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公开(公告)号：US10767855B2
公开(公告)日：2020-09-08
申请号：US15739371
申请日：2016-06-20
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat , Timothy Hughes , Jonathan May , Ian Wilkinson
Abstract: In a method and system for the combustion of ammonia, wherein a first combustion chamber receives ammonia and hydrogen in controlled proportions, and an oxygen-containing gas such as air. Combustion of the ammonia and hydrogen produces nitrogen oxides among other combustion products. A second combustion chamber receives the nitrogen oxides along with further ammonia and hydrogen in further controlled proportions along with further oxygen-containing gas such as air. The nitrogen oxides are combusted into nitrogen and water.
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公开(公告)号：US10704402B2
公开(公告)日：2020-07-07
申请号：US15315772
申请日：2015-06-01
Applicant: Siemens Aktiengesellschaft
Inventor： Steven Brewer , Ghenadie Bulat , Robert Parke
Abstract: A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile. A thermal barrier coating is located on the internal surface having a first and second thermal barrier coating patch. The first patch having a first thickness located on the internal surface and within a first area subject to a higher temperature than an uncoated part and bounded by a first isotherm of a first temperature. The second patch having a second thickness located on the internal surface and within a second area subject to a higher temperature than the uncoated part and bounded by a second isotherm of a second temperature. The second temperature is higher than the first temperature and the second thickness is thicker than the first thickness.
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公开(公告)号：US20160305666A1
公开(公告)日：2016-10-20
申请号：US15103159
申请日：2014-12-04
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat , Michael Turnbull
Abstract: A method of calibrating a swirler for a burner of a turbine engine, the swirler having a plurality of vanes and a plurality of mixing channels between the vanes, wherein each mixing channel directs air from a radially outer end of the mixing channel to a radially inner end of the mixing channel, the method of calibrating the swirler including: determining a flow characteristic of the swirler, calculating the difference between the determined flow characteristic of the swirler and a predetermined flow characteristic of the swirler, and dependent on the difference, applying a calibration to the swirler to alter its flow characteristic, the calibration having a known influence on the flow characteristic such that the altered flow characteristic is within an acceptable tolerance of the predetermined flow characteristic.
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公开(公告)号：US20210071870A1
公开(公告)日：2021-03-11
申请号：US16643938
申请日：2018-09-03
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat
Abstract: A combustor assembly of a gas turbine engine having a trapped vortex feature to reduce emissions where the trapped vortex is formed using ammonia injected into an annular cavity located in a wall surrounding a combustion chamber of the combustor assembly. The annular cavity, and therefore the trapped vortex, is positioned such that when the combustion occurs within the combustion chamber the position of the annular cavity, and therefore of the trapped vortex, is downstream of a flame front. The emissions resulting from combustion travel through the combustion chamber and pass by the annular cavity before exiting the combustion chamber. The trapped vortex in the combustion chamber supplies NH2 radicals, resulting from the ammonia of the trapped vortex, to the passing by emissions and converts NOx and/or N2O in the emissions to non-polluting products, mainly water and nitrogen.
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公开(公告)号：US20210071590A1
公开(公告)日：2021-03-11
申请号：US16644814
申请日：2018-09-12
Applicant: Siemens Aktiengesellschaft
Inventor： Jadeed Beita , Ghenadie Bulat
IPC: F02C9/32
Abstract: A controller for a gas turbine is arranged to supply a load L. The gas turbine includes a fuel supply arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply includes a first fuel supply and a second fuel supply. The controller is arranged to determine one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR. The controller is further arranged to control a proportion P of the fuel flow rate FF supplied via the first fuel supply based, at least in part, on the determined one or more ratios R. A gas turbine with the controller and a method controls the gas turbine.
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Patent Agency Ranking
公开(公告)号：US20170009598A1
公开(公告)日：2017-01-12
申请号：US15113427
申请日：2015-01-06
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Ghenadie Bulat , Paul Headland
CPC classification number: F01D21/10 , F02C7/30 , F23D2208/10 , F23D2900/00016 , F23N5/16 , F23N5/242 , F23R3/00 , F23R2900/00004 , G01N29/04 , G01N29/07 , G01N2291/0258 , G01N2291/044 , G01N2291/102
Abstract: A method for monitoring a combustor comprising: measuring several times a distance between a first wall of the combustor and either a second wall of the combustor or a sensor of the combustor by the sensor, and concluding from a variation in the distances a formation of deposit on the first and/or second wall and/or sensor, and/or a temperature change within the combustor, and/or a pressure change within the combustor.
