TURBINE TO OPERATE AT PART-LOAD

• US 20130167551A1
• Filed: 01/04/2012
• Published: 07/04/2013
• Est. Priority Date: 01/04/2012
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Subramaniyan, Moorthi, Garg, Umesh, John, Joshy, Valliappan, Lakshmanan
• Granted Patent: US 9,169,782 B2
• Time in Patent Office: Days
• US Class Current: 60/795
• CPC Class Codes: F01D 25/08 Cooling of machines or engines in general F01P; Heating; Heat-insulation of blade-carrying members, of blades F01D5/00
• 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 5/187 Convection cooling
• CPC Class Codes: F01D 9/04 forming ring or sector
• 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 1/04 the working fluid being heated indirectly in a fluidised-bed combustor F02C3/205
• CPC Class Codes: F02C 7/14 of fluids in the plant , e.g. lubricant or fuel F02C7/185 takes precedence
• CPC Class Codes: F02C 9/18 by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence

Abstract

A turbine includes a compressor to intake a fluid and to compress the fluid, a combustion chamber to heat the fluid from the compressor, a turbine section to rotate a shaft with the heated fluid from the combustion chamber, and a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.

Claims

1. A turbine to operate at part-load, comprising:

a compressor to intake a fluid;

a combustion chamber to heat the fluid from the compressor;

a turbine section to rotate a shaft with the heated fluid from the combustion chamber;

a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor and transmitting the portion of the fluid to the turbine section; and

a controller to determine whether a part-load operation is selected, and to open the bypass circuit when the part-load operation is selected,

wherein when the controller determines that the part-load operation is selected, the controller determines a normal part-load fluid intake to the compressor, increases the part-load fluid intake to the compressor by a predetermined first percentage above the normal part-load fluid intake, and controls the bypass circuit to remove the portion of the fluid from the compressor such that a percentage of the portion of the fluid removed from the compressor relative to the increased part-load fluid intake is less than or equal to the predetermined first percentage.

2. The turbine of claim 1, wherein the compressor includes a fluid intake device, and the controller controls the fluid intake device to increase the part-load fluid intake.

3. The turbine of claim 1, wherein the controller increases the part-load fluid intake by 20% and controls the bypass circuit to remove 15% of the fluid from the compressor.

4. A turbine, comprising:

a compressor to intake a fluid and to compress the fluid;

a combustion chamber to heat the fluid from the compressor;

a turbine section to rotate a shaft with the heated fluid from the combustion chamber; and

a bypass circuit to generate a bypass flow by removing a portion of the fluid from the compressor, to heat the bypass flow, and to insert the bypass flow to the turbine section.

5. The turbine of claim 4, wherein the bypass circuit includes at least one of a steam generator and a firing unit to heat the bypass flow.

6. The turbine of claim 4, wherein the turbine further includes an exhaust section, and

the bypass circuit heats the bypass flow with a heated fluid from the exhaust section.

7. The turbine of claim 4, wherein the compressor includes at least eleven stages, and the bypass circuit removes the portion of the fluid from at least one of a third stage through an eleventh stage from among the at least eleven stages, where the at least eleven stages are numbered in order from an intake end of the compressor to a combustion chamber end of the compressor.

8. The turbine of claim 4, wherein the turbine section includes at least three stages numbered in ascending order from a combustion end of the turbine section to an output end of the turbine section, the at least three stages including a last stage adjacent to the output end of the turbine section, and

the bypass circuit inserts the bypass flow to the last stage of the turbine section.

9. The turbine of claim 8, wherein each stage of the turbine section includes a nozzle to direct the heated fluid to buckets, each nozzle comprising adjacent airfoils, an outer airfoil support, and an inner airfoil support, to together define a nozzle opening, and

the bypass circuit inserts the bypass flow through the outer airfoil support into the nozzle opening.

10. The turbine of claim 4, further comprising a cooling circuit to provide a purge flow to the turbine section,

wherein a casing of the turbine section includes a purge flow inlet to receive the purge flow and a separate bypass flow inlet to receive the bypass flow.

11. The turbine of claim 10, wherein the turbine section includes a plurality of nozzles, each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support, and an outer airfoil support,

the cooling circuit inputs the purge flow into at least one of the first and second airfoils of at least one of the plurality of nozzles, and

the bypass circuit inserts the bypass flow into the nozzle opening of the at least one of the plurality of nozzles.

12. The turbine of claim 11, wherein the at least one of the first and second airfoils includes a cavity extending between the outer airfoil support and the inner airfoil support, and the purge flow inlet is connected to the cavity, and

the outer airfoil support of the at least one of the plurality of nozzles includes an outlet to receive the bypass flow from the bypass flow inlet and to insert the bypass flow into the nozzle opening.

13. The turbine of claim 11, wherein the outer airfoil support includes a cavity having a divider to divide the cavity into two sections, and

the purge flow inlet opens into one of the two sections and the bypass flow inlet opens into the other of the two sections.

14. The turbine of claim 13, wherein the divider includes an opening connecting the two sections.

15. The turbine of claim 10, wherein the turbine section includes a plurality of nozzles, each nozzle having a nozzle opening defined by first and second airfoils, an inner airfoil support, and an outer airfoil support,

the cooling circuit inputs the purge flow into a purge flow cavity of the first airfoil, and

the bypass circuit inserts the bypass flow into a bypass flow cavity of the first airfoil.

16. The turbine of claim 15, wherein the first airfoil includes an opening to connect the bypass flow cavity to the nozzle opening.

17. A turbine section of a turbine, comprising:

a casing;

a rotor including a shaft and buckets extending radially from the shaft; and

nozzles comprising a plurality of airfoils positioned between an outer airfoil support connected to the casing and an inner airfoil support adjacent to the shaft of the rotor to define a nozzle opening,

wherein the casing includes a first inlet to receive a purge flow to cool at least the plurality of airfoils and a second inlet to receive a bypass flow to supply the bypass flow to the buckets of the rotor.

18. The turbine section of claim 17, wherein the turbine section includes a plurality of stages, each stage comprising an annular group of the nozzles and an adjacent annular group of the buckets, and

the second inlet is located at a last stage of the plurality of stages.

19. The turbine section of claim 17, wherein at least one of the plurality of airfoils includes a purge flow cavity and a bypass flow cavity, the purge flow cavity having an inlet at one end and an outlet at an opposing end, the bypass flow cavity having an inlet at the one end and an outlet along a side of the at least one of the plurality of airfoils to transmit the bypass flow to the nozzle opening, and

the first inlet of the casing is connected to the inlet of the purge flow cavity and the second inlet of the casing is connected to the inlet of the bypass flow cavity.

20. The turbine section of claim 19, wherein the at least one of the plurality of airfoils includes at least one opening between the purge flow cavity and the bypass flow cavity.