HEAT PIPE TEMPERATURE MANAGEMENT SYSTEM FOR A TURBOMACHINE

• US 20160290235A1
• Filed: 04/02/2015
• Published: 10/06/2016
• Est. Priority Date: 04/02/2015
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Ekanayake, Sanji, Mestroni, Julio Enrique, Rizzo, Joseph Paul, Scipio, Alston Ilford, Yang, Timothy Tahteh, Wickert, Thomas Edward
• Application Number:
  US14/676,950
• Publication Number:
  US 20160290235A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 25/125 of bearings
• CPC Class Codes: F01D 25/14 Casings modified therefor double casings F01D25/26
• 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: 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 7/143 before or between the compressor stages
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F05D 2260/208 using heat pipes

Abstract

A turbomachine includes a compressor, combustor and a turbine. An intercooler is operatively connected to the compressor. The intercooler includes a first plurality of heat pipes that extend into the inter-stage gap of the compressor, and the heat pipes are operatively connected to a first manifold. The heat pipes and the manifold are configured to transfer heat from the compressed airflow to one or more heat exchangers. A first cooling system is operatively connected to the turbine. The first cooling system includes a second plurality of heat pipes attached to or embedded within at least one of the plurality of wheels. The compressor bleed off air is configured to impinge onto at least one of the plurality of wheels or the second plurality of heat pipes. The second plurality of heat pipes and the compressor bleed off air are configured to cool at least one of the plurality of wheels.

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 wheels and a plurality of nozzles, a turbine casing forming an outer shell of the turbine, and the turbine receiving compressor bleed off air to cool at least one of the plurality of wheels;

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 first cooling system operatively connected to the turbine, the first cooling system including a second plurality of heat pipes attached to or embedded within at least one of the plurality of wheels, the compressor bleed off air is configured to impinge onto at least one of the plurality of wheels or the second plurality of heat pipes, and wherein the second plurality of heat pipes and the compressor bleed off air are configured to cool at least one of the plurality of wheels.

2. The turbomachine of claim 1, further comprising:

a second cooling system operatively connected to the turbine, the second cooling system including a third plurality of heat pipes located in at least a portion of the plurality of nozzles, 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 plurality of nozzles to the one or more heat exchangers.

3. The turbomachine of claim 2, further comprising:

a third cooling system operatively connected to the turbine casing, the third cooling system including a fourth plurality of heat pipes attached to and in thermal communication with the turbine casing, 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 turbine casing to the one or more heat exchangers.

4. The turbomachine of claim 3, further comprising:

an aftercooler operatively connected to the outlet portion of the compressor, the aftercooler including a fifth plurality of heat pipes that extend into the outlet portion, the fifth plurality of heat pipes operatively connected to a fifth manifold, the fifth plurality of heat pipes and the fifth manifold are configured to transfer heat from the compressed airflow in the outlet portion 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, further comprising:

the first plurality of heat pipes located in the inter-stage gap corresponding to an air bleed-off stage of the compressor;

the compressor bleed off air being withdrawn from at or between a first stage of the compressor and a third stage of the compressor; and

the second plurality of heat pipes located in or on a first stage turbine wheel, and the compressor bleed off air configured to impinge on an inner low pressure radius of the first stage turbine wheel.

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, a turbine casing forming an outer shell of the turbine, the turbine receiving compressor bleed off air to cool at least one of the plurality of wheels, 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 first cooling system operatively connected to the turbine, the first cooling system including a second plurality of heat pipes attached to or embedded within at least one of the plurality of wheels, the compressor bleed off air from the compressor is configured to impinge onto at least one of the plurality of wheels or the second plurality of heat pipes, and wherein the second plurality of heat pipes and the compressor bleed off air are configured to cool at least one of the plurality of wheels.

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

a second cooling system operatively connected to the turbine, the second cooling system including a third plurality of heat pipes located in at least a portion of the plurality of nozzles, 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 plurality of nozzles to the one or more heat exchangers.

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

a third cooling system operatively connected to the turbine casing, the third cooling system including a fourth plurality of heat pipes attached to and in thermal communication with the turbine casing, 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 turbine casing to the one or more heat exchangers.

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

an aftercooler operatively connected to the outlet portion of the compressor, the aftercooler including a fifth plurality of heat pipes that extend into the outlet portion, the fifth plurality of heat pipes operatively connected to a fifth manifold, the fifth plurality of heat pipes and the fifth manifold are configured to transfer heat from the compressed airflow in the outlet portion 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, further comprising:

the first plurality of heat pipes located in the inter-stage gap corresponding to an air bleed-off stage of the compressor;

the compressor bleed off air being withdrawn from at or between a first stage of the compressor and a third stage of the compressor; and

the second plurality of heat pipes located in or on a first stage turbine wheel, and the compressor bleed off air configured to impinge on an inner low pressure radius of the first stage turbine wheel.

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.