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1. 发明授权

US08211524B1 CMC anchor for attaching a ceramic thermal barrier to metal 失效
标题翻译： CMC锚固件用于将陶瓷热障贴附于金属
公开(公告)号：US08211524B1
公开(公告)日：2012-07-03
申请号：US12108708
申请日：2008-04-24
申请人： Malberto Gonzalez , Douglas A. Keller , Bonnie D. Marini , Jay A. Morrison
发明人： Malberto Gonzalez , Douglas A. Keller , Bonnie D. Marini , Jay A. Morrison
IPC分类号： B32B3/12
CPC分类号： C04B35/80 , B28B23/0018 , B33Y80/00 , C04B2235/616 , C22C1/1015 , C22C1/1036 , C22C29/00 , F01D5/288 , F05D2250/283 , F05D2300/6033 , F23M2900/05004 , F23R3/007 , Y10T428/24149 , Y10T428/24157 , Y10T428/24165 , Y10T428/24174 , Y10T428/24289 , Y10T428/24322 , Y10T428/24331 , Y10T428/24496 , Y10T428/24529 , Y10T428/24587 , Y10T428/24744 , Y10T428/249953 , Y10T428/31678
摘要： A ceramic matrix composite (CMC) anchor (20, 100) joining a metal substrate (40) and a ceramic thermal barrier (38). The CMC anchor extends into and interlocks with the ceramic barrier, and extends into and interlocks with the metal substrate. The CMC anchor may be a honeycomb (20) or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first (22) and second (24) arrays of cells (26) with open distal ends (28) on respective opposite sides of a sheet (30). The cells may have walls (32) with transverse passages (36). A metal (40) may be deposited into the cells and passages on one side of the sheet, forming a metal substrate locked into the honeycomb. A ceramic insulation material (38) may be deposited into the cells and passages on the opposite side of the sheet, forming a layer of ceramic insulation locked into the honeycomb.
摘要翻译：连接金属基板（40）和陶瓷热障（38）的陶瓷基体复合（CMC）锚（20,100）。 CMC锚固体延伸到陶瓷阻挡层并与其互锁，并延伸到金属基底并与其互锁。 CMC锚可以是蜂窝（20）或其它延伸到互锁的几何形状。可以在片材（30）的相对的相对侧上形成有具有开放的远端（28）的第一（22）和第二（24）电池阵列（26）的CMC蜂窝体。细胞可以具有带有横向通道（36）的壁（32）。金属（40）可以沉积在片材一侧的电池和通道中，形成锁定在蜂窝中的金属基底。可以将陶瓷绝缘材料（38）沉积到片材的相对侧上的电池和通道中，形成锁定在蜂巢中的陶瓷绝缘层。

