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1. 发明授权

US08007273B2 Premixing burner for generating an ignitable fuel/air mixture 有权
标题翻译：用于产生可燃燃料/空气混合物的预混燃烧器
公开(公告)号：US08007273B2
公开(公告)日：2011-08-30
申请号：US11838999
申请日：2007-08-15
申请人： Thomas Ruck , Slawomir Slowik , Christian Steinbach , Martin Andrea Von Planta
发明人： Thomas Ruck , Slawomir Slowik , Christian Steinbach , Martin Andrea Von Planta
IPC分类号： F23M3/00
CPC分类号： F23C7/002 , F23C2900/07002 , F23D17/002 , F23D2211/00 , F23R3/286
摘要： A premixing burner has a swirl generator with at least two burner shells (1) which jointly enclose an axia conically widening swirl space and delimit tangential air inlet slits (3) through which combustion supply air passes into the swirl space in which an axially propagating swirl flow is formed, and with fuel injection devices at least partially along the tangentially running air inlet slits (3). The fuel injection devices include a fuel line (6) separate from the burner shell (1) and which is firmly attached to the burner shell (1) so as to be longitudinally movable with respect to the burner shell (1) and releasable perpendicularly to the surface of the burner shell (1). In the burner shell (1), orifices (4) are provided, into which issue fuel injectors (7) which are provided along the fuel line (6) and which project beyond the circumferential edge of the fuel line (6).
摘要翻译：预混燃烧器具有涡流发生器，其具有至少两个燃烧器壳体（1），该燃烧器壳体联合地包围轴向锥形加宽的涡流空间并限定切向空气入口狭缝（3），燃烧供给空气通过该空气入口狭缝（3）进入涡流空间，流动形成，并且燃料喷射装置至少部分地沿着切向运行的空气入口狭缝（3）。燃料喷射装置包括与燃烧器壳体（1）分离并且牢固地附接到燃烧器壳体（1）的燃料管线（6），以便能够相对于燃烧器壳体（1）纵向移动并且可以垂直于燃烧器壳体（1）的表面。在燃烧器壳体（1）中，设有孔口（4），其中沿燃料管线（6）设置并且突出超过燃料管线（6）的周边边缘的燃料喷射器（7）。

2. 发明申请

US20080032246A1 Premixing Burner for Generating an Ignitable Fuel/Air Mixture 有权
标题翻译：预混燃烧器产生可燃燃料/空气混合物
公开(公告)号：US20080032246A1
公开(公告)日：2008-02-07
申请号：US11838999
申请日：2007-08-15
申请人： Thomas Ruck , Slawomir Slowik , Christian Steinbach , Martin Von Planta
发明人： Thomas Ruck , Slawomir Slowik , Christian Steinbach , Martin Von Planta
IPC分类号： B01F5/04 , F23C7/00
CPC分类号： F23C7/002 , F23C2900/07002 , F23D17/002 , F23D2211/00 , F23R3/286
摘要： A premixing burner for generating an ignitable fuel/air mixture has a swirl generator with at least two burner shells (1) which complement one another to form a throughflow body and which jointly enclose an axial conically widening swirl space and delimit, with respect to one another in the axial longitudinal extent of the cone, tangential air inlet slits (3) through which combustion supply air passes into the swirl space in which an axially propagating swirl flow is formed, and with fuel injection devices, which are provided at least partially along the tangentially running air inlet slits (3). The fuel injection devices are designed as a fuel line (6) which is separate from the burner shell (1) and which is firmly attached to the burner shell (1) so as to be longitudinally movable with respect to the burner shell (1) and so as to be releasable perpendicularly to the surface of the burner shell (1), and in that, in the burner shell (1), orifices (4) are provided, into which issue fuel injectors (7) which are provided along the fuel line (6) and which project beyond the circumferential edge of the fuel line (6).
摘要翻译：用于产生可燃燃料/空气混合物的预混合燃烧器具有涡流发生器，其具有至少两个燃烧器壳体（1），所述燃烧器壳体彼此互补以形成通流体，并且联合地包围轴向锥形加宽的涡流空间并相对于一个另一个在锥体的轴向纵向范围内，切向空气入口狭缝（3），燃烧供给空气通过其进入涡旋空间中，其中形成轴向传播的涡流，以及燃料喷射装置，其至少部分地沿着切向运行的空气入口狭缝（3）。燃料喷射装置被设计为与燃烧器壳体（1）分离并且牢固地附接到燃烧器壳体（1）以相对于燃烧器壳体（1）可纵向移动的燃料管线（6）并且能够垂直于燃烧器壳体（1）的表面释放，并且在燃烧器壳体（1）中设置有孔口（4），其中设置有沿着燃烧器壳体（1）设置的燃料喷射器燃料管线（6），并且突出超出燃料管线（6）的周向边缘。

