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51. 发明申请

US20090071160A1 Wavy CMC Wall Hybrid Ceramic Apparatus 有权
标题翻译：波纹CMC墙混合陶瓷设备
公开(公告)号：US20090071160A1
公开(公告)日：2009-03-19
申请号：US11855623
申请日：2007-09-14
申请人： Douglas A. Keller , Anthony L. Schiavo , Jay A. Morrison
发明人： Douglas A. Keller , Anthony L. Schiavo , Jay A. Morrison
IPC分类号： F01D25/24 , F02C7/24
CPC分类号： F01D9/023 , F23R3/007 , Y10T428/1317
摘要： A ceramic hybrid structure (207, 502, 602, 608) that includes a wavy ceramic matrix composite (CMC) wall (214, 532, 603, 609) bonded with a ceramic insulating layer (230, 538, 604, 610) having a distal surface (242) that may define a hot gas passage (250, 550, 650) or otherwise be in proximity to a source of elevated temperature. In various embodiments, the waves (216, 537, 637) of the CMC wall (214, 532, 603, 609) may conform to the following parameters: a thickness (222) between 1 and 10 millimeters; an amplitude (224) between one and 2.5 times the thickness; and a period (226) between one and 20 times the amplitude. The uninsulated backside surface (218) of the CMC wall (214) provides a desired stiffness and strength and enhanced cooling surface area. In various embodiments the amplitude (224), excluding the thickness (222), may be at least 2 mm.
摘要翻译：一种陶瓷混合结构（207,502,602,608），其包括与陶瓷绝缘层（230,538,604,610）接合的波纹陶瓷基复合材料（CMC）壁（214,532,603,609），其具有远端表面（242），其可以限定热气体通道（250,550,650）或以其它方式接近升高的温度源。在各种实施例中，CMC壁（214,532,603,609）的波浪（216,537,637）可以符合以下参数：1和10毫米之间的厚度（222）; 幅度（224）为厚度的1至2.5倍; 以及振幅的1到20倍之间的周期（226）。 CMC壁（214）的未绝缘的背侧表面（218）提供期望的刚度和强度以及增强的冷却表面积。在各种实施例中，不包括厚度（222）的振幅（224）可以至少为2mm。

52. 发明申请

US20090010755A1 Ceramic matrix composite attachment apparatus and method 有权
标题翻译：陶瓷基复合材料附着装置及方法
公开(公告)号：US20090010755A1
公开(公告)日：2009-01-08
申请号：US11824796
申请日：2007-07-03
申请人： Douglas A. Keller , Jay A. Morrison
发明人： Douglas A. Keller , Jay A. Morrison
IPC分类号： F01D1/02
CPC分类号： F01D25/243 , F01D21/045 , F01D25/246 , F05D2300/21 , F05D2300/603
摘要： An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring (36, 68), to a metal support structure. A CMC flange (20A) may be formed by attaching a wedge-shaped block (26) of a ceramic material to a CMC wall structure (22), and wrapping CMC layers (24) of the wall structure (22) at least partly around the block (26), forming the flange (20A) with an inner oblique face (34) and an outer face (35) normal to the wall structure. An adjacent support structure, such as a metal support ring (40A), may abut the outer face (35) of the CMC flange (20A) and be clamped or bolted to the CMC flange (20A).
摘要翻译：用于将诸如燃气涡轮机护罩环（36,68）的陶瓷基体复合材料（CMC）部件连接到金属支撑结构的附接方法和法兰。可以通过将陶瓷材料的楔形块（26）附接到CMC壁结构（22）并且至少部分地围绕壁结构（22）的CMC层（24）包裹来形成CMC凸缘（20A）所述块体（26）形成具有与所述壁结构垂直的内倾斜面（34）和外表面（35）的所述凸缘（20A）。诸如金属支撑环（40A）的相邻的支撑结构可以邻接CMC凸缘（20A）的外表面（35）并且被夹紧或螺栓连接到CMC凸缘（20A）。

