[특허]Method and system for controlling a set point for extracting air from a compressor to provide turbine cooling air in a gas turbine

General Electric Company

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특허 상세정보

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Method and system for controlling a set point for extracting air from a compressor to provide turbine cooling air in a gas turbine

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02C-007/18 F02C-009/18
미국특허분류(USC)	060/782; 060/785; 060/795; 060/806
출원번호	US-0120621 (2008-05-14)
등록번호	US-8240153 (2012-08-14)
발명자 / 주소	Childers, Priscilla Disch, Mark Newton, III, Curtis Ball, Jr., David Wesley Whaling, Kenneth Neil Truesdale, Alan Meier
출원인 / 주소	General Electric Company
대리인 / 주소	Nixon & Vanderhye P.C.
인용정보	피인용 횟수 : 73 인용 특허 : 5

초록
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A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine including: extracting compressed air from a low pressure and a high pressure stage of the compressor; adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging the combined air as turbine cooling air; bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage; in response to turning on the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air, and adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

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1. A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine, the method comprising: extracting compressed air from a low pressure stage of the compressor and from a high pressure stage of the compressor;adding in an ejector the extracted compressed air from the low pressure stage to the extracted air from the high pressure stage and discharging the compressed air from the ejector to the turbine cooling air;bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage, wherein the bypass portion enters the turbine cooling air discharged from the ejector;adjusting the flow of the extracted compressed air from the low pressure stage to the ejector;in response to adjusting the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air;adjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point. 2. The method of claim 1 wherein the low pressure stage is a stage no higher than a tenth stage of the compressor and the high pressure stage is a stage no lower than an eleventh stage of the compressor. 3. The method of claim 1 wherein the pressure ratio is of the pressure of the turbine cooling air and a pressure of compressed air a discharge of the compressor to a combustor of the gas turbine. 4. The method of claim 1 wherein the changing of the set point is a step change in which the set point is immediately increased contemporaneously with the adjusting of the flow of extracted compressed air from the low pressure stage to the ejector, and the set point is subsequently reduced. 5. The method of claim 4 wherein the step change occurs for no more than ten seconds. 6. The method of claim 4 wherein the step change is sufficiently large to prevent the actual pressure ratio from traversing a predetermined pressure level. 7. The method of claim 1 wherein the set point is changed in response to adjusting the flow of the extracted compressed air from the low pressure stage to the ejector, and adjusting a bypass valve to make the adjustment to the bypass flow. 8. A method for controlling the position of a bypass valve in a system for providing turbine cooling air from air extracted from a compressor in a gas turbine, wherein the bypass valve regulates compressed air extracted from a high compressor stage bypassing an ejector which mixes extracted compressed air from the high compressor stage with extracted compressed air from a low compressor stage, and wherein the flow of bypass extracted compressed air and compressed air from the ejector are combined to form turbine cooling air, the method comprising: adjusting the flow of the extracted compressed air from the low pressure stage to the ejector after blocking the flow of the extracted compressed air from the low pressure stage to the ejector;in response to adjustment of the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air; andadjusting the bypass valve in response to the changed set point to allow for additional bypass airflow and thereby cause the actual pressure ratio to approach the changed set point. 9. The method of claim 8 wherein the low pressure stage is a stage no higher than a tenth stage of the compressor and the high pressure stage is a stage no lower than an eleventh stage of the compressor. 10. The method of claim 8 wherein the pressure ratio is a ratio of the pressure of the turbine cooling air and a pressure of compressed air at a discharge of the compressor to a combustor of the gas turbine. 11. The method of claim 8 wherein the changing of the set point is a step change in which the set point is immediately increased contemporaneously with the turning on of the flow of extracted compressed air from the low pressure stage to the ejector, and the set point is subsequently reduced. 12. The method of claim 11 wherein the step change occurs for no more than ten seconds. 13. The method of claim 11 wherein the step change is sufficiently large to prevent the actual pressure ratio from traversing a predetermined pressure level. 14. The method of claim 8 wherein the set point is changed in response to turning on of the flow of the extracted compressed air from the low pressure stage to the ejector, and adjusting a bypass valve to make the adjustment to the bypass flow. 15. A system for controlling the position of a turbine cooling air bypass valve in a gas turbine having a compressor and a turbine, the system comprising: a low pressure extraction port of compressed air from a low stage of the compressor;a high pressure extraction port of compressed air from a high stage of the compressor;an ejector receiving a portion of the extracted compressed air from both the low stage and high stage;a valve upstream of the ejector and controlling whether extracted compressed air from the low stage reaches the ejector;a bypass valve in a bypass conduit circumventing the ejector and regulating a second portion of the extracted compressed air from the high stage compressor that bypasses the ejector and is combined with turbine cooling air discharged by the ejector, anda controller which responds to a command to open the valve upstream of the ejector, changes a set point for an actual pressure ratio that includes a pressure of the turbine cooling air and the change in the setpoint causes the controller to adjust the bypass valve to allow for additional bypass airflow and thereby cause the actual pressure ratio to approach the changed set point. 16. The system of claim 15 wherein the low pressure stage is a stage no higher than a tenth stage of the compressor and the high pressure stage is a stage no lower than an eleventh stage of the compressor. 17. The system of claim 15 wherein the pressure ratio is of the pressure of the turbine cooling air and a pressure of compressed air at a discharge of the compressor to a combustor of the gas turbine. 18. The system of claim 15 wherein the changing of the set point is a step change in which the set point is immediately increased contemporaneously with the turning on of the flow of extracted compressed air from the low pressure stage to the ejector, and the set point is subsequently reduced. 19. The system of claim 18 wherein the step change occurs for no more than ten seconds. 20. The system of claim 18 wherein the step change is sufficiently large to prevent the actual pressure ratio from traversing a predetermined pressure level. 21. A method for controlling the generation of turbine cooling air from air extracted from a compressor of a gas turbine, the method comprising: extracting compressed air from a low pressure stage of the compressor and from a high pressure stage of the compressor;adding in an ejector the compressed air from the low pressure stage to the air from the high pressure stage and discharging from the ejector the turbine cooling air;bypassing the ejector with a bypass portion of the extracted compressed air from the high pressure stage, wherein the bypass portion enters the turbine cooling air discharged from the ejector;adjusting the flow of the extracted compressed air from the low pressure stage to the ejector after blocking the flow of the extracted compressed air from the low pressure stage to the ejector;in response to adjusting the flow of extracted compressed air from the low pressure stage, changing a set point for an actual pressure ratio that includes a pressure of the turbine cooling air; andadjusting the bypass flow in response to the changed set point to cause the actual pressure ratio to approach the changed set point.

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 73

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Method and system for controlling a set point for extracting air from a compressor to provide turbine cooling air in a gas turbine

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Method and system for controlling a set point for extracting air from a compressor to provide turbine cooling air in a gas turbine

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이 특허에 인용된 특허 (5)

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