IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0700005
(2010-02-04)
|
등록번호 |
US-8495883
(2013-07-30)
|
발명자
/ 주소 |
- Foust, Adam M.
- Nordlund, Raymond S.
- Chhabra, Nitin
- Little, David A.
|
출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
5 인용 특허 :
16 |
초록
▼
A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell
A turbine engine assembly for a generator including a turbine engine having a compressor section, a combustor section and a turbine section. An air bleed line is in communication with the combustor section for receiving combustor shell air from the combustor section and conveying the combustor shell air as bleed air to a plurality of stages of the turbine section. Bleed air is controlled to flow through the air bleed line when an operating load of the turbine engine assembly is less than a base load of the engine to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section.
대표청구항
▼
1. A turbine engine assembly for a generator, the assembly comprising: a turbine engine having a compressor section, a combustor section and a turbine section, the combustor section having a primary zone temperature (T_PZ) and the turbine engine having a base load;at least one air bleed line in comm
1. A turbine engine assembly for a generator, the assembly comprising: a turbine engine having a compressor section, a combustor section and a turbine section, the combustor section having a primary zone temperature (T_PZ) and the turbine engine having a base load;at least one air bleed line in communication with the combustor section for receiving bleed air comprising combustor shell air from the combustor section;the at least one air bleed line providing cooling air to stationary vanes in a second stage of the turbine section and providing cooling air to stationary vanes in third and fourth stages of the turbine section downstream from the second stage for discharging bleed air into a hot working gas passing through the turbine section;each of the second, third and fourth stages of the turbine section including blades mounted to a common rotor for the compressor section;at least one valve for controlling air flow through the at least one air bleed line;a controller for opening the at least one valve to allow bleed air to flow through the at least one air bleed line when an operating load is less than the base load to bypass air exiting the compressor section around a combustor in the combustor section and effect a flow of high pressure combustor shell air to the stages of the turbine section; andwherein all bleed air for cooling the second, third and fourth stages of the turbine comprises air that has passed from the compressor section to the combustor section to maximize the amount of power that is absorbed at the compressor section prior to passing to the second, third and fourth stages of the turbine section in combination with increasing bleed air flow into the hot working gas to effect in an increased reduction in the temperature of the hot working gas within the turbine section. 2. The turbine engine assembly of claim 1, including at least one heat exchanger for cooling the air flowing in the at least one air bleed line from the combustor section to the turbine section. 3. The turbine engine assembly of claim 2, including a separate air bleed branch line to each of the stages of the turbine section, and a separate heat exchanger in each air bleed branch line for separately cooling bleed air passing to each of the stages of the turbine section. 4. The turbine engine assembly of claim 1, wherein the bleed air provides overcooling to stationary vanes in the second, third and fourth stages of the turbine section thereby providing excess cooling air for discharging into the hot working gas. 5. The turbine engine assembly of claim 4, wherein at least a portion of the bleed air provided to the vanes in the turbine section subsequently passes through the blades of one or more stages of the turbine section. 6. The turbine engine assembly of claim 1, wherein a flow rate through the at least one air bleed line is increased as the operating load is decreased thereby reducing power delivered to the generator while maintaining the T_PZ above a T_PZ lower limit. 7. The turbine engine assembly of claim 6, wherein the T_PZ lower limit is selected so as to maintain CO production at less than about 10 ppmvd at 15% O2. 8. A cooling system for a turbine engine operably coupled to a generator, the system comprising: an air bleed line in communication with a combustor section of the turbine engine, and in communication with a turbine section of the turbine engine;a flow control device for controlling flow through the air bleed line;a controller for actuating the flow control device to allow bleed air to flow through the air bleed line and provide cooling air to the turbine section when an operating load is less than a base load of the turbine engine, wherein substantially all cooling air for the turbine section is obtained from compressor exit air exiting a compressor section of the turbine engine; andwherein the bleed air comprises cooling air provided to a plurality of stages in the turbine section comprising a second stage and one or more subsequent stages of the turbine section defining a path for a hot working gas, each of the stages of the turbine section including blades mounted on a common rotor for the compressor section; andan increasing bleed air flow being provided to the turbine section and discharged into the hot working gas with a decreasing load to effect an increased reduction in the temperature of the hot working gas within the turbine section. 9. The system of claim 8, wherein the bleed air comprises cooling air provided to a plurality of stages in the turbine section comprising said second stage and at least third and fourth stages of the turbine section. 10. The system of claim 8, including at least one heat exchanger for cooling the air flowing in the at least one air bleed line from the combustor section to the turbine section. 11. The system of claim 10, including a separate air bleed branch line to each of the stages of the turbine section, and a separate heat exchanger in each air bleed branch line for separately cooling bleed air passing to each of the stages of the turbine section. 12. The system of claim 8, wherein, when the operating load is less than a base load of the turbine engine, no bleed air is extracted upstream of the compressor exit. 13. A method of operating a turbine engine assembly comprising: sensing a load on a turbine engine for a reduced operating load;bleeding air from a combustor section of the turbine engine to provide bleed air to a turbine section of the turbine engine responsive to the reduced load, wherein substantially all bleed air for the turbine section is obtained from compressor exit air discharged from a compressor section of the turbine engine; andwherein the bleed air comprises cooling air provided to a plurality of stages in the turbine section comprising a second stage and one or more subsequent stages of the turbine section defining a path for a hot working gas, each of the stages of the turbine section including blades mounted on a common rotor for the compressor section; andan increasing bleed air flow being provided to the turbine section and discharged into the hot working gas with a decreasing load to effect an increased reduction in the temperature of the hot working gas within the turbine section. 14. The method of claim 13, further comprising passing the bleed air through at least one heat exchanger and removing heat from the bleed air. 15. The method of claim 14, wherein the turbine section includes said second stage and at least third and fourth stages receiving the bleed air, and including a heat exchanger associated with each of the stages and controlling the temperature of the bleed air going to each of the second, third and fourth stages. 16. The method of claim 13, wherein a flow rate through the at least one air bleed line is increased as the operating load is decreased thereby reducing power delivered to the generator while maintaining the T_PZ above a T_PZ lower limit. 17. The method of claim 16, wherein the T_PZ lower limit is selected so as to maintain CO production at less than about 10 ppmvd at 15% O2. 18. The method of claim 13, wherein the compressor section of the turbine engine includes inlet guide vanes (IGVs) movable to a closed position to restrict air flow into the compressor section, and the method further comprises: a) initially closing the IGVs as the load decreases; andb) subsequently, at a predetermined reduced load, opening the IGVs while increasing the flow of bleed air from the compressor exit to the turbine section during a further decrease in the load. 19. The method of claim 18, wherein the predetermined reduced load is about 60% load. 20. The method of claim 19, wherein the IGVs are closed to a limit closed position when the 60% load is reached.
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