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61. 发明授权

US07351364B2 Method of manufacturing a hybrid structure 失效
标题翻译：制造混合结构的方法
公开(公告)号：US07351364B2
公开(公告)日：2008-04-01
申请号：US10767012
申请日：2004-01-29
申请人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Michael A. Burke
发明人： Jay A. Morrison , Gary B. Merrill , Steven James Vance , Michael A. Burke
IPC分类号： B28B11/00 , B28B5/00 , B29C33/76
CPC分类号： B28B7/342 , B28B11/08 , B28B19/00 , C04B2235/6028 , F05D2300/6033 , Y10S264/44
摘要： A method of manufacturing a hybrid structure (100) having a layer of CMC material (28) defining an interior passageway (24) and a layer of ceramic insulating material (18) lining the passageway. The method includes the step of casting the insulating material to a first thickness required for effective casting but in excess of a desired second thickness for use of the hybrid structure. An inner mold (14) defining a net shape desired for the passageway remains in place after the casting step to mechanically support the insulating material during a machining process used to reduce the thickness of the insulating material from the as-cast first thickness to the desired second thickness. The inner mold also provides support as the CMC material is deposited onto the insulating material. The inner mold may include a fugitive material portion (20) to facilitate its removal after the CMC material is formed.
摘要翻译：一种制造具有限定内部通道（24）的CMC材料层（28）和衬套通道的陶瓷绝缘材料层（18）的混合结构（100）的方法。该方法包括将绝缘材料浇铸到有效铸造所需的第一厚度但超过所需的第二厚度以用于混合结构的步骤。限定通道所需的净形状的内模（14）在铸造步骤之后保持就位，以在用于将绝缘材料的厚度从铸造第一厚度减小到期望的机械加工过程期间机械地支撑绝缘材料第二厚度。当CMC材料沉积到绝缘材料上时，内模还提供支撑。内部模具可以包括短暂材料部分（20），以便在形成CMC材料之后便于其移除。

62. 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。

63. 发明授权

US5962076A Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal 失效
标题翻译：可磨性组合物，可磨性组合物的制造方法和具有耐磨性密封件的燃气轮机
公开(公告)号：US5962076A
公开(公告)日：1999-10-05
申请号：US064143
申请日：1998-04-22
申请人： Stephen Mason , Michael J L Percival , Gary B. Merrill , Paul A. Doleman
发明人： Stephen Mason , Michael J L Percival , Gary B. Merrill , Paul A. Doleman
IPC分类号： F01D11/08 , B32B18/00 , C04B20/00 , C04B28/34 , C09K3/10 , F01D11/12 , F16J15/20 , C04B35/447 , B32B5/16 , C04B35/78 , F01D11/00
CPC分类号： B32B18/00 , C04B20/002 , C04B28/34 , F01D11/127 , B22F2003/1106 , C04B2111/00353 , C04B2111/00612 , C04B2235/656 , C04B2235/6567 , C04B2235/661 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/38 , Y10T428/252 , Y10T428/256 , Y10T428/259 , Y10T428/2982
摘要： An abradable seal comprises a plurality of hollow aluminosilicate spheres in a matrix of aluminium phosphate. The matrix of aluminium phosphate also has an aluminosilicate filler. The hollow aluminosilicate spheres have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate spheres in the abradable seal is 30% to 50%. The density of the abradable seal is 1.5 grams per cubic centimeter. The hollow aluminosilicate spheres in the aluminium phosphate matrix have a relatively high temperature capability of approximately 1300.degree. C. maximum. This makes the abradable seal better able to withstand the environment in the turbine of a turbofan gas turbine engine.
摘要翻译：可磨损密封件包括在磷酸铝基质中的多个中空铝硅酸盐球体。磷酸铝基质也具有铝硅酸盐填料。中空铝硅酸盐球体的直径在400至1800微米的范围内，优选直径在800至1400微米的范围内。耐磨密封件中的中空铝硅酸盐球的重量比例为30％至50％。耐磨密封件的密度为1.5克/立方厘米。磷酸铝基体中的中空铝硅酸盐球体具有最高约1300℃的较高温度能力。这使得可磨损密封件更好地能够承受涡轮风扇燃气涡轮发动机的涡轮机中的环境。

