HEAT PIPE TEMPERATURE MANAGEMENT SYSTEM FOR A TURBOMACHINE

• US 20160290233A1
• Filed: 04/02/2015
• Published: 10/06/2016
• Est. Priority Date: 04/02/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Rizzo, Joseph Paul, Yang, Timothy Tahteh, Ekanayake, Sanji, Scipio, Alston Ilford, Wickert, Thomas Edward
• Granted Patent: US 9,797,310 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/125 of bearings
• CPC Class Codes: F01D 5/082 on the side of the rotor disc
• CPC Class Codes: F01D 5/088 in a closed cavity
• CPC Class Codes: F01D 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/181 Blades having a closed internal cavity containing a cooling medium, e.g. sodium
• CPC Class Codes: F01D 9/065 Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids see also F01D25/16, F01D25/24 and F01D25/26
• CPC Class Codes: F01K 23/02 the engine cycles being thermally coupled
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 6/18 using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants using waste heat as source of energy for refrigeration plants F25B27/02; using the waste heat of a gasturbine for steam generation or in a steam cycle see F01K23/10
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F02C 7/141 of working fluid
• CPC Class Codes: F02C 7/143 before or between the compressor stages
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F05D 2260/208 using heat pipes
• CPC Class Codes: Y02E 20/16 Combined cycle power plant [CCPP], or combined cycle gas turbine [CCGT]

Abstract

A turbomachine includes a compressor having an inter-stage gap between adjacent rows of rotor blades and stator vanes. A combustor is connected to the compressor, and a turbine is connected to the combustor. An intercooler is operatively connected to the compressor, and includes a first plurality of heat pipes that extend into the inter-stage gap. The first plurality of heat pipes are operatively connected to a first manifold, and the heat pipes and the first manifold are configured to transfer heat from the compressed airflow from the compressor to heat exchangers. A cooling system is operatively connected to the turbine, and includes a second plurality of heat pipes located in the turbine nozzles. The second plurality of heat pipes are operatively connected to a second manifold, and the heat pipes and the second manifold are configured to transfer heat from the turbine nozzles to the heat exchangers.

Claims

1. A turbomachine comprising:

a compressor including an intake portion and an outlet portion, the compressor having a plurality of rotor blades and a plurality of stator vanes, and an inter-stage gap exists between adjacent rows of rotor blades and stator vanes, the compressor compressing air received at the intake portion to form a compressed airflow that exits into the outlet portion;

a combustor operably connected with the compressor, the combustor receiving the compressed airflow;

a turbine operably connected with the combustor, the turbine receiving combustion gas flow from the combustor, the turbine having a plurality of turbine blades, a plurality of wheels and a plurality of nozzles, and a turbine casing forming an outer shell of the turbine;

an intercooler operatively connected to the compressor, the intercooler including a first plurality of heat pipes that extend into the inter-stage gap, the first plurality of heat pipes operatively connected to a first manifold, the first plurality of heat pipes and the first manifold are configured to transfer heat from the compressed airflow to one or more heat exchangers; and

a cooling system operatively connected to the turbine, the cooling system including a second plurality of heat pipes located in at least a portion of the plurality of nozzles, the second plurality of heat pipes operatively connected to a second manifold, the second plurality of heat pipes and the second manifold are configured to transfer heat from the plurality of nozzles to the one or more heat exchangers.

2. The turbomachine of claim 1, further comprising:

a second cooling system operatively connected to the turbine casing, the second cooling system including a third plurality of heat pipes attached to and in thermal communication with the turbine casing, the third plurality of heat pipes operatively connected to a third manifold, the third plurality of heat pipes and the third manifold are configured to transfer heat from the turbine casing to the one or more heat exchangers.

3. The turbomachine of claim 2, further comprising:

an aftercooler operatively connected to the outlet portion of the compressor, the aftercooler including a fourth plurality of heat pipes that extend into the outlet portion, the fourth plurality of heat pipes operatively connected to a fourth manifold, the fourth plurality of heat pipes and the fourth manifold are configured to transfer heat from the compressed airflow in the outlet portion to the one or more heat exchangers.

4. The turbomachine of claim 3, further comprising:

a third cooling system operatively connected to the turbine, the third cooling system including a fifth plurality of heat pipes located axially upstream of at least one of the plurality of wheels, the fifth plurality of heat pipes operatively connected to a bearing cooler system, the fifth plurality of heat pipes and the bearing cooler system are configured to transfer heat from the compressor bleed off air to the one or more heat exchangers.

5. The turbomachine of claim 1, the first plurality of heat pipes and the second plurality of heat pipes further comprising a heat transfer medium including one or combinations of:

aluminum, beryllium, beryllium-fluorine alloy, boron, calcium, cesium, cobalt, lead-bismuth alloy, liquid metal, lithium-chlorine alloy, lithium-fluorine alloy, manganese, manganese-chlorine alloy, mercury, molten salt, potassium, potassium-chlorine alloy, potassium-fluorine alloy, potassium-nitrogen-oxygen alloy, rhodium, rubidium-chlorine alloy, rubidium-fluorine alloy, sodium, sodium-chlorine alloy, sodium-fluorine alloy, sodium-boron-fluorine alloy, sodium nitrogen-oxygen alloy, strontium, tin, zirconium-fluorine alloy.

