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公开(公告)号：US20210190319A1
公开(公告)日：2021-06-24
申请号：US16771060
申请日：2018-11-15
Applicant: Siemens Aktiengesellschaft
Inventor： Matthias Gralki , Marvin Hümbs , Claus Krusch , Daniel Schmidt , Holger Grote , Marc Tertilt
Abstract: A combustion chamber with a jacket arranged around a principal axis of the combustion chamber, a ceramic tube that is arranged inside the jacket, wherein an intermediate layer is arranged between the jacket and the ceramic tube. The jacket is at least partially conical. The ceramic tube is under axial stress in the jacket along the principal axis. The ceramic tube is an assembly of multiple heat shield segments. The heat shield segments each have a hot side that is designed to come into contact with a hot medium, a cold side that is opposite the hot side and is oriented toward the jacket, and a circumferential rim between the hot side and the cold side. In the cold state, individual heat shield segments of a segment row have, on the rim, bearing surfaces that the adjoin the cold side and gaps that open toward the hot gas side.
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公开(公告)号：US20150369137A1
公开(公告)日：2015-12-24
申请号：US14768095
申请日：2014-02-12
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Thorsten Engler , Markus Gorynski , Manuel Gutermuth , Philipp Kreutzer , Marco Link , Nicolas Savilius , Kai Suselbeck , Marc Tertilt
CPC classification number: F02C9/20 , F02C3/04 , F02C9/22 , F02C9/28 , F05D2220/32 , F05D2270/05 , F05D2270/08 , F05D2270/083 , F05D2270/303 , F23N2041/20 , F23N2900/05001
Abstract: A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.
Abstract translation: 用于将燃气涡轮机操作在低于标称功率的方法包括：确定燃气轮机的较低功率阈值，其使燃气涡轮机离开燃气轮机的CO排放兼容部分负载范围; 为输出燃气轮机功率提供指定的阈值，其中指定的阈值小于燃气轮机的额定功率; 以及在恒定排气温度下将燃气轮机的输出燃气涡轮机功率操作在特定阈值以上，其中燃气轮机的压缩机的入口引导叶片进一步关闭，以便降低输出燃气轮机功率。 选择足够大的阀用于规定的阈值，使得主区域温度，燃烧温度和排气温度的增加超过尽可能大的燃气涡轮机的CO排放兼容的部分负载范围。
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3.发明申请PARTIAL-LOAD OPERATION OF A GAS TURBINE WITH AN ADJUSTABLE BYPASS FLOW CHANNEL 审中-公开具有可调节旁通流量通道的气体涡轮机的部分负载运行公开(公告)号：US20160273457A1
公开(公告)日：2016-09-22
申请号：US15030931
申请日：2014-10-23
Applicant: Siemens Aktiengesellschaft
Inventor： Thorsten Engler , Manuel Gutermuth , Thomas Kerstiens , Matthias Kleinenhammann , Norbert Knüwer , Kai Süselbeck , Marc Tertilt , Ulrich Wagner , Frank Weidner
Abstract: A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%.
Abstract translation: 燃气轮机具有提供压缩空气的压缩机，设置有燃烧器的燃烧室和膨胀涡轮机，其中还设置有旁路流动通道，其设计成供应经过燃烧器的压缩空气并提供在燃烧中产生的热气流 在燃气轮机的运行期间。 可以调节旁通流路的开口横截面，并且设计调节单元以调节旁通流动通道的开口横截面，使得选择开口横截面的修改速度，使得相对燃烧室压降 或者燃烧室的材料温度基本恒定，特别是燃烧室的相对燃烧室压降或材料温度不变化大于10％。
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公开(公告)号：US20160024960A1
公开(公告)日：2016-01-28
申请号：US14777319
申请日：2014-02-20
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Thorsten Engler , Markus Gorynski , Manuel Gutermuth , Philipp Kreutzer , Marco Link , Nicolas Savilius , Kai Suselbeck , Marc Tertilt
CPC classification number: F01D17/16 , F01D9/041 , F01D17/08 , F01D17/085 , F01D25/02 , F02C7/04 , F02C7/057 , F05D2220/32 , F05D2240/12 , F05D2270/301 , F05D2270/303 , F05D2270/311
Abstract: A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.