64. 发明授权

US5780146A Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal 失效
标题翻译：可磨性组合物，可磨性组合物的制造方法和具有耐磨性密封件的燃气轮机
公开(公告)号：US5780146A
公开(公告)日：1998-07-14
申请号：US651486
申请日：1996-05-22
申请人： Stephen Mason , Michael J. L. Percival , Gary B. Merrill , Paul A. Doleman
发明人： Stephen Mason , Michael J. L. Percival , Gary B. Merrill , Paul A. Doleman
IPC分类号： F01D11/08 , B32B18/00 , C04B20/00 , C04B28/34 , C09K3/10 , F01D11/12 , F16J15/20 , C04B35/447 , B32B5/16 , C04B35/78 , F01D11/00
CPC分类号： B32B18/00 , C04B20/002 , C04B28/34 , F01D11/127 , B22F2003/1106 , C04B2111/00353 , C04B2111/00612 , C04B2235/656 , C04B2235/6567 , C04B2235/661 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/38 , Y10T428/252 , Y10T428/256 , Y10T428/259 , Y10T428/2982
摘要： An abradable seal comprises a plurality of hollow aluminosilicate spheres in a matrix of aluminium phosphate. The matrix of aluminium phosphate also has an aluminosilicate filler. The hollow aluminosilicate spheres have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate spheres in the abradable seal is 30% to 50%. The density of the abradable seal is 1.5 grammes per cubic centimetre. The hollow aluminosilicate spheres in the aluminium phosphate matrix have a relatively high temperature capability of approximately 1300.degree. C. maximum. This makes the abradable seal better able to withstand the environment in the turbine of a turbofan gas turbine engine.
摘要翻译：可磨损密封件包括在磷酸铝基质中的多个中空铝硅酸盐球体。磷酸铝基质也具有铝硅酸盐填料。中空铝硅酸盐球体的直径在400至1800微米的范围内，优选直径在800至1400微米的范围内。耐磨密封件中的中空铝硅酸盐球的重量比例为30％至50％。耐磨密封件的密度为1.5克/立方厘米。磷酸铝基体中的中空铝硅酸盐球体具有最高约1300℃的较高温度能力。这使得可磨损密封件更好地能够承受涡轮风扇燃气涡轮发动机的涡轮机中的环境。

65. 发明授权

US09328028B2 Structure and method for protecting a hybrid ceramic structure from moisture attack in a high temperature environment 有权
标题翻译：在高温环境下保护混合陶瓷结构免受水分侵蚀的结构和方法
公开(公告)号：US09328028B2
公开(公告)日：2016-05-03
申请号：US12177531
申请日：2008-07-22
申请人： Jay E. Lane , Gary B. Merrill
发明人： Jay E. Lane , Gary B. Merrill
IPC分类号： C04B41/50 , F01D5/28 , B32B18/00 , C04B41/45 , C04B41/00
CPC分类号： C04B41/5025 , B32B18/00 , C04B41/009 , C04B41/457 , F01D5/282 , Y10T428/249953 , C04B41/4535 , C04B41/5024 , C04B41/5042 , C04B41/5044 , C04B41/5045 , C04B41/5032 , C04B35/803 , C04B28/34
摘要： A hybrid ceramic structure and a method for protecting the hybrid ceramic structure from moisture attack in a high temperature combustion environment are provided. The structure includes a ceramic matrix composite (CMC) substrate (12). A thermal insulation material (14) is disposed on the substrate. A vapor resistant material (20) is applied through at least one surface of the hybrid ceramic structure while the hybrid ceramic structure is in a bisque condition that provides a degree of porosity to the hybrid ceramic structure so that the vapor resistant material is infiltrated through interstices available within a thickness of the hybrid ceramic structure.
摘要翻译：提供了一种混合陶瓷结构和用于保护混合陶瓷结构免受高温燃烧环境中的水分侵害的方法。该结构包括陶瓷基质复合材料（CMC）衬底（12）。绝热材料（14）设置在基板上。通过混合陶瓷结构的至少一个表面施加防蒸汽材料（20），而混合陶瓷结构处于向混合陶瓷结构提供一定程度的孔隙度的条纹状态，使得耐蒸汽材料通过间隙渗透可用于混合陶瓷结构的厚度。

