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1. 发明申请

US20100247309A1 LAMELLAR SEAL FOR A TURBOMACHINE 有权
标题翻译： LAMELLAR密封用于涡轮发动机
公开(公告)号：US20100247309A1
公开(公告)日：2010-09-30
申请号：US12732359
申请日：2010-03-26
申请人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
发明人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
IPC分类号： F01D25/00 , F16J15/16
CPC分类号： F01D11/001 , F05D2240/57 , F16J15/3292
摘要： A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
摘要翻译：用于密封围绕轴线旋转的轴的层状密封件，特别是在燃气轮机中，包括多个薄片（13），所述多个薄片（13）彼此间隔开，并以轴为中心圆周排列并固定在其位置，其中通过其表面的薄片（13）基本上平行于轴线定向。通过薄片（13）在每种情况下具有形成结构（19,20,21）以便将薄片（13）定位和保持在层状密封件（12）中的事实来改善层状密封，其包括一个或多个更侧向突出的支撑臂（19,20,21），其接合端板（15,16）的互补形成的凹部（25,26）。

2. 发明申请

US20110099809A1 METHODS FOR REPAIRING A GAS TURBINE COMPONENT 有权
标题翻译：修理气体涡轮组件的方法
公开(公告)号：US20110099809A1
公开(公告)日：2011-05-05
申请号：US12915951
申请日：2010-10-29
申请人： Simone Hövel , Günter Ambrosy , Matthias Höbel
发明人： Simone Hövel , Günter Ambrosy , Matthias Höbel
IPC分类号： B23P17/00
CPC分类号： F01D5/005 , B23P6/005 , F05D2230/80 , Y10T29/49229 , Y10T29/49318 , Y10T29/49336 , Y10T29/49732 , Y10T29/49734 , Y10T29/49771
摘要： A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10). A higher degree of precision and automation can be achieved, because the worn out location is measured/scanned with a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data; the nominal geometry for the insert is defined by the actual geometry of the worn out location, with respect to certain defined gap tolerances; the actual geometry of the insert is measured during the manufacture of the insert; the nominal geometry and the actual geometry of the insert are compared; and an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.
摘要翻译：一种用于修理燃气涡轮机部件的方法包括：在所述燃气涡轮机部件（10）上识别所述燃气涡轮机部件（10）损坏的磨损位置; 去除损坏的位置，从而形成缺失区域（18）; 制造适合于缺失区（18）的插入件; 将插入物放入缺失区域（18）中; 调整所述燃气轮机部件（10）中的所述插入件; 并将调整好的插入件接合到燃气轮机部件（10）上。可以实现更高的精度和自动化程度，因为用3维扫描/测量系统（20）测量/扫描磨损的位置以获得缺失区域（18）的实际几何形状，特别是作为CAD数据 ; 相对于某些限定的间隙公差，插入件的标称几何形状由磨损位置的实际几何形状定义; 在插入件的制造期间测量插入件的实际几何形状; 比较插入物的名义几何和实际几何形状; 并且基于插入件的实际和标称几何形状的比较的结果来执行插入件的自适应加工操作。

3. 发明授权

US06318891B1 Method of temperature measurement by correlation of chemiluminescent spectrum emitted by a flame with stored theoretical emission spectra for OH and/or CH radicals 有权
标题翻译：通过火焰发射的化学发光谱与OH和/或CH自由基的储存理论发射光谱的相关性进行温度测量的方法
公开(公告)号：US06318891B1
公开(公告)日：2001-11-20
申请号：US09230847
申请日：1999-02-02
申请人： Ken-Yves Haffner , Matthias Höbel
发明人： Ken-Yves Haffner , Matthias Höbel
IPC分类号： G01J3457
CPC分类号： G01J5/0014
摘要： In a temperature measurement method for determining the adiabatic temperature of a flame, in particular in the combustion chamber of a gas turbine, the chemiluminescence radiation from the flame, emitted by OH radicals and CH radicals, is detected using a spectrograph via an optical sensor fiber. The spectrally resolved raw signal of the chemiluminescence radiation is then corrected and compared with a multiplicity of theoretically determined emission spectra, until a theoretical emission spectrum coincides with the chemiluminescence spectrum. The Boltzmann temperature associated with this coinciding emission spectrum is then assigned to the chemiluminescence spectrum, the adiabatic flame temperature being derived from the Boltzmann temperature by correlation.
摘要翻译：在用于确定火焰的绝热温度的温度测量方法中，特别是在燃气轮机的燃烧室中，使用光谱仪通过光学传感器光纤检测来自火焰的OH自由基和CH自由基发射的化学发光辐射。然后对化学发光辐射的光谱解析的原始信号进行校正，并与多个理论确定的发射光谱进行比较，直到理论发射光谱与化学发光光谱一致。然后将与此一致的发射光谱相关联的玻尔兹曼温度分配给化学发光光谱，绝热火焰温度通过相关从玻尔兹曼温度得到。