Abstract translation: 燃气轮机包括进气道和具有压缩机流动通道的压缩机。 压缩机还包括定位在压缩机流动通道中的入口引导叶片排，其具有可以调节的入口导向叶片。 燃气轮机具有结冰传感器单元，其具有布置在第一压缩机叶片排和第一压缩机引导叶片排之间的至少一个传感器。 因此，第一压缩机叶片排布置在直接在入口引导叶片排的下游的压缩机流动通道中，并且第一压缩机引导叶片排直接布置在第一压缩机叶片排的下游。 一种方法检测压缩机即将结冰，并且压缩机得到保护，使得至少入口引导叶片排的入口引导叶片被调节，使得进气体质量流的加速度减小。
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公开(公告)号：US10408135B2
公开(公告)日：2019-09-10
申请号：US14768095
申请日：2014-02-12
Applicant: Siemens Aktiengesellschaft
Inventor： Thorsten Engler , Markus Gorynski , Manuel Gutermuth , Philipp Kreutzer , Marco Link , Nicolas Savilius , Kai Suselbeck , Marc Tertilt
Abstract: A method for operating a gas turbine below the nominal power includes: determining a lower power threshold value of the gas turbine which causes the gas turbine to leave a CO-emission-compliant partial load range of the gas turbine; providing a specified threshold value for output gas turbine power, wherein the specified threshold value is less than the nominal power of the gas turbine; and operating the gas turbine at an output gas turbine power above the specified threshold value at a constant exhaust gas temperature, wherein the inlet guide blades of a compressor of the gas turbine are closed further in order to reduce the output gas turbine power. A sufficiently large valve is selected for the specified threshold value so that increases of the primary zone temperature, combustion temperature, and exhaust temperature extend over a CO-emission-compliant partial load range of the gas turbine that is as large as possible.
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Patent Agency Ranking
公开(公告)号：US20160010566A1
公开(公告)日：2016-01-14
申请号：US14768827
申请日：2014-02-06
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Andreas Bottcher , Eberhard Deuker , Andre Kluge , Philipp Kreutzer , Marco Link , Ansgar Sternemann , Marc Tertilt , Martin Wilke
CPC classification number: F02C9/20 , F01K23/10 , F02C3/04 , F02C6/18 , F02C7/141 , F02C7/16 , F05D2220/32 , F05D2260/2322 , F05D2270/083
Abstract: A method for operating a gas turbine below its rated power, in which CO emissions in the exhaust gas of the gas turbine increase with a reduction of the output gas turbine power, wherein, if a predefined threshold value, which can be selected as desired, for the CO emissions is reached or if a predefined threshold value, specified in relative or absolute terms, for the output gas turbine power is undershot, the combustion temperature in the combustion chamber of the gas turbine is increased. To operate the gas turbine with low emissions, for a constant power output, the exhaust-gas temperature increase generated at the outlet of the gas turbine as a result of the combustion temperature increase is at least partially compensated through the addition of a liquid or vaporous medium.