2. 发明申请

US20120148794A1 CMC ANCHOR FOR ATTACHING A CERAMIC THERMAL BARRIER TO METAL 失效
标题翻译：用于将陶瓷热障连接到金属的CMC锚杆
公开(公告)号：US20120148794A1
公开(公告)日：2012-06-14
申请号：US12108708
申请日：2008-04-24
申请人： Douglas A. Keller , Jay A. Morrison , Malberto Gonzalez , Bonnie D. Marini
发明人： Douglas A. Keller , Jay A. Morrison , Malberto Gonzalez , Bonnie D. Marini
IPC分类号： B32B3/12 , B32B18/00 , B32B7/04 , B32B15/04 , B32B3/30 , B32B3/26
CPC分类号： C04B35/80 , B28B23/0018 , B33Y80/00 , C04B2235/616 , C22C1/1015 , C22C1/1036 , C22C29/00 , F01D5/288 , F05D2250/283 , F05D2300/6033 , F23M2900/05004 , F23R3/007 , Y10T428/24149 , Y10T428/24157 , Y10T428/24165 , Y10T428/24174 , Y10T428/24289 , Y10T428/24322 , Y10T428/24331 , Y10T428/24496 , Y10T428/24529 , Y10T428/24587 , Y10T428/24744 , Y10T428/249953 , Y10T428/31678
摘要： A ceramic matrix composite (CMC) anchor (20, 100) joining a metal substrate (40) and a ceramic thermal barrier (38). The CMC anchor extends into and interlocks with the ceramic barrier, and extends into and interlocks with the metal substrate. The CMC anchor may be a honeycomb (20) or other extending-into-and-interlocking geometry. A CMC honeycomb may be formed with first (22) and second (24) arrays of cells (26) with open distal ends (28) on respective opposite sides of a sheet (30). The cells may have walls (32) with transverse passages (36). A metal (40) may be deposited into the cells and passages on one side of the sheet, forming a metal substrate locked into the honeycomb. A ceramic insulation material (38) may be deposited into the cells and passages on the opposite side of the sheet, forming a layer of ceramic insulation locked into the honeycomb.
摘要翻译：连接金属基板（40）和陶瓷热障（38）的陶瓷基体复合（CMC）锚（20,100）。 CMC锚固体延伸到陶瓷阻挡层并与其互锁，并延伸到金属基底并与其互锁。 CMC锚可以是蜂窝（20）或其它延伸到互锁的几何形状。可以在片材（30）的相对的相对侧上形成有具有开放的远端（28）的第一（22）和第二（24）电池阵列（26）的CMC蜂窝体。细胞可以具有带有横向通道（36）的壁（32）。金属（40）可以沉积在片材一侧的电池和通道中，形成锁定在蜂窝中的金属基底。可以将陶瓷绝缘材料（38）沉积到片材的相对侧上的电池和通道中，形成锁定在蜂巢中的陶瓷绝缘层。

3. 发明授权

US07871244B2 Ring seal for a turbine engine 有权
标题翻译：涡轮发动机的环形密封
公开(公告)号：US07871244B2
公开(公告)日：2011-01-18
申请号：US11707193
申请日：2007-02-15
申请人： Bonnie D. Marini , Douglas A. Keller
发明人： Bonnie D. Marini , Douglas A. Keller
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2240/127 , F05D2250/70 , F05D2250/71 , F05D2250/711 , F05D2260/30 , F05D2300/21
摘要： A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.
摘要翻译：涡轮发动机环密封件，用于密封涡轮发动机外密封段和涡轮叶片尖端之间的间隙。涡轮发动机环段可以具有限定间隙气体流动路径的一部分的内部径向表面，其中内部径向表面可以由可磨损陶瓷涂层形成，并且包括多个气体流动突起，其横向于间隙气体流路。气流突起可以在间隙气体流动路径中的气流中引起涡流。此外，气流突起可以是两个相邻峰之间的一系列峰和凹陷，其中凹陷具有近似的半圆形。两个相邻峰之间的距离可以等于或大于凹陷的宽度，单个峰的高度可以是两个相邻峰之间的距离的6％或更大。