53. 发明授权

US07255535B2 Cooling systems for stacked laminate CMC vane 有权
标题翻译：堆叠层压板CMC叶片的冷却系统
公开(公告)号：US07255535B2
公开(公告)日：2007-08-14
申请号：US11002030
申请日：2004-12-02
申请人： Harry A. Albrecht , Yevgeniy Shteyman , Steven James Vance , Jay A. Morrison
发明人： Harry A. Albrecht , Yevgeniy Shteyman , Steven James Vance , Jay A. Morrison
IPC分类号： F01D5/18 , F01D5/14
CPC分类号： F01D5/147 , F01D5/187 , F01D5/284 , F05D2260/201 , F05D2300/501 , F05D2300/603 , F05D2300/702
摘要： Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Such a vane construction lends itself to the inclusion of various cooling features in individual laminates using conventional manufacturing and forming techniques. When assembled in a radial stack, the cooling features in the individual laminates can cooperate to form intricate three dimensional cooling systems in the vane.
摘要翻译：本发明的实施例涉及由堆叠的陶瓷基质复合（CMC）层压体制成的涡轮叶片的各种冷却系统。每个翼型层压板具有基本上垂直于面内方向的面内方向和贯穿厚度方向。层压板具有各向异性强度特性，其中面内拉伸强度基本上大于贯穿厚度拉伸强度。这种叶片结构使得能够使用常规的制造和成形技术将各种冷却特征包含在单独的层压板中。当组装成径向堆叠时，单个层压板中的冷却特征可以协作以在叶片中形成复杂的三维冷却系统。

54. 发明授权

US07247003B2 Stacked lamellate assembly 有权
标题翻译：堆叠层状组件
公开(公告)号：US07247003B2
公开(公告)日：2007-07-24
申请号：US11031797
申请日：2005-01-07
申请人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
发明人： Michael A. Burke , Jay A. Morrison , Steven James Vance , Daniel G. Thompson , Vijay Parthasarathy , Gary B. Merrill , Douglas Allen Keller
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , F01D5/284 , F04D29/388 , F05D2230/23 , F05D2300/601 , F05D2300/603 , F05D2300/614
摘要： A stacked ceramic matrix composite lamellate assembly (10) including shear force bearing structures (48) for resisting relative sliding movement between adjacent lamellae. The shear force bearing structures may take the form of a cross-lamellar stitch (50), a shear pin (62), a warp (90) in the lamellae, a tongue (104) and groove (98) structure, or an inter-lamellar sealing member (112), in various embodiments. Each shear force bearing structure secures a subset of the lamellae, with at least one lamella being common between adjacent subsets in order to secure the entire assembly.
摘要翻译：一种层叠的陶瓷基复合材料层状组件（10），其包括用于抵抗相邻薄片之间的相对滑动运动的剪切力轴承结构（48）。剪切力承载结构可以采取跨层状缝合（50），剪切销（62），薄片中的经线（90），舌状物（104）和凹槽（98）结构的形式， - 绝缘密封件（112）。每个剪切力轴承结构确保薄片的一个子集，其中至少一个薄片在相邻子集之间是共同的，以便固定整个组件。

55. 发明授权

US07179524B2 Insulated ceramic matrix composite and method of manufacturing 有权
标题翻译：绝缘陶瓷基复合材料及其制造方法
公开(公告)号：US07179524B2
公开(公告)日：2007-02-20
申请号：US10667264
申请日：2003-09-19
申请人： Gary B. Merrill , Jay E. Lane , Steven C. Butner , Robert Kreutzer , Jay A. Morrison
发明人： Gary B. Merrill , Jay E. Lane , Steven C. Butner , Robert Kreutzer , Jay A. Morrison
IPC分类号： B32B3/00
CPC分类号： C04B38/085 , B28B11/041 , C04B28/00 , C04B28/18 , C04B28/34 , C04B35/117 , C04B35/18 , C04B35/803 , C04B41/009 , C04B41/5092 , C04B41/85 , C04B2235/3217 , C04B2235/3463 , C04B2235/5228 , C04B2235/528 , C04B2235/5436 , C04B2235/5445 , C04B2235/5472 , C04B2235/616 , Y10T428/249973 , C04B20/0036 , C04B20/004 , C04B14/303 , C04B14/306 , C04B14/324 , C04B14/328 , C04B20/0048 , C04B20/0076 , C04B38/0061 , C04B38/08
摘要： A composite material (10) formed of a ceramic matrix composite (CMC) material (12) protected by a ceramic insulating material (14). The constituent parts of the insulating material are selected to avoid degradation of the CMC material when the two layers are co-processed. The CMC material is processed to a predetermined state of shrinkage before wet insulating material is applied against the CMC material. The two materials are then co-fired together, with the relative amount of shrinkage between the two materials during the firing step being affected by the amount of pre-shrinkage of the CMC material during the bisque firing step. The shrinkage of the two materials during the co-firing step may be matched to minimize shrinkage stresses, or a predetermined amount of prestress between the materials may be achieved. An aluminum hydroxyl chloride binder material (24) may be used in the insulating material in order to avoid degradation of the fabric (28) of the CMC material during the co-firing step.
摘要翻译：由陶瓷绝缘材料（14）保护的陶瓷基复合材料（CMC）材料（12）形成的复合材料（10）。选择绝缘材料的组成部分以避免当两层被共同处理时CMC材料的劣化。在向CMC材料施加湿绝缘材料之前，将CMC材料加工成预定的收缩状态。然后将两种材料共烧，在焙烧步骤期间两种材料之间的相对收缩量受到在坯料烧结步骤期间CMC材料的预收缩量的影响。可以在共烧步骤期间两种材料的收缩率相匹配以最小化收缩应力，或者可以实现材料之间的预定量的预应力。可以在绝缘材料中使用铝羟基氯化物粘合剂材料（24），以避免在共烧烧步骤期间CMC材料的织物（28）的降解。