66. 发明授权

US09206983B2 Internal combustion engine hot gas path component with powder metallurgy structure 有权
标题翻译：内燃机热气路组件，粉末冶金结构
公开(公告)号：US09206983B2
公开(公告)日：2015-12-08
申请号：US13096128
申请日：2011-04-28
申请人： Gary B. Merrill , Iain A. Fraser
发明人： Gary B. Merrill , Iain A. Fraser
IPC分类号： B32B5/18 , F23R3/00 , F23M5/08 , F23R3/06
CPC分类号： F23R3/002 , F23M5/08 , F23M2900/05004 , F23R3/06 , F23R2900/03041 , F23R2900/03042
摘要： A hot gas path component (100) including: a metallic substrate (102) disposed beneath an outer surface (112) of the component (100) that is exposed to a hot gas present during operation of an internal combustion engine; a thermal barrier coating (TBC) (110) disposed on the metallic substrate (102) and defining a first portion (118) of the component outer surface (112); and a powder metallurgy structure (104) bonded to the metallic substrate (102) and in contact with the TBC (110).
摘要翻译：一种热气路径部件（100），包括：金属基板（102），其设置在所述部件（100）的外表面（112）的下方，所述外表面暴露于内燃机的运转期间存在的热气体; 设置在所述金属基板（102）上并限定所述部件外表面（112）的第一部分（118）的热障涂层（TBC）（110）; 和结合到金属基底（102）并与TBC（110）接触的粉末冶金结构（104）。

67. 发明授权

US09132476B2 Multi-wall gas turbine airfoil cast using a ceramic core formed with a fugitive insert and method of manufacturing same 有权
标题翻译：使用由短片插入物形成的陶瓷芯和其制造方法的多壁燃气轮机翼型铸造
公开(公告)号：US09132476B2
公开(公告)日：2015-09-15
申请号：US14068061
申请日：2013-10-31
申请人： Ching-Pang Lee , Gary B. Merrill
发明人： Ching-Pang Lee , Gary B. Merrill
IPC分类号： B22C9/10 , B22C9/24 , B22C7/02 , F01D5/18 , F01D5/14
CPC分类号： B22C9/24 , B22C7/02 , B22C9/10 , B22C21/14 , F01D5/147 , F01D5/187 , F05D2230/211
摘要： A multi-wall gas turbine airfoil (192) and method of forming same using a casting core (150) having a monolithic body configured to define a pressure side wall (12), a suction side wall (14), and a third wall (16). The casting core is formed around a fugitive insert (96) during a single pour casting process.
摘要翻译：一种多壁燃气轮机翼型（192）及其使用具有整体式铸件（150）的成形方法，所述整体式主体构造成限定压力侧壁（12），吸力侧壁（14）和第三壁（ 16）。在单次浇铸过程期间，铸芯在短片（96）周围形成。

68. 发明授权

US09102015B2 Method and apparatus for fabrication and repair of thermal barriers 有权
标题翻译：制造和修复热障的方法和装置
公开(公告)号：US09102015B2
公开(公告)日：2015-08-11
申请号：US13827233
申请日：2013-03-14
申请人： Anand A. Kulkarni , Ahmed Kamel , Stefan Lampenscherf , Jonathan E. Shipper, Jr. , Cora Schillig , Gary B. Merrill
发明人： Anand A. Kulkarni , Ahmed Kamel , Stefan Lampenscherf , Jonathan E. Shipper, Jr. , Cora Schillig , Gary B. Merrill
IPC分类号： B23K31/02 , B23K10/00 , B23P6/00 , B23K1/00 , B22F7/06 , B23K35/02 , B22F5/04 , B22F3/105 , B22F5/00 , B23K35/30 , C23C26/00 , F01D11/08 , F01D11/12 , B22F7/02 , B23K1/008
CPC分类号： F01D5/284 , B22F3/105 , B22F5/009 , B22F5/04 , B22F7/02 , B22F7/06 , B22F7/062 , B23K1/0012 , B23K1/0018 , B23K1/008 , B23K35/02 , B23K35/0222 , B23K35/0244 , B23K35/3033 , B23K35/304 , B23K2101/001 , B23P6/005 , C22C19/03 , C22C19/056 , C22C19/058 , C23C26/00 , F01D11/08 , F01D11/122 , F05B2230/80 , F05B2230/90 , F05D2230/30 , F05D2230/80 , F05D2240/11 , Y10T428/24612 , Y10T428/249961
摘要： A thermal barrier tile (34) with a braze layer (46) co-sintered to a ceramic layer (48) is brazed to a substrate (26) of a component for fabrication or repair of a thermal barrier coating (28) for example on a gas turbine ring segment (22, 24). The tile may be fabricated by disposing a first layer of a metal brazing material in a die case (40); disposing a second layer of a ceramic powder on the metal brazing material; and co-sintering the two layers with spark plasma sintering to form the co-sintered ceramic/metal tile. A material property of an existing thermal barrier coating to be repaired may be determined (90), and the co-sintering may be controlled (93) responsive to the property to produce tiles compatible with the existing thermal barrier coating in a material property such as thermal conductivity.
摘要翻译：共烧结到陶瓷层（48）的钎焊层（46）的热障砖（34）钎焊到用于制造或修复热障涂层（28）的部件的基底（26）上，例如，燃气涡轮机环段（22,24）。可以通过在模具壳体（40）中设置金属钎焊材料的第一层来制造瓦片。在所述金属钎料上设置第二层陶瓷粉末; 并用放电等离子体烧结共烧两层以形成共烧陶瓷/金属瓦。可以确定待修复的现有热障涂层的材料性质（90），并且响应于该性质可以控制共烧结（93）以产生与现有热障涂层相容的瓷砖，材料性质如导热系数。