4. 发明申请

US20080273967A1 Ring seal for a turbine engine 有权
标题翻译：涡轮发动机的环形密封
公开(公告)号：US20080273967A1
公开(公告)日：2008-11-06
申请号：US11707193
申请日：2007-02-15
申请人： Bonnie D. Marini , Douglas A. Keller
发明人： Bonnie D. Marini , Douglas A. Keller
IPC分类号： F01D11/12
CPC分类号： F01D11/122 , F05D2230/31 , F05D2230/90 , F05D2240/11 , F05D2240/127 , F05D2250/70 , F05D2250/71 , F05D2250/711 , F05D2260/30 , F05D2300/21
摘要： A turbine engine ring seal for sealing gaps between turbine engine outer seal segments and turbine blade tips. The turbine engine ring segment may have an inner radial surface that defines a portion of a gap gas flow path where the inner radial surface may be formed of an abradable ceramic coating and includes a plurality of gas flow protrusions that are oriented transverse to the gap gas flow path. The gas flow protrusions may induce vortices in the gas flow in the gap gas flow path. Additionally, the gas flow protrusions may be series of peaks and depressions between two adjacent peaks, where the depressions have an approximate semicircular shape. The distance between two adjacent peaks may be equal or greater than a width of the depression and the height of a single peak may be six percent or greater than the distance between two adjacent peaks.
摘要翻译：涡轮发动机环密封件，用于密封涡轮发动机外密封段和涡轮叶片尖端之间的间隙。涡轮发动机环段可以具有限定间隙气体流动路径的一部分的内部径向表面，其中内部径向表面可以由可磨损陶瓷涂层形成，并且包括多个气体流动突起，其横向于间隙气体流路。气流突起可以在间隙气体流动路径中的气流中引起涡流。此外，气流突起可以是两个相邻峰之间的一系列峰和凹陷，其中凹陷具有近似的半圆形。两个相邻峰之间的距离可以等于或大于凹陷的宽度，单个峰的高度可以是两个相邻峰之间的距离的6％或更大。

5. 发明申请

US20080025838A1 Ring seal for a turbine engine 审中-公开
标题翻译：涡轮发动机的环形密封
公开(公告)号：US20080025838A1
公开(公告)日：2008-01-31
申请号：US11492589
申请日：2006-07-25
申请人： Bonnie D. Marini , Douglas A. Keller , David C. Radonovich , Gary B. Merrill , Steven J. Vance , Anthony L. Schiavo
发明人： Bonnie D. Marini , Douglas A. Keller , David C. Radonovich , Gary B. Merrill , Steven J. Vance , Anthony L. Schiavo
IPC分类号： F01D5/20
CPC分类号： F01D25/246 , F05D2300/21 , F05D2300/6033
摘要： Aspects of the invention are directed to a ceramic matrix composite ring seal segment. The ring seal segment according to aspects of the invention includes a relatively simple body that is circumferentially curved. At least a portion of the hot gas path surface of the ring seal segment can be coated with a thermal insulating. material. In one embodiment, each ring seal segment can be operatively connected to a stationary support structure, such as by way of isolation rings. The ring seal segments and/or the isolation rings can be configured so as to restrain the ring seal segments in the axial, radial and/or circumferential directions. The ring seal segments can be attached to the isolation rings so that the support points act opposite the operating pressure loads. Thus, the ring seal segments carry these loads in compression, a strong direction of the CMC fibers.
摘要翻译：本发明的方面涉及一种陶瓷基复合环密封段。根据本发明的方面的环形密封段包括周向弯曲的相对简单的主体。环形密封段的热气体路径表面的至少一部分可以被涂覆绝热。材料。在一个实施例中，每个环形密封段可以可操作地连接到固定的支撑结构，例如通过隔离环。环形密封段和/或隔离环可以构造成在轴向，径向和/或圆周方向上限制环形密封段。环形密封段可以连接到隔离环，使得支撑点与操作压力负载相反。因此，环形密封段承受这些负载在CMC纤维的强力方向的压缩。

