최소 단어 이상 선택하여야 합니다.
최대 10 단어까지만 선택 가능합니다.
다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
NTIS 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
DataON 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Edison 바로가기다음과 같은 기능을 한번의 로그인으로 사용 할 수 있습니다.
Kafe 바로가기국가/구분 | United States(US) Patent 등록 |
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국제특허분류(IPC7판) |
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출원번호 | US-0557068 (2014-12-01) |
등록번호 | US-10030588 (2018-07-24) |
발명자 / 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 | 피인용 횟수 : 0 인용 특허 : 526 |
In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change
In an embodiment, a method includes performing a turbine combustor diagnostic routine including operating a first turbine combustor of a plurality of turbine combustors at a substantially steady state of combustion; adjusting an operational parameter of the first turbine combustor to cause a change in combustion products produced by the first turbine combustor; identifying a first sensor response of a first subset of a plurality of sensors disposed within or downstream from a turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors; correlating the first subset of sensors with the first turbine combustor; and diagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response.
1. A system, comprising: a gas turbine system, comprising: a turbine combustion system comprising a plurality of turbine combustors, including a first turbine combustor, each combustor of the plurality of turbine combustors being configured to combust a fuel/oxidant mixture to produce combustion pro
1. A system, comprising: a gas turbine system, comprising: a turbine combustion system comprising a plurality of turbine combustors, including a first turbine combustor, each combustor of the plurality of turbine combustors being configured to combust a fuel/oxidant mixture to produce combustion products;a turbine driven by the combustion products produced by the turbine combustion system;a plurality of sensors positioned downstream of the turbine combustion system and configured to monitor one or more parameters of the combustion products; anda control system comprising one or more non-transitory machine-readable media collectively storing one or more sets of instructions executable by a processor to perform a diagnostic routine comprising: adjusting, at a first time, an operational parameter of the first turbine combustor of the plurality of turbine combustors to cause a change in the combustion products produced by the first turbine combustor;identifying, at a second time, a respective sensor response of a first sensor of the plurality of sensors that detects the change in the combustion products, the respective sensor response comprising a delay time being between the first time and the second time;correlating the respective sensor response with the first turbine combustor; andcomparing the delay time of the respective sensor response to an expected delay time of an expected sensor response to diagnose a condition of the first sensor, the expected delay time being between the first time and a third time at which the respective sensor response is expected to occur; andwherein, when the delay time is not within a predetermined tolerance of the expected delay time, the control system diagnoses a degraded state of the first sensor and utilizes sensors adjacent to the first sensor to monitor the one or more parameters of the combustion products produced by the first turbine combustor. 2. The system of claim 1, wherein the control system performs a corrective action, provides a user-perceivable indication, or a combination thereof, when the respective sensor response is not within the predetermined tolerance. 3. The system of claim 2, further comprising comparing an actual position of the first sensor having the respective sensor response to an expected position of a sensor expected to have the respective sensor response, and wherein the control circuitry uses the actual position of the first sensor having the respective sensor response when the actual position and the expected position are not the same. 4. The system of claim 3, wherein the diagnostic routine comprises: using the actual position of the first sensor to generate swirl angle information of combustion products produced by the first turbine combustor; andcomparing the generated swirl angle information to expected swirl angle information for the combustion products produced by the first turbine combustor, andwherein, when the generated swirl angle information is not within a predetermined tolerance of the expected swirl angle, the control system diagnoses a poor fit for the expected swirl angle and updates the expected swirl angle using the generated swirl angle information. 5. The system of claim 2, wherein, when the respective sensor response of the first sensor is within the predetermined tolerance of the expected response, the turbine combustor diagnostic routine re-adjusts operation of the first turbine combustor to normal operation, and begins testing a second turbine combustor of the plurality of turbine combustors. 6. The system of claim 5, wherein normal operation comprises combustion of the fuel/oxidant mixture at a predetermined equivalence ratio in the presence of an exhaust gas diluent. 7. The system of claim 6, wherein the predetermined equivalence ratio is between approximately 0.95 and 1.05, and wherein a sensor of the plurality of sensors is a wideband oxygen sensor. 8. The system of claim 1, wherein adjusting the operational parameter of the first turbine combustor of the plurality of turbine combustors comprises adjusting a fuel/oxidant ratio in the first turbine combustor by adjusting a fuel level trim valve such that the expected sensor response is indicative of a particular fuel/oxidant ratio in the first turbine combustor; wherein, when the respective sensor response of the first sensor of the plurality of sensors is not within an additional predetermined tolerance of the particular fuel/oxidant ratio, the control system uses a sensor of the plurality of sensors that is adjacent to the first sensor to monitor the fuel/oxidant ratio, provides a fault indication of the first sensor, or a combination thereof. 9. The system of claim 8, wherein, when the respective sensor responses of all of the plurality of sensors are not within the additional predetermined tolerance of the particular fuel/oxidant ratio, the control system provides a fault indication of multiple sensors, including the first sensor, provides a fault indication of the first turbine combustor, adjusts the operation of the first turbine combustor, or any combination thereof. 10. The system of claim 1, comprising: an exhaust gas compressor driven by the turbine, wherein the exhaust gas compressor is configured to compress exhaust gas generated by the turbine from the combustion products and supply the compressed exhaust gas to the turbine combustion system as an exhaust gas diluent; andan exhaust gas recirculation (EGR) system configured to recirculate the exhaust gas along an exhaust recirculation path from the turbine to the exhaust gas compressor. 