3. 发明申请

US20050042092A1 Method of reconditioning a turbine blade 有权
标题翻译：涡轮叶片修复方法
公开(公告)号：US20050042092A1
公开(公告)日：2005-02-24
申请号：US10892136
申请日：2004-07-16
申请人： Andreas Boegli , James Ritchie , Slawomir Slowik , Heinrich Stuessi
发明人： Andreas Boegli , James Ritchie , Slawomir Slowik , Heinrich Stuessi
IPC分类号： F01D5/00 , F01D5/22 , B63H1/00
CPC分类号： B23P6/002 , F01D5/005 , F01D5/225 , F05D2230/10 , F05D2230/23 , F05D2230/30 , F05D2230/80 , F05D2230/90 , F05D2300/611 , Y10T29/49318 , Y10T29/49718 , Y10T29/49719 , Y10T29/49732 , Y10T29/49742 , Y10T29/49746
摘要： A method of reconditioning a rotating blade (1) with a shroud (8) following the operation in a gas turbine, includes the application of a barrier (14) placed on the edge of the shroud (8) facing the edge of a shroud (8) of an adjacent blade having creep deformation. The barrier (14) prevents hot gas ingestion into a shroud cavity (10). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud (8) is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating (15) is additionally applied to the surfaces of the shroud (8) that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade (1).
摘要翻译：在燃气轮机中的操作之后，用护罩（8）重新调节旋转叶片（1）的方法包括施加位于护罩（8）的面向护罩边缘的边缘（14）上的屏障（14） 8）具有蠕变变形的相邻叶片。阻挡层（14）防止热气体吸入护罩腔（10）。它是通过焊接或激光熔覆或其他方法逐层预制或组装的。此外，为了重新建立护罩的初始质量，护罩（8）的质量被减小。隔热涂层（15）另外施加到暴露于涡轮机的热气体的护罩（8）的表面。该方法显着增加了叶片（1）的寿命。

4. 发明授权

US07326033B2 Turbomachine blade 有权
标题翻译：涡轮机刀片
公开(公告)号：US07326033B2
公开(公告)日：2008-02-05
申请号：US11600754
申请日：2006-11-17
申请人： Andreas Boegli , Alexander Mahler , James Ritchie , Slawomir Slowik
发明人： Andreas Boegli , Alexander Mahler , James Ritchie , Slawomir Slowik
IPC分类号： F01D11/02
CPC分类号： F01D5/225 , F05D2230/10 , F05D2240/11
摘要： A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.
摘要翻译：公开了一种涡轮机叶片，其具有护罩元件，其中在离心载荷下操作期间导致护罩元件在一侧上的塑性变形和提升。该负载可能导致叶片的高温蠕变。布置在护罩元件上的密封条可以被构造成在圆周方向上变化的厚度。护罩元件的质量以及因此不对称的离心载荷和护罩元件在其一侧产生的护罩元件的提升可以通过在圆周方向上位于外侧的区域处的材料去除而减少。

5. 发明申请

US20070104570A1 Turbomachine blade 有权
标题翻译：涡轮机刀片
公开(公告)号：US20070104570A1
公开(公告)日：2007-05-10
申请号：US11600754
申请日：2006-11-17
申请人： Andreas Boegli , Alexander Mahler , James Ritche , Slawomir Slowik
发明人： Andreas Boegli , Alexander Mahler , James Ritche , Slawomir Slowik
IPC分类号： F01D11/08
CPC分类号： F01D5/225 , F05D2230/10 , F05D2240/11
摘要： A turbomachine blade is disclosed having a shroud element, wherein plastic deformations and lifting of the shroud element on one side result during operation under centrifugal load. This load may result in high-temperature creep of the blade. A sealing strip which is arranged on the shroud element can be configured with a thickness varying in a circumferential direction. The mass of the shroud element and thus the asymmetrical centrifugal load and the lifting of the shroud element on one side resulting therefrom can be reduced by material removal at regions lying on the outside in the circumferential direction.
摘要翻译：公开了一种涡轮机叶片，其具有护罩元件，其中在离心载荷下操作期间导致护罩元件在一侧上的塑性变形和提升。该负载可能导致叶片的高温蠕变。布置在护罩元件上的密封条可以被构造成在圆周方向上变化的厚度。护罩元件的质量以及因此不对称的离心载荷和护罩元件在其一侧产生的护罩元件的提升可以通过在圆周方向上位于外侧的区域处的材料去除而减少。