56. 发明授权

US06709230B2 Ceramic matrix composite gas turbine vane 有权
标题翻译：陶瓷基复合燃气轮机叶片
公开(公告)号：US06709230B2
公开(公告)日：2004-03-23
申请号：US10158946
申请日：2002-05-31
申请人： Jay A. Morrison , Chris Campbell , Gary Brian Merrill , Jay Edgar Lane , Daniel George Thompson , Harry A. Albrecht , Yevgeniy P. Shteyman
发明人： Jay A. Morrison , Chris Campbell , Gary Brian Merrill , Jay Edgar Lane , Daniel George Thompson , Harry A. Albrecht , Yevgeniy P. Shteyman
IPC分类号： F01D904
CPC分类号： F01D5/189 , F01D5/282 , F01D5/284 , F01D5/288 , F05D2300/50212 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676 , Y10T428/252 , Y10T428/257
摘要： A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.
摘要翻译：一种用于燃气涡轮发动机的混合叶片（50），其具有结合到基本上实心的芯构件（54）上的陶瓷基体复合（CMC）翼型件（52）。机翼构件和芯构件通过穿过形成在芯构件中的冷却通道（56）的冷却流体（58）来冷却。翼型部件通过导电传热通过芯部件和翼型部件之间的（70）进行冷却，并通过直接暴露于冷却流体的表面上的对流传热来冷却。翼型件的表面提供所需的外部空气动力学轮廓并且减少维持翼型构件的结构完整性所需的冷却流体的量。混合叶片的每个构件被配制成具有热膨胀系数和弹性模量，在制造期间和涡轮发动机运行期间最小化热应力。

57. 发明授权

US06235370B1 High temperature erosion resistant, abradable thermal barrier composite coating 有权
标题翻译：耐高温侵蚀，耐磨耐热复合涂层
公开(公告)号：US06235370B1
公开(公告)日：2001-05-22
申请号：US09261721
申请日：1999-03-03
申请人： Gary B. Merrill , Jay A. Morrison
发明人： Gary B. Merrill , Jay A. Morrison
IPC分类号： B32B312
CPC分类号： F23R3/007 , C23C4/02 , C23C26/02 , C23C28/042 , C23C28/044 , F01D5/288 , F01D11/125 , F01D11/127 , Y02T50/672 , Y10T29/49245 , Y10T428/1234 , Y10T428/24149
摘要： A composite thermal barrier coating system includes a honeycomb metallic structure filled with high thermal expansion ceramic hollow spheres in a phosphate bonded matrix. The composite thermal barrier coating system may be manufactured to thicknesses in excess of current thermal barrier coating systems, thereby imparting greater thermal protection. Superior erosion resistance and abrasion properties are also achieved. The composite thermal barrier coating is useful on combustion turbine components such as ring seal segments, vane segment shrouds, transitions and combustors.
摘要翻译：复合热障涂层系统包括在磷酸盐键合基质中填充有高热膨胀陶瓷中空球的蜂窝金属结构。复合热障涂层系统可以制造成超过当前热障涂层系统的厚度，从而赋予更大的热保护。也实现了优异的耐冲蚀性和耐磨性。复合热障涂层可用于燃气轮机部件，如环形密封段，叶片段护罩，过渡和燃烧器。