11. A method for performing the diagnostic routine, using the control system of claim 1, comprising the acts of: operating the first turbine combustor of the plurality of turbine combustors at a substantially steady state of combustion;adjusting the operational parameter of the first turbine combustor to cause the change in combustion products produced by the first turbine combustor;identifying a first sensor response of a first subset of the plurality of sensors disposed within or downstream from the turbine fluidly coupled to the turbine combustor, the first sensor response being indicative of the change in the combustion products, and wherein the first subset comprises one or more first sensors;correlating the first subset of sensors with the first turbine combustor; anddiagnosing a condition of the first subset of the plurality of sensors, the first turbine combustor, or a combination thereof, based on the first sensor response. 12. The method of claim 11, wherein adjusting the operational parameter of the first turbine combustor comprises adjusting a flow of compressed exhaust gas diluent to the first turbine combustor to cause a change in combustion temperature, or adjusting a flow of fuel or oxidant to the first turbine combustor to cause a change in a combustion equivalence ratio of the first turbine combustor. 13. The method of claim 11, comprising: determining whether the first subset of sensors corresponds to an expected subset of sensors correlated to the first turbine combustor; andde-correlating the expected subset of sensors if the expected subset of sensors and the first subset of sensors do not match, or updating swirl angle information correlated to the first turbine combustor if the expected subset of sensors and the first subset of sensors do not match, or a combination thereof. 14. The method of claim 11, comprising: determining whether the first sensor response is within a predetermined tolerance of an expected sensor response; andproviding an indication of a fuel to oxidant ratio shift when the first sensor response is indicative of a first combustion equivalence ratio, the expected sensor response is indicative of a second combustion equivalence ratio, and the first and second combustion equivalence ratios do not match within the predetermined tolerance. 15. The method of claim 14, comprising adjusting the operational parameter, an additional operational parameter, or a combination thereof, of the first turbine combustor until the first and second combustion equivalence ratios match within the predetermined tolerance. 16. The method of claim 11, wherein when the first sensor response is within the predetermined tolerance of the expected sensor response, the turbine combustor diagnostic routine re-adjusts operation of the first turbine combustor to the substantially steady state of combustion, and begins testing a second turbine combustor of the plurality of turbine combustors. 17. The method of claim 11, wherein identifying the first sensor response comprises identifying a first time delay between the adjustment of the operational parameter and the first sensor response, and wherein the turbine combustor diagnostic routine comprises determining whether the first time delay is within a predetermined time delay range, and providing a sensor fault indication when the first time delay is not within the predetermined time delay range. 18. The method of claim 11, wherein identifying the first sensor response of the first subset of the plurality of sensors comprises identifying a location of the first subset of the plurality of sensors, and determining whether the first sensor response is homogeneous across the entire first subset when the first subset comprises more than one sensor. 19. The method of claim 11, wherein operating the first turbine combustor of the plurality of turbine combustors at the substantially steady state of combustion comprises operating the first turbine combustor at a combustion equivalence ratio of between approximately 0.95 and 1.05 and combusting the fuel/oxidant mixture in the presence of a recirculated exhaust gas recirculated from the turbine, and wherein each sensor of the plurality of sensors is a wideband oxygen sensor. 20. A system, comprising: one or more tangible, machine-readable media collectively storing one or more sets of instructions executable by a processor to perform a diagnostic routine comprising: operating a first turbine combustor of a plurality of turbine combustors at a combustion equivalence ratio of between approximately 0.95 and 1.05;adjusting, at a first time, a flow of fuel, a flow of oxidant, or a combination thereof, to the first turbine combustor to cause combustion products produced by the first turbine combustor to change from first combustion products to second combustion products that are different than the first combustion products;identifying, at a second time, a first sensor response of a first sensor that detects the second combustion products, the first sensor being one of a plurality of sensors positioned downstream of the plurality of turbine combustors and the first sensor response comprising a delay time being between the first time and the second time;correlating the first sensor response with the first turbine combustor; andcomparing the delay time of the first sensor response to an expected delay time of an expected sensor response to diagnose a condition of the first sensor, the expected delay time being between the first time and a third time at which the first sensor response is expected to occur. 21. The system of claim 20, wherein adjusting the flow of fuel, the flow of the oxidant, or a combination thereof, to the first turbine combustor comprises increasing the flow of the fuel such that the second combustion products comprise a higher concentration of uncombusted fuel than the first combustion products, wherein the first sensor response comprises a first fuel to oxidant ratio, and wherein the diagnostic routine comprises comparing the first fuel to oxidant ratio of the first sensor response with a second fuel to oxidant ratio of the expected sensor response. 22. The system of claim 21, wherein, when the delay time of the first sensor response does not fall within a tolerance range of the expected delay time of the expected sensor response, the diagnostic routine comprises providing a sensor fault indication for the first sensor, and utilizes at least a second sensor of the plurality of sensors for monitoring combustion products produced by the first turbine combustor, the second sensor being adjacent to the first sensor. 23. The system of claim 21, wherein, when a predetermined number of the plurality of sensors have respective sensor responses that do not fall within a tolerance range of respective expected sensor responses, the diagnostic routine comprises providing a combustor fault indication for the first turbine combustor.
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