69. 发明授权

US08940114B2 Hybrid manufacturing process and product made using laminated sheets and compressive casing 有权
标题翻译：混合制造工艺和使用层压板和压缩套管制成的产品
公开(公告)号：US08940114B2
公开(公告)日：2015-01-27
申请号：US13094985
申请日：2011-04-27
申请人： Allister W. James , Gary B. Merrill , Iain A. Fraser
发明人： Allister W. James , Gary B. Merrill , Iain A. Fraser
IPC分类号： B32B37/02 , B28B1/00
CPC分类号： B32B3/266 , B28B1/002 , B32B1/00 , B32B2605/00 , B33Y10/00 , Y10T428/249923
摘要： Fabricating a core of a component (34A, 34B, 34C) from a stack (25, 36) of sheets (20) of material with cutouts (22A) in the sheets aligned to form passages (38) in the core. A casing preform (28) is then fitted over the core. The preform is processed to form a casing (29) that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses (46) the sheets together. The preform may slide (52) over the core, and may be segmented (28A, 28B, 28C) to fit over the core. A hoop (66) may be fitted and compressed around the segmented casing (29A, 29B, 29C).
摘要翻译：从片材（20）的堆叠（25,36）制造组件（34A，34B，34C）的芯，其中片材中的切口（22A）被排列成在芯中形成通道（38）。然后将壳体预制件（28）装配在芯上。处理预成型件以形成一个壳体（29），该壳体（29）支撑堆叠的相对端的至少部分。加工过程中外壳的收缩将片材（46）压缩在一起。预制件可以在芯上滑动（52），并且可以被分段（28A，28B，28C）以配合在芯上。箍（66）可以围绕分段的壳体（29A，29B，29C）被安装和压缩。

70. 发明授权

US08790082B2 Gas turbine blade with intra-span snubber 有权
标题翻译：带跨度缓冲器的燃气轮机叶片
公开(公告)号：US08790082B2
公开(公告)日：2014-07-29
申请号：US12848456
申请日：2010-08-02
申请人： Gary B. Merrill , Clinton Mayer
发明人： Gary B. Merrill , Clinton Mayer
IPC分类号： F01D5/22
CPC分类号： F01D5/187 , B22C9/04 , B22C9/10 , F01D5/147 , F01D5/16 , F05D2230/21 , F05D2230/236 , F05D2230/237 , F05D2300/21
摘要： A gas turbine blade (10) including a hollow mid-span snubber (16). The snubber is affixed to the airfoil portion (14) of the blade by a fastener (20) passing through an opening (24) cast into the surface (22) of the blade. The opening is defined during an investment casting process by a ceramic pedestal (38) which is positioned between a ceramic core (32) and a surrounding ceramic casting shell (48). The pedestal provides mechanical support for the ceramic core during both wax and molten metal injection steps of the investment casting process.
摘要翻译：一种包括中空中跨缓冲器（16）的燃气轮机叶片（10）。缓冲器通过穿过叶片的表面（22）的开口（24）的紧固件（20）固定到叶片的翼型部分（14）上。该开口是通过位于陶瓷芯（32）和周围的陶瓷铸造壳（48）之间的陶瓷基座（38）在熔模铸造过程中限定的。在熔模铸造工艺的蜡和熔融金属注射步骤期间，基座为陶瓷芯提供机械支撑。

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