6. 发明授权

US07604456B2 Vane shroud through-flow platform cover 失效
标题翻译：叶片护罩通流平台盖
公开(公告)号：US07604456B2
公开(公告)日：2009-10-20
申请号：US11401987
申请日：2006-04-11
申请人： Anthony L. Schiavo, Jr. , Bonnie D. Marini
发明人： Anthony L. Schiavo, Jr. , Bonnie D. Marini
IPC分类号： F04D29/40 , F03B11/02
CPC分类号： F01D5/225 , F01D11/008 , F05D2240/80
摘要： A turbine vane array (10) for a combustion assembly (8) in a combustion turbine engine. The vane array (10) includes a plurality of stationary vane assemblies (12), each vane assembly (12) including at least one airfoil (24) and inner and outer shroud segments (26, 28) attached to opposing ends of the airfoil (24). The inner and outer shroud segments (26, 28) each include an inner face (34, 36) facing toward a gas path (13) extending through the vane array (10). A removable cover structure may be provided on the inner faces (34, 36) of the inner and outer shroud segments (26, 28). The cover structure may include removably attached insert elements (72, 72′) that are positioned on the inner faces (34, 36) extending between upstream edges (44) and downstream edges (46) of the shroud segments (26, 28) and extending between adjacent airfoils (24).
摘要翻译：一种用于燃气涡轮发动机中的燃烧组件（8）的涡轮叶片阵列（10）。叶片阵列（10）包括多个静止叶片组件（12），每个叶片组件（12）包括至少一个翼型件（24），以及附接到翼型件的相对端部的内部和外侧护罩段（26,28） 24）。内部和外部护罩段（26,28）各自包括面向延伸穿过叶片阵列（10）的气体路径（13）的内表面（34,36）。可拆卸的盖结构可以设置在内和外护罩段（26,28）的内表面（34,36）上。盖结构可以包括可移除地附接的插入元件（72,72'），其位于在护罩段（26,28）的上游边缘（44）和下游边缘（46）之间延伸的内表面（34,36）上，以及在相邻的翼型件（24）之间延伸。

7. 发明申请

US20080025842A1 Turbine vane with removable platform inserts 失效
标题翻译：涡轮叶片带有可移动平台插入件
公开(公告)号：US20080025842A1
公开(公告)日：2008-01-31
申请号：US11494177
申请日：2006-07-27
申请人： Bonnie D. Marini , Anthony L. Schiavo
发明人： Bonnie D. Marini , Anthony L. Schiavo
IPC分类号： F01D11/00
CPC分类号： F01D5/147 , F01D5/18 , F01D25/12 , F05D2230/80 , F05D2230/90 , F05D2240/80 , F05D2240/81 , F05D2300/21 , F05D2300/603 , F05D2300/611
摘要： Aspects of the invention are related to a turbine vane assembly in which at least one of the platforms is equipped with one or more removable platform inserts. The inserts can be used in those areas of the platform where failures or damage has been known to occur, among other locations. If an insert becomes damaged or is destroyed during engine operation, the insert can be easily replaced, and the platform frames and the airfoil can be reused. As a result, the overall life of the vane can be extended. Further, the inserts can be made of materials that can reduce cooling requirements compared to known turbine vanes, thereby allowing cooling air to be used for other uses in the engine.
摘要翻译：本发明的方面涉及涡轮叶片组件，其中至少一个平台装备有一个或多个可移除的平台插入件。这些插入件可用于已知发生故障或损坏的平台的其他位置的那些区域。如果在发动机运行期间插入件损坏或损坏，则可以方便地更换插入件，并可以重新使用平台框架和翼型件。结果，叶片的整体寿命可以延长。此外，与已知的涡轮叶片相比，插入件可以由能够降低冷却要求的材料制成，从而允许将冷却空气用于发动机中的其它用途。

8. 发明授权

US08322983B2 Ceramic matrix composite structure 有权
标题翻译：陶瓷基复合结构
公开(公告)号：US08322983B2
公开(公告)日：2012-12-04
申请号：US12208542
申请日：2008-09-11
申请人： Bonnie D. Marini
发明人： Bonnie D. Marini
IPC分类号： F01D25/24
CPC分类号： F23R3/60 , F23R3/007 , Y10T428/24008
摘要： A composite structure (10), which may be a 2-dimensional ceramic matrix composite material, may include a first body (30) made of a composite material defining a first in-plane direction, a second body (20) made of a composite material defining a second in-plane direction wherein the first body (30) is connected with the second body (20) so that the first in-plane direction is substantially normal to the second in-plane direction. The second body (20) of the composite structure may include a first leg (24), a first bolting surface (22) extending from the first leg (24) and at least one aperture (56) formed in the first bolting surface (22) substantially normal to the second in-plane direction. A first recess (32) may be formed within the first body (30) sized to receive the first leg (24).
摘要翻译：可以是二维陶瓷基复合材料的复合结构（10）可以包括由限定第一面内方向的复合材料制成的第一主体（30），由复合材料制成的第二主体（20）限定第二平面方向的材料，其中所述第一主体（30）与所述第二主体（20）连接，使得所述第一面内方向基本上垂直于所述第二平面内方向。复合结构的第二主体（20）可以包括第一腿部（24），从第一腿部（24）延伸的第一螺栓连接表面（22）和形成在第一螺栓连接表面（22）中的至少一个孔）基本上垂直于第二平面内方向。第一凹部（32）可以形成在第一主体（30）内，其尺寸适于接纳第一腿部（24）。

