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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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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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Patent Agency Ranking
公开(公告)号：US20150007573A1
公开(公告)日：2015-01-08
申请号：US14382918
申请日：2013-03-15
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Francois Benkler , Thomas Brandenburg , Olga Deiss , Thomas Grieb , Marco Link , Nicolas Savilius , Daniel Vogtmann , Jan Wilkes
Abstract: An annular combustion chamber (1) for a gas turbine, the chamber having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air is guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Ring segments around the outer shell have projections selectively movable to at least partially block and open the ducts. A gas turbine is also disclosed.
Abstract translation: 一种用于燃气轮机的环形燃烧室（1），所述腔室具有外壳（12），所述外壳具有用于燃烧器（3）的至少一个入口（4）和通向涡轮室（7）的出口（7） 8），其中可以关闭的导管（14）基本上平行于环形燃烧室（1）的对称轴线（2）定向，并且最终的压缩机空气通过该导管引导到环形燃烧室（1）中， 在出口（7）的区域中设置在外壳（12）中。 围绕外壳的环形段具有选择性地可移动以至少部分地阻挡和打开导管的突起。 还公开了一种燃气轮机。
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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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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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6.发明申请HEAT-SHIELD ELEMENT FOR A COMPRESSOR-AIR BYPASS AROUND THE COMBUSTION CHAMBER 审中-公开用于燃烧室周围的压缩空气旁路的加热元件公开(公告)号：US20150027128A1
公开(公告)日：2015-01-29
申请号：US14384257
申请日：2013-03-12
Applicant: SIEMENS AKTIENGESELLSCHAFT
Inventor： Francois Benkler , Thomas Brandenburg , Olga Deiss , Thomas Grieb , Marco Link , Nicolas Savilius , Daniel Vogtmann , Jan Wilkes
Abstract: A heat-shield element (14), for lining a combustion-chamber wall (13), the chamber wall has a first wall (17) with a hot side (18) which can be loaded with a hot medium, a cold side (19) which lies opposite the hot side (18), and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) of the first wall (17) to a first height (25) beyond the cold side (19), the circumferential edge (24) extends on a fourth narrow side (23) to a second shorter height (26), substantially at the second height (26), a second wall (27) lies opposite the cold side (19) and extends over the width of the fourth narrow side (23) from the fourth narrow side (23) and over a part of the length of the narrow sides (20, 22), which adjoin the fourth narrow side; (23), the second wall (27) has an edge (29) at the end (28) thereof which faces away from the fourth narrow side (23), which edge (29) extends to the first height (25). Furthermore, a combustion chamber and a gas turbine are disclosed.
Abstract translation: 一种用于衬里燃烧室壁（13）的隔热元件（14），所述室壁具有第一壁（17），所述第一壁具有热侧（18），所述第一壁可以装载有热介质，冷侧 19），以及在第一壁（17）的第一（20），第二（21）和第三窄边（22）上延伸到第一壁（17）的周向边缘（24） 第一高度（25）超过冷侧（19），圆周边缘（24）在第四窄边（23）延伸到第二较短高度（26），基本上在第二高度（26），第二壁 27）与冷侧（19）相对并且从第四窄边（23）延伸到第四窄边（23）的宽度上并且在窄边（20,22）的一部分长度上延伸，其邻接 第四窄边 （23）中，第二壁（27）在其端部（28）处具有远离第四窄边（23）的边缘（29），该边缘（29）延伸到第一高度（25）。 此外，公开了燃烧室和燃气轮机。
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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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