turbine, the gas turbine further comprising a compressor, a turbine section, a plurality of combustors disposed downstream from the compressor and upstream from the turbine, the rotor shaft extending between the turbine and the compressor, a casing between the rotor shaft and the plurality of combustors and a high pressure packing seal disposed in a high pressure packing seal cavity between the rotor shaft and the casing, the method comprising:

directing a supply stream of a cooling fluid within the casing in an upstream direction from an inlet proximate to an aft end of the casing; and

directing a return stream of the cooling fluid within the casing in a downstream direction to an outlet proximate the aft end of the casing;

whereby heat is transferred from the rotor shaft to the cooling fluid.

14. The method of claim 13, wherein the cooling fluid is a first cooling fluid, the method further comprising a step of injecting a stream of a second cooling fluid into the high pressure packing seal cavity.

15. The method of claim 14, wherein the second cooling fluid is steam.

16. The method of claim 13, wherein the step of directing a supply stream further comprises directing the cooling fluid to an internal plenum defined within the casing proximate a forward end of the casing.

17. The method of claim 13, wherein the step of directing a return stream further comprises directing the cooling fluid from an internal plenum defined within the casing proximate a forward end of the casing.

18. The method of claim 13, further comprising directing a stream of cooling fluid from an intermediate stage of the compressor to the inlet so as to form the supply stream of cooling fluid.

19. The method of claim 13, further comprising directing a stream of cooling fluid from the outlet to the turbine section.

20. The method of claim 13, wherein the cooling fluid is liquid water.