4. 发明授权

US08978249B2 Methods for repairing a gas turbine component 有权
标题翻译：修理燃气轮机部件的方法
公开(公告)号：US08978249B2
公开(公告)日：2015-03-17
申请号：US12915951
申请日：2010-10-29
申请人： Simone Hövel , Günter Ambrosy , Matthias Höbel
发明人： Simone Hövel , Günter Ambrosy , Matthias Höbel
IPC分类号： B23P6/00 , F01D5/00
CPC分类号： F01D5/005 , B23P6/005 , F05D2230/80 , Y10T29/49229 , Y10T29/49318 , Y10T29/49336 , Y10T29/49732 , Y10T29/49734 , Y10T29/49771
摘要： A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10). A higher degree of precision and automation can be achieved, because the worn out location is measured/scanned with a 3-D scanning/measuring system (20) to get the actual geometry of the missing zone (18), especially as a CAD data; the nominal geometry for the insert is defined by the actual geometry of the worn out location, with respect to certain defined gap tolerances; the actual geometry of the insert is measured during the manufacture of the insert; the nominal geometry and the actual geometry of the insert are compared; and an adaptive machining operation of the insert is carried out based on the results from the comparison between the actual and nominal geometries of the insert.
摘要翻译：一种用于修理燃气涡轮机部件的方法包括：在所述燃气涡轮机部件（10）上识别所述燃气涡轮机部件（10）损坏的磨损位置; 去除损坏的位置，从而形成缺失区域（18）; 制造适合于缺失区（18）的插入件; 将插入物放入缺失区域（18）中; 调整所述燃气轮机部件（10）中的所述插入件; 并将调整好的插入件接合到燃气轮机部件（10）上。可以实现更高的精度和自动化程度，因为用3维扫描/测量系统（20）测量/扫描磨损的位置以获得缺失区域（18）的实际几何形状，特别是作为CAD数据 ; 相对于某些限定的间隙公差，插入件的标称几何形状由磨损位置的实际几何形状定义; 在插入件的制造期间测量插入件的实际几何形状; 比较插入物的名义几何和实际几何形状; 并且基于插入件的实际和标称几何形状的比较的结果来执行插入件的自适应加工操作。

5. 发明授权

US08517673B2 Lamellar seal for a turbomachine 有权
标题翻译：用于涡轮机的层状密封
公开(公告)号：US08517673B2
公开(公告)日：2013-08-27
申请号：US12732359
申请日：2010-03-26
申请人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
发明人： Günter Ambrosy , Matthias Höbel , Ernst Vogt , Josef Hafner
IPC分类号： F01D25/00
CPC分类号： F01D11/001 , F05D2240/57 , F16J15/3292
摘要： A lamellar seal for sealing a shaft which rotates around an axis, especially in a gas turbine, includes a multiplicity of lamella (13) which are spaced one beneath the other, arranged in a concentric circle around the axis, and fixed in their position, wherein the lamellae (13) by their surfaces are oriented essentially parallel to the axis. The lamellar seal is improved by the fact that the lamellae (13) have formed-on structures (19, 20, 21) in each case for positioning and retaining the lamellae (13) in the lamellar seal (12), which include one or more laterally projecting support arms (19, 20, 21) which engage in complementarily formed recesses (25, 26) of the end plates (15, 16).
摘要翻译：用于密封围绕轴线旋转的轴的层状密封件，特别是在燃气轮机中，包括多个薄片（13），所述多个薄片（13）彼此间隔开，并以轴为中心圆周排列并固定在其位置，其中通过其表面的薄片（13）基本上平行于轴线定向。通过薄片（13）在每种情况下具有形成结构（19,20,21）以便将薄片（13）定位和保持在层状密封件（12）中的事实来改善层状密封，其包括一个或多个更侧向突出的支撑臂（19,20,21），其接合端板（15,16）的互补形成的凹部（25,26）。

6. 发明申请

US20110099810A1 METHOD FOR REPAIRING A GAS TURBINE COMPONENT 审中-公开
标题翻译：修复气体涡轮组件的方法
公开(公告)号：US20110099810A1
公开(公告)日：2011-05-05
申请号：US12916032
申请日：2010-10-29
申请人： Alexander STANKOWSKI , Simone HÖVEL , Lukas RICKENBACHER , Matthias HÖBEL , Günter AMBROSY
发明人： Alexander STANKOWSKI , Simone HÖVEL , Lukas RICKENBACHER , Matthias HÖBEL , Günter AMBROSY
IPC分类号： B23P17/00
CPC分类号： F01D5/005 , B22F7/062 , B22F2999/00 , B23K2101/001 , B23P6/005 , F05D2230/13 , F05D2230/80 , F05D2250/20 , Y02P10/295 , Y10T29/49229 , B22F3/1055
摘要： A method for repairing an ex-service gas turbine component (10) includes the steps of: removing a damaged section (13) from the gas turbine component (10), manufacturing a 3-D article, which fits in the gas turbine component (10) to replace the removed damaged section (13), and joining the gas turbine component (10) and the 3-D article inserted therein. Reduced cost, improved flexibility and productivity, and simplified handling are achieved by removing the damaged section (13) in the form of a cut-out section along a split line (14) as one single cut-out piece (15), measuring the cut-out piece (15) to obtain the actual non-parametric geometry data set of the cut-out piece (15), and manufacturing the 3-D article based on the geometry data set of the cut-out piece (15).
摘要翻译：一种维修燃气轮机组件（10）的方法，包括以下步骤：从燃气轮机部件（10）中取出损坏的部分（13），制造适合燃气轮机部件（3）的3-D制品 10），以更换已拆除的损坏部分（13），并且连接燃气轮机部件（10）和插入其中的3-D制品。通过沿着分割线（14）将作为切割部分的形式的损坏部分（13）作为单个切割件（15）移除，测量成本，改进的柔性和生产率以及简化的处理切割件（15），以获得切割件（15）的实际非参数几何数据集，并且基于切割件（15）的几何数据集来制造3-D制品。

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