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-0312665 (2014-06-23) |
등록번호 | US-9617914 (2017-04-11) |
발명자 / 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
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인용정보 | 피인용 횟수 : 0 인용 특허 : 530 |
A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of extraction passages, wherein the plurality of sensors is confi
A system includes a plurality of extraction passages configured to passively extract a portion of a gas flow from a downstream region of a gas flow path. The system includes a plurality of sensors respectively coupled to the plurality of extraction passages, wherein the plurality of sensors is configured to measure one or more parameters of the portion of the gas flow traversing the plurality of extraction passages. The system also includes a manifold coupled to the plurality of extraction passages, wherein the manifold is configured to receive the portion of the gas flow from the plurality of extraction passages. The system further includes a return passage coupled to the manifold, wherein the return passage is configured to passively provide the portion of the gas flow to an upstream region of the gas flow path.
1. A system, comprising: a gas turbine engine, comprising: a combustor section having one or more combustors configured to combust a fuel and produce an exhaust gas;a turbine section comprising one or more turbine stages disposed downstream from the combustor and configured to be driven by the exhau
1. A system, comprising: a gas turbine engine, comprising: a combustor section having one or more combustors configured to combust a fuel and produce an exhaust gas;a turbine section comprising one or more turbine stages disposed downstream from the combustor and configured to be driven by the exhaust gas;an exhaust section disposed downstream from the one or more turbine stages, wherein the exhaust section comprises an exhaust passage configured to receive the exhaust gas from the turbine section; anda gas flow extraction system coupled to the exhaust section and comprising a plurality of extraction passages disposed about the exhaust section, wherein each extraction passage is configured to receive a portion of the exhaust gas from a downstream portion of the exhaust passage, wherein the gas flow extraction system is configured to passively route the portion of the exhaust gas to an upstream portion of the exhaust passage via one or more return passages, and wherein the gas flow extraction system comprises a ring manifold disposed around the exhaust section and coupled to each of the plurality of extraction passages, and wherein the ring manifold, the plurality of extraction passages, and the one or more return passages are configured to allow condensate to accumulate and to be drained from a low point in the gas flow extraction system. 2. The system of claim 1, wherein each of the plurality of extraction passages comprises one or more sensors. 3. The system of claim 2, wherein the one or more sensors comprise an oxygen sensor, a carbon monoxide sensor, a nitrogen oxide (NOx) sensor, a water vapor sensor, a hydrogen sensor, an unburnt fuel sensor, or a combination thereof. 4. The system of claim 2, wherein the one or more sensors comprise a wide-band lambda sensor. 5. The system of claim 2, wherein the one or more sensors comprise a universal exhaust gas oxygen (UEGO) sensor. 6. The system of claim 2, comprising a controller coupled to the one or more sensors, wherein the controller is configured to control operation of the gas turbine engine based, at least in part, on respective outputs of the one or more sensors. 7. The system of claim 1, wherein the one or more return passages comprise one or more internal return passages that are disposed substantially within a portion of the exhaust section. 8. The system of claim 1, wherein the one or more return passages comprises one or more external return passages that are disposed substantially outside of the exhaust section. 9. The system of claim 1, comprising a compressor section configured to compress and route the exhaust gas to the combustor section; andan exhaust gas recirculation loop coupled to the exhaust section and to the compressor section, wherein the exhaust gas recirculation loop is configured to receive the exhaust gas from the exhaust section and to provide the exhaust gas to the compressor section. 10. A method, comprising: combusting a fuel with an oxidant in a combustor of a gas turbine system to generate an exhaust gas;driving a turbine of the gas turbine system with the exhaust gas from the combustor;providing the exhaust gas from the turbine through an exhaust passage in an exhaust section of the gas turbine system;passively extracting a portion of the exhaust gas from a downstream portion of the exhaust passage via one or more extraction passages;performing one or more measurements on the portion of the exhaust gas using one or more sensors coupled to the one or more extraction passages;passively routing the portion of the exhaust gas from the one or more extraction passages to a ring manifold; andpassively routing the portion of the exhaust gas from the ring manifold to an upstream portion of the exhaust passage via one or more return passages. 11. The method of claim 10, comprising determining one or more properties of the portion of the exhaust gas based on the one or more measurements. 12. The method of claim 11, wherein the one or more properties comprise an oxygen content, a water vapor content, a nitrogen oxide (NOx) content, a carbon monoxide content, a hydrogen content, an unburnt fuel content, or a combination thereof. 13. The method of claim 11, comprising adjusting one or more parameters of the gas turbine system based, at least in part, on the one or more properties of the portion of the exhaust gas, wherein adjusting the one or more parameters of the gas turbine system comprises adjusting one or more of a fuel mixture, a fuel flow rate, an oxidant intake rate, a fuel-oxidant ratio, an exhaust gas recirculation rate, or an equivalence ratio of combustion. 14. The method of claim 10, wherein passively extracting the portion of the exhaust gas comprises opening one or more valves associated with each of the one or more extraction passages to allow the portion of the exhaust gas to traverse the one or more extraction passages. 15. The method of claim 10, wherein the one or more measurements comprise temperature measurements, flow rate measurements, pressure measurements, composition measurements, or a combination thereof. 16. The method of claim 10, wherein combusting the fuel comprises stoichiometrically combusting the fuel with the oxidant and exhaust gas. 17. A system, comprising: a gas flow path through a rotary machine, wherein the gas flow path comprises a high-pressure region and a low-pressure region;an extraction passage configured to passively extract a portion of a gas flow from the high-pressure region of the gas flow path;a sensor coupled to the extraction passage, wherein the sensor is configured to measure a parameter of the portion of the gas flow traversing the extraction passage; anda return passage coupled to the extraction passage, wherein the return passage is configured to passively route the portion of the gas flow from the extraction passage to the low-pressure region of the gas flow path, and wherein the return passage comprises one or more external return passages that are disposed substantially outside of an exhaust section. 18. The system of claim 17, wherein the portion of the gas flow is less than approximately 1% of the gas flow. 19. The system of claim 17, wherein a flow rate of the portion of the gas flow is based, at least in part, on a diameter of the extraction passage, a position of the extraction passage in the high-pressure region, a diameter of the return passage, and a position of the return passage in the low-pressure region. 20. The system of claim 17, wherein the rotary machine comprises an exhaust section, a compressor section, or a recycle blower of a gas turbine system. 21. The system of claim 17, wherein the extraction passage comprises a first isolation valve disposed upstream of the sensor and a second isolation valve disposed downstream of the sensor, wherein the first and second isolation valves, when closed, are configured to block the portion of the gas flow past the sensor to enable replacement of the sensor while the system is operational. 22. The system of claim 17, comprising a manifold coupled to the extraction passage and the return passage, wherein the manifold is configured to receive the portion of the gas flow from the extraction passage and to provide the portion of the gas flow to the return passage. 23. The system of claim 17, comprising a plurality of return passage sensors coupled to the return passage, wherein the plurality of return passage sensors is configured to measure the parameter of the portion of the gas flow traversing the return passage.
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