Abstract translation: 一种将燃气轮机运转低于其额定功率的方法，其中燃气轮机废气中的CO排放随着输出燃气轮机功率的减小而增加，其中如果可以根据需要选择预定义的阈值， 为了达到CO排放，或者如果输出燃气轮机功率的相对或绝对值规定的预定阈值不足，则燃气轮机的燃烧室内的燃烧温度升高。 为了操作具有低排放的燃气轮机，为了恒定功率输出，由于燃烧温度升高而在燃气轮机的出口处产生的废气温度升高至少部分地通过添加液体或蒸气来补偿 中。
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公开(公告)号：US10408451B2
公开(公告)日：2019-09-10
申请号：US14915230
申请日：2014-09-10
Applicant: Siemens Aktiengesellschaft
Inventor： Marco Larson , Marc Tertilt
Abstract: A heat shield element for a heat shield has a support structure. The heat shield element includes a hot side which can be exposed to hot gas, a cold side opposite the hot side, and peripheral sides connecting the hot side to the cold side. The heat shield element can be fastened to the support structure of the heat shield with the cold side facing the support structure and has a height running vertically to the cold side. The height of the heat shield element increases in a rising direction, the rising portion of the heat shield element running in the rising direction substantially up to at least one peripheral side or up to a projection that extends the hot side over the base surface of the cold side.
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公开(公告)号：US09915166B2
公开(公告)日：2018-03-13
申请号：US14777319
申请日：2014-02-20
Applicant: Siemens Aktiengesellschaft
Inventor： Thorsten Engler , Markus Gorynski , Manuel Gutermuth , Philipp Kreutzer , Marco Link , Nicolas Savilius , Kai Suselbeck , Marc Tertilt
CPC classification number: F01D17/16 , F01D9/041 , F01D17/08 , F01D17/085 , F01D25/02 , F02C7/04 , F02C7/057 , F05D2220/32 , F05D2240/12 , F05D2270/301 , F05D2270/303 , F05D2270/311
Abstract: A gas turbine includes an intake tract and a compressor having a compressor flow channel. The compressor further includes an inlet guide vane row positioned in the compressor flow channel having inlet guide vanes that can be adjusted. The gas turbine has an icing sensor unit having at least one sensor arranged between a first compressor blade row and a first compressor guide vane row. The first compressor blade row is thereby arranged in the compressor flow channel directly downstream of the inlet guide vane row, and the first compressor guide vane row is arranged directly downstream of the first compressor blade row. A method detects an imminent icing of the compressor, and the compressor is safeguarded therefrom such that at least inlet guide vanes of the inlet guide vane row are adjusted such that the acceleration of an intake air mass flow is reduced.
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公开(公告)号：US10774751B2
公开(公告)日：2020-09-15
申请号：US15030931
申请日：2014-10-23
Applicant: Siemens Aktiengesellschaft
Inventor： Thorsten Engler , Manuel Gutermuth , Thomas Kerstiens , Matthias Kleinenhammann , Norbert Knüwer , Kai Süselbeck , Marc Tertilt , Ulrich Wagner , Frank Weidner
Abstract: A gas turbine has a compressor providing compressed air, a combustion chamber provided with a burner, and an expansion turbine, wherein a bypass flow channel is also provided designed to supply compressed air past the burner and to supply a hot gas flow generated in the combustion chamber during operation of the gas turbine. The opening cross section of the bypass flow channel can be adjusted, and an adjustment unit is designed to adjust the opening cross section of the bypass flow channel such that the modification speed of the opening cross section is selected such that the relative combustion chamber pressure drop or a material temperature of the combustion chamber is substantially constant, in particular that the relative combustion chamber pressure drop or the material temperature of the combustion chamber does not vary by more than 10%.
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公开(公告)号：US10088163B2
公开(公告)日：2018-10-02
申请号：US14773345
申请日：2014-02-07
Applicant: Siemens Aktiengesellschaft
Inventor： Christian Beck , Simon Bez , Bjorn Buchholz , Thomas Grieb , Matthias Hase , Werner Krebs , Berthold Kostlin , Stefan Reich , Marc Tertilt , Jan Wilkes
Abstract: A jet burner has a hot-gas side, which faces toward a combustion chamber during operation, and a cold-gas side, which faces away from a combustion chamber, including a base plate on which there are arranged multiple jet nozzles, wherein the base plate has at least one cooling duct, wherein the at least one cooling duct issues into a burner stage which comprises a pilot burner arranged on the base plate.
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