6. The turbomachine of claim 1, the first plurality of heat pipes and the second plurality of heat pipes further comprising a molten salt heat transfer medium including one or combinations of, potassium, sodium or cesium.

7. The turbomachine of claim 1, the first plurality of heat pipes located in the inter-stage gap corresponding to an air bleed-off stage of the compressor.

8. The turbomachine of claim 1, wherein the first plurality of heat pipes and the second plurality of heat pipes have a cross-sectional shape, the cross sectional shape generally comprising at least one of:

circular, oval, rectangular with rounded corners or polygonal.

9. The turbomachine of claim 8, at least one of the first plurality of heat pipes or the second plurality of heat pipes further comprising a plurality of fins, the plurality of fins configured to increase the heat transfer capability of the plurality of heat pipes.

10. The turbomachine of claim 1, the one or more heat exchangers including a heat pipe heat exchanger operably connected to at least one of:

a fuel heating heat exchanger;

or

a heat recovery steam generator heat exchanger;

or

a fuel heating heat exchanger and a heat recovery steam generator heat exchanger.

11. A temperature management system for a turbomachine, the turbomachine having a compressor including an intake portion and an outlet portion, the compressor having a plurality of rotor blades and a plurality of stator vanes, and an inter-stage gap that exists between adjacent rows of rotor blades and stator vanes, the compressor compressing air received at the intake portion to form a compressed airflow that exits into the outlet portion, a combustor operably connected with the compressor, the combustor receiving the compressed airflow, and a turbine operably connected with the combustor, the turbine receiving combustion gas flow from the combustor, the turbine having a plurality of turbine blades, a plurality of wheels and a plurality of nozzles, and a turbine casing forming an outer shell of the turbine, the temperature management system comprising:

an intercooler operatively connected to the compressor, the intercooler including a first plurality of heat pipes that extend into the inter-stage gap, the first plurality of heat pipes operatively connected to a first manifold, the first plurality of heat pipes and the first manifold are configured to transfer heat from the compressed airflow to one or more heat exchangers; and

a cooling system operatively connected to the turbine, the cooling system including a second plurality of heat pipes located in at least a portion of the plurality of nozzles, the second plurality of heat pipes operatively connected to a second manifold, the second plurality of heat pipes and the second manifold are configured to transfer heat from the plurality of nozzles to the one or more heat exchangers.

12. The temperature management system of claim 11, further comprising:

a second cooling system operatively connected to the turbine casing, the second cooling system including a third plurality of heat pipes attached to and in thermal communication with the turbine casing, the third plurality of heat pipes operatively connected to a third manifold, the third plurality of heat pipes and the third manifold are configured to transfer heat from the turbine casing to the one or more heat exchangers.

13. The temperature management system of claim 11, further comprising:

an aftercooler operatively connected to the outlet portion of the compressor, the aftercooler including a fourth plurality of heat pipes that extend into the outlet portion, the fourth plurality of heat pipes operatively connected to a fourth manifold, the fourth plurality of heat pipes and the fourth manifold are configured to transfer heat from the compressed airflow in the outlet portion to the one or more heat exchangers.

14. The temperature management system of claim 11, further comprising:

a third cooling system operatively connected to the turbine, the third cooling system including a fifth plurality of heat pipes located axially upstream of at least one of the plurality of wheels, the fifth plurality of heat pipes operatively connected to a bearing cooler system, the fifth plurality of heat pipes and the bearing cooler system are configured to transfer heat from the compressor bleed off air to the one or more heat exchangers.

15. The temperature management system of claim 11, the first plurality of heat pipes and the second plurality of heat pipes further comprising a heat transfer medium including one or combinations of:

aluminum, beryllium, beryllium-fluorine alloy, boron, calcium, cesium, cobalt, lead-bismuth alloy, liquid metal, lithium-chlorine alloy, lithium-fluorine alloy, manganese, manganese-chlorine alloy, mercury, molten salt, potassium, potassium-chlorine alloy, potassium-fluorine alloy, potassium-nitrogen-oxygen alloy, rhodium, rubidium-chlorine alloy, rubidium-fluorine alloy, sodium, sodium-chlorine alloy, sodium-fluorine alloy, sodium-boron-fluorine alloy, sodium nitrogen-oxygen alloy, strontium, tin, zirconium-fluorine alloy.

16. The temperature management system of claim 11, the first plurality of heat pipes and the second plurality of heat pipes further comprising a molten salt heat transfer medium including one or combinations of, potassium, sodium or cesium.

17. The temperature management system of claim 11, the first plurality of heat pipes located in the inter-stage gap corresponding to an air bleed-off stage of the compressor.

18. The temperature management system of claim 11, wherein the first plurality of heat pipes and the second plurality of heat pipes have a cross-sectional shape, the cross sectional shape generally comprising at least one of:

circular, oval, rectangular with rounded corners or polygonal.

19. The temperature management system of claim 18, at least one of the first plurality of heat pipes or the second plurality of heat pipes further comprising a plurality of fins, the plurality of fins configured to increase the heat transfer capability of the plurality of heat pipes.

20. The temperature management system of claim 11, the one or more heat exchangers including a heat pipe heat exchanger operably connected to at least one of:

a fuel heating heat exchanger;

or

a heat recovery steam generator heat exchanger;

or

a fuel heating heat exchanger and a heat recovery steam generator heat exchanger.