Abstract translation: 一种用于监测燃烧器的方法，包括：通过传感器测量燃烧器的第一壁和燃烧器的第二壁或燃烧器的传感器之间的距离的几倍，并且从距离的变化得出沉积物的形成 在第一和/或第二壁和/或传感器上，和/或燃烧器内的温度变化和/或燃烧器内的压力变化。
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7.发明申请公开(公告)号：US20180216820A1
公开(公告)日：2018-08-02
申请号：US15747490
申请日：2016-07-28
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat , Timothy Dolmansley
CPC classification number: F23N5/242 , F02C9/28 , F05D2220/32 , F05D2240/35 , F05D2260/80 , F05D2270/092 , F05D2270/14 , F05D2270/3032 , F05D2270/44 , F23N2023/06 , F23N2023/10 , F23N2025/04 , F23N2025/16 , F23N2041/20 , F23R3/28
Abstract: A method for predicting a combustion error type of a combustion flame. A raw signal of an error parameter of the combustion flame within a predefined time span is measured, the error parameter is adapted for determining the combustion error type. A predefined frequency range from the raw signal is extracted using a by-pass filter, where the raw signal is decomposed. The number of peaks of the predefined frequency range within the time span is counted. An actual reference value is determined by dividing the number of counted peaks by the time span. The actual reference value is compared with a nominal reference value, wherein the nominal reference value is determined by dividing a predefined number of peaks of the predefined frequency range by the time span, so that the combustion error type is predictable if the actual reference value differs to the nominal reference value.
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公开(公告)号：US20180172277A1
公开(公告)日：2018-06-21
申请号：US15739286
申请日：2016-07-04
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat , Jonathan May
CPC classification number: F23R3/286 , F02C3/22 , F05D2220/32 , F05D2240/35 , F23C2900/9901 , F23C2900/99011 , F23R3/14 , F23R3/36 , F23R2900/00002 , F23R2900/00013
Abstract: A burner for a gas turbine, having a combustion chamber, a first injector adapted to inject a first fuel into the combustion chamber and a second injector adapted to inject a second fuel being less reactive than the first fuel into the combustion chamber, wherein the burner is adapted to premix the fuels with an air flow before the fuel enter the reaction zone of the combustion chamber such that a first fuel flow of the first fuel has a first premixing stream line and a second fuel flow of the second fuel has a second premixing stream line, wherein each of the premixing stream lines begins with the beginning of the premixing with the air flow and ends at the location where the fuel enters the reaction zone and the length of the second premixing stream line is longer than the length of the first premixing stream line.
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公开(公告)号：US20180156458A1
公开(公告)日：2018-06-07
申请号：US15576970
申请日：2016-05-24
Applicant: Siemens Aktiengesellschaft
Inventor： Ghenadie Bulat
CPC classification number: F23N5/242 , F01D17/085 , F02C3/20 , F23R3/28 , F23R2900/00013
Abstract: A method for controlling an engine vibration of a gas turbine engine where engine vibration of the gas turbine engine is measured. The measured engine vibration is compared with a threshold value of a nominal engine vibration. A fuel supply parameter of a fuel supply to a combustion chamber of the gas turbine engine is controlled for controlling combustion dynamics of a combustion flame within the combustion chamber. The engine vibration of the gas turbine engine is indicative of the combustion dynamics of the combustion flame, so that the fuel supply is adjusted for controlling the combustion dynamics if the measured engine vibration exceeds the threshold value of the nominal engine vibration.
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10.发明申请公开(公告)号：US20170107833A1
公开(公告)日：2017-04-20
申请号：US15315772
申请日：2015-06-01
Applicant: Siemens Aktiengesellschaft
Inventor： Steven Brewer , Ghenadie Bulat , Robert Parke
Abstract: A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile. A thermal barrier coating is located on the internal surface having a first and second thermal barrier coating patch. The first patch having a first thickness located on the internal surface and within a first area subject to a higher temperature than an uncoated part and bounded by a first isotherm of a first temperature. The second patch having a second thickness located on the internal surface and within a second area subject to a higher temperature than the uncoated part and bounded by a second isotherm of a second temperature. The second temperature is higher than the first temperature and the second thickness is thicker than the first thickness.
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