9. 发明申请

US20100062210A1 CERAMIC MATRIX COMPOSITE STRUCTURE 有权
标题翻译：陶瓷基体复合结构
公开(公告)号：US20100062210A1
公开(公告)日：2010-03-11
申请号：US12208542
申请日：2008-09-11
申请人： Bonnie D. Marini
发明人： Bonnie D. Marini
IPC分类号： B32B3/06
CPC分类号： F23R3/60 , F23R3/007 , Y10T428/24008
摘要： A composite structure (10), which may be a 2-dimensional ceramic matrix composite material, may include a first body (30) made of a composite material defining a first in-plane direction, a second body (20) made of a composite material defining a second in-plane direction wherein the first body (30) is connected with the second body (20) so that the first in-plane direction is substantially normal to the second in-plane direction. The second body (20) of the composite structure may include a first leg (24), a first bolting surface (22) extending from the first leg (24) and at least one aperture (56) formed in the first bolting surface (22) substantially normal to the second in-plane direction. A first recess (32) may be formed within the first body (30) sized to receive the first leg (24).
摘要翻译：可以是二维陶瓷基复合材料的复合结构（10）可以包括由限定第一面内方向的复合材料制成的第一主体（30），由复合材料制成的第二主体（20）限定第二平面方向的材料，其中所述第一主体（30）与所述第二主体（20）连接，使得所述第一面内方向基本上垂直于所述第二平面内方向。复合结构的第二主体（20）可以包括第一腿部（24），从第一腿部（24）延伸的第一螺栓连接表面（22）和形成在第一螺栓连接表面（22）中的至少一个孔）基本上垂直于第二平面内方向。第一凹部（32）可以形成在第一主体（30）内，其尺寸适于接纳第一腿部（24）。

10. 发明申请

US20130227954A1 GAS TURBINE ENGINE CONFIGURED TO SHAPE POWER OUTPUT 有权
标题翻译：气体涡轮发动机配置形成电源输出
公开(公告)号：US20130227954A1
公开(公告)日：2013-09-05
申请号：US13754936
申请日：2013-01-31
申请人： Bonnie D. Marini , Brian J. Bohinsky
发明人： Bonnie D. Marini , Brian J. Bohinsky
IPC分类号： F02C9/20
CPC分类号： F02C9/20 , F02C7/057 , F02C9/28 , F02C9/54 , F05D2270/05 , F05D2270/20
摘要： A gas turbine engine and method of controlling the gas turbine engine that may be utilized in a power grid having a plurality of additional power generation sources. The gas turbine engine is configured with a compressor having an enlarged mass flow volume. The gas turbine engine may be operated at a base load for supplying power to the power grid at a part load and optimum efficiency for the engine, and may be ramped up to a higher output to supply a peak load output to the power grid.
摘要翻译：一种燃气涡轮发动机和控制可用于具有多个附加发电源的电网中的燃气涡轮发动机的方法。燃气涡轮发动机配置有具有扩大的质量流量的压缩机。燃气涡轮发动机可以在基本负载下操作，以在部分负载处为发电机提供电力并且对于发动机提供最佳效率，并且可以升高到更高的输出以向电网提供峰值负载输出。

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