58. 发明授权

US09528706B2 Swirling midframe flow for gas turbine engine having advanced transitions 有权
标题翻译：具有高级过渡的燃气涡轮发动机的旋转中架流
公开(公告)号：US09528706B2
公开(公告)日：2016-12-27
申请号：US14105313
申请日：2013-12-13
申请人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
发明人： Matthew D. Montgomery , Richard C. Charron , Jose L. Rodriguez , Bernhard W. Küsters , Jay A. Morrison , Alexander R. Beeck
IPC分类号： F23R3/46 , F04D29/54 , F23R3/02 , F23R3/04 , F23R3/42
CPC分类号： F23R3/46 , F04D29/542 , F04D29/545 , F04D29/547 , F23R3/02 , F23R3/04 , F23R3/425
摘要： A gas turbine engine can-annular combustion arrangement (10), including: an axial compressor (82) operable to rotate in a rotation direction (60); a diffuser (100, 110) configured to receive compressed air (16) from the axial compressor; a plenum (22) configured to receive the compressed air from the diffuser; a plurality of combustor cans (12) each having a combustor inlet (38) in fluid communication with the plenum, wherein each combustor can is tangentially oriented so that a respective combustor inlet is circumferentially offset from a respective combustor outlet in a direction opposite the rotation direction; and an airflow guiding arrangement (80) configured to impart circumferential motion to the compressed air in the plenum in the direction opposite the rotation direction.
摘要翻译：一种燃气涡轮发动机罐环式燃烧装置（10），包括：轴向压缩机（82），其可操作以沿旋转方向（60）旋转; 构造成从所述轴向压缩机接收压缩空气（16）的扩散器（100,110）; 配置成从扩散器接收压缩空气的增压室（22）多个燃烧器罐（12）各自具有与所述气室流体连通的燃烧器入口（38），其中每个燃烧室可以被切向地定向，使得相应的燃烧器入口在与旋转相反的方向上与相应的燃烧室出口周向偏移方向; 以及气流引导装置（80），其构造成沿着与旋转方向相反的方向对所述增压室中的压缩空气施加周向运动。

59. 发明授权

US09297269B2 Patterned reduction of surface area for abradability 有权
标题翻译：图形化的表面积减少磨损性
公开(公告)号：US09297269B2
公开(公告)日：2016-03-29
申请号：US11800801
申请日：2007-05-07
申请人： Jay A. Morrison , Jay E. Lane , Gary B. Merrill
发明人： Jay A. Morrison , Jay E. Lane , Gary B. Merrill
IPC分类号： B32B3/30 , F01D11/12
CPC分类号： F01D11/122 , B32B3/30 , F05D2250/18 , F05D2250/70 , F05D2300/21 , F05D2300/603 , Y10T428/24355
摘要： A gas turbine component (20) with a layer of ceramic material (22) defining a wear surface (21), in which an array of cross-shaped depressions (26A, 26B) formed in the wear surface (21) define a continuous labyrinth of orthogonal walls (28, 30) of the ceramic material, and reduce the area of the wear surface (21) by about 50%. Within a representative area (36) of the wear surface (21), the depressions (26A, 26B) provide a ratio of a lineal sum of depression perimeters (27) divided by the representative area (36) of the wear surface of least 0.9 per unit of measurement for improved abradability characteristics of the wear surface (21).
摘要翻译：一种具有限定磨损表面（21）的陶瓷材料层（22）的燃气轮机部件（20），其中形成在磨损表面（21）中的十字形凹陷阵列（26A，26B）限定了连续的迷宫的陶瓷材料的正交壁（28,30），并且将磨损表面（21）的面积减小约50％。在磨损表面（21）的代表区域（36）内，凹陷（26A，26B）提供凹陷周长（27）的直线和除以磨损表面的代表区域（36）的比率为至少0.9 每单位测量以改善磨损表面（21）的耐磨特性。

60. 发明授权

US09133721B2 Turbine transition component formed from a two section, air-cooled multi-layer outer panel for use in a gas turbine engine 有权
标题翻译：涡轮转换部件由用于燃气涡轮发动机的两段风冷多层外板形成
公开(公告)号：US09133721B2
公开(公告)日：2015-09-15
申请号：US12945948
申请日：2010-11-15
申请人： Ching-Pang Lee , Jay A. Morrison
发明人： Ching-Pang Lee , Jay A. Morrison
IPC分类号： F23R3/46 , F01D9/02 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F05D2260/201
摘要： A cooling system for a transition duct for routing a gas flow from a combustor to the first stage of a turbine section in a combustion turbine engine is disclosed. The transition duct may have a multi-panel outer wall formed from an inner panel having an inner surface that defines at least a portion of a hot gas path plenum and an intermediate panel positioned radially outward from the inner panel such that at least one cooling chamber is formed between the inner and intermediate panels. The transition duct may also include an outer panel. The inner, intermediate and outer panels may include one or more metering holes for passing cooling fluids between cooling chambers for cooling the panels. The intermediate and outer panels may be secured with an attachment system coupling the panels to the inner panel such that the intermediate and outer panels may move in-plane.
摘要翻译：公开了一种用于将来自燃烧器的气流引导到燃气涡轮发动机中的涡轮部分的第一级的过渡管道的冷却系统。过渡管道可以具有由内板形成的多面板外壁，该内板具有限定热气路径气室的至少一部分的内表面和从内板径向向外定位的中间板，使得至少一个冷却室形成在内板和中间板之间。过渡管还可以包括外板。内部，中间和外部面板可以包括一个或多个计量孔，用于在冷却室之间通过冷却流体以冷却面板。中间板和外板可以用连接系统固定到内板上，使得中间板和外板可在平面内移动。

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