6. 发明授权

US07231713B2 Method of reconditioning a turbine blade 有权
标题翻译：涡轮叶片修复方法
公开(公告)号：US07231713B2
公开(公告)日：2007-06-19
申请号：US10892136
申请日：2004-07-16
申请人： Andreas Boegli , James George Ritchie , Slawomir Slowik , Heinrich Stuessi
发明人： Andreas Boegli , James George Ritchie , Slawomir Slowik , Heinrich Stuessi
IPC分类号： B23P6/00 , B23K9/04
CPC分类号： B23P6/002 , F01D5/005 , F01D5/225 , F05D2230/10 , F05D2230/23 , F05D2230/30 , F05D2230/80 , F05D2230/90 , F05D2300/611 , Y10T29/49318 , Y10T29/49718 , Y10T29/49719 , Y10T29/49732 , Y10T29/49742 , Y10T29/49746
摘要： A method of reconditioning a rotating blade (1) with a shroud (8) following the operation in a gas turbine, includes the application of a barrier (14) placed on the edge of the shroud (8) facing the edge of a shroud (8) of an adjacent blade having creep deformation. The barrier (14) prevents hot gas ingestion into a shroud cavity (10). It is pre-fabricated or built-up layer-by-layer by welding or laser cladding or other methods. Additionally, the mass of the shroud (8) is reduced in order to re-establish the initial mass of the shroud. A thermal barrier coating (15) is additionally applied to the surfaces of the shroud (8) that are exposed to the hot gas of the turbine. The method significantly increases the lifetime of the blade (1).
摘要翻译：在燃气轮机中的操作之后，用护罩（8）重新调节旋转叶片（1）的方法包括施加位于护罩（8）的面向护罩边缘的边缘（14）上的屏障（14） 8）具有蠕变变形的相邻叶片。阻挡层（14）防止热气体吸入护罩腔（10）。它是通过焊接或激光熔覆或其他方法逐层预制或组装的。此外，为了重新建立护罩的初始质量，护罩（8）的质量被减小。隔热涂层（15）另外施加到暴露于涡轮机的热气体的护罩（8）的表面。该方法显着增加了叶片（1）的寿命。

7. 发明申请

US20080298970A1 Turbo Machine 审中-公开
标题翻译：涡轮机
公开(公告)号：US20080298970A1
公开(公告)日：2008-12-04
申请号：US12045895
申请日：2008-03-11
申请人： Joergen Ferber , James Ritchie , Slawomir Slowik
发明人： Joergen Ferber , James Ritchie , Slawomir Slowik
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F05B2240/33 , F05D2230/60 , F05D2260/30 , Y02T50/671 , Y02T50/673
摘要： A turbo machine (1, 101), in particular turbine or compressor, includes a rotor (2, 102) which has at least one moving blade row (4, 104) with a plurality of moving blades (5, 105), and a stator (3) which has at least one guide vane row (6, 106) with a plurality of guide vanes (7, 107), at least one moving blade row (4, 104) having a shroud (8, 108). The shroud (8, 108) is designed to be self-supporting in such a way that it can at least partially absorb the centrifugal forces arising during operation and discharge them in the circumferential direction.
摘要翻译：特别是涡轮机或压缩机的涡轮机（1,101）包括具有至少一个具有多个活动叶片（5,105）的活动叶片排（4,104）的转子（2,102），以及定子（3）具有至少一个具有多个导向叶片（7,107）的导向叶片排（6,106），至少一个具有护罩（8,108）的活动叶片排（4,104）。护罩（8,108）被设计成自支撑，使得其可以至少部分地吸收在操作过程中产生的离心力并在圆周方向上排出它们。

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