公开(公告)号：US06758653B2

公开(公告)日：2004-07-06

申请号：US10237769

申请日：2002-09-09

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: F01D1112

CPC classification number: F01D25/12 ,  F01D9/04 ,  F01D11/18

Abstract: A ceramic matrix composite (CMC) component for a combustion turbine engine (10). A blade shroud assembly (30) may be formed to include a CMC member (32) supported from a metal support member (32). The CMC member includes arcuate portions (50, 52) shaped to surround extending portions (46, 48) of the support member to insulate the metal support member from hot combustion gas (16). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap (42) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip (14). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot (76) defined by the arcuate portion.

Abstract translation: 一种用于燃气涡轮发动机（10）的陶瓷基体复合材料（CMC）组件。 叶片护罩组件（30）可以形成为包括从金属支撑构件（32）支撑的CMC构件（32）。 CMC构件包括成形为围绕支撑构件的延伸部分（46,48）的弓形部分（50,52），以使金属支撑构件与热燃烧气体（16）绝缘。 使用低导热性CMC材料允许金属支撑构件与CMC材料直接接触。 CMC构件和支撑构件之间的间隙（42）被有目的地保持小，以限制当CMC构件通过摩擦叶片尖端（14）的力而偏转抵靠支撑构件时产生的应力。 可以通过选择由弧形部分限定的锥形槽（76）的角度（A）来调节由差分热生长引起的间隙尺寸的变化。

公开(公告)号：US06746755B2

公开(公告)日：2004-06-08

申请号：US09962733

申请日：2001-09-24

Applicant: Jay Morrison ,  Steven C. Butner ,  Christian X. Campbell ,  Harry A. Albrecht ,  Yevgeuiy Shteyman

Inventor： Jay Morrison ,  Steven C. Butner ,  Christian X. Campbell ,  Harry A. Albrecht ,  Yevgeuiy Shteyman

IPC: B32B300

CPC classification number: B32B18/00 ,  B32B3/18 ,  B32B2315/02 ,  C04B35/645 ,  C04B35/80 ,  C04B38/0003 ,  C04B2111/00612 ,  C04B2235/6028 ,  C04B2235/6581 ,  C04B2237/341 ,  C04B2237/343 ,  C04B2237/365 ,  C04B2237/368 ,  C04B2237/38 ,  C04B2237/56 ,  C04B2237/62 ,  C04B2237/66 ,  C04B2237/704 ,  C04B2237/76 ,  F01D5/187 ,  F01D5/282 ,  Y10T428/24562 ,  Y10T428/24661 ,  Y10T428/24744 ,  C04B38/0645

Abstract: A multi-layer ceramic matrix composite structure (40) having a plurality of fiber-reinforced cooling passages (42) formed therein. The cooling passages are formed by the removal of a fugitive material (24). The fugitive material is part of a wrapped fugitive material structure (28) containing a layer of reinforcing ceramic fibers (26) that is used to lay-up the multi-layer structure. An intermediate layer of ceramic fabric 56 may be placed alternately over and under the wrapped fugitive material structure to separate the cooling passages into alternating upper (54) and lower (52) cooling passages. The transversely oriented fibers surrounding the cooling passages serve to increase the interlaminar strength of the structure when compared to prior art designs. An airfoil member (112) incorporating such reinforced integral cooling passages (120) is provided.

Abstract translation: 一种多层陶瓷基复合结构（40），其中形成有多个纤维增强的冷却通道（42）。 冷却通道是通过去除缓冲材料（24）形成的。 短暂的材料是包裹的缓冲材料结构（28）的一部分，其包含用于堆叠多层结构的增强陶瓷纤维层（26）。 陶瓷织物56的中间层可以交替地放置在缠绕的缓冲材料结构之上和之下，以将冷却通道分离成交替的上部（54）和下部（52）冷却通道。 与现有技术的设计相比，围绕冷却通道的横向取向的纤维用于增加结构的层间强度。 提供了包括这种加强的整体冷却通道（120）的翼型件（112）。

公开(公告)号：US09677849B2

公开(公告)日：2017-06-13

申请号：US15170868

申请日：2016-06-01

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: F41G1/467 ,  F41B5/14 ,  F41G1/35

CPC classification number: F41G1/467 ,  F41B5/1492 ,  F41G1/35

Abstract: A multiple laser sight system for an archery bow or the like configured so that the multiple laser systems can be calibrated together and having features such that the user can use one laser system during the day and one laser system during the light. The laser sight is further configured to not interfere with the optional use of conventional sighting pins and the use of evening infrared systems, like the prior art use of night vision goggles.

公开(公告)号：US07785076B2

公开(公告)日：2010-08-31

申请号：US11215582

申请日：2005-08-30

Applicant: Jay Morrison ,  Andrew Szweda

Inventor： Jay Morrison ,  Andrew Szweda

IPC: F01D5/18

CPC classification number: C04B41/5025 ,  C04B41/009 ,  C04B41/87 ,  F01D5/147 ,  F01D5/18 ,  F01D5/284 ,  F01D5/288 ,  F05D2230/90 ,  F05D2300/603 ,  F05D2300/611 ,  F05D2300/614 ,  F05D2300/702 ,  F23M2900/05004 ,  F23R3/007 ,  C04B35/803

Abstract: Aspects of the invention relate to a construction system and method for components in high temperature environments, such as the hot gas path components of a turbine engine. Such a component can include a skeleton and a coating. The skeleton can be formed by a plurality of interconnected frame members, which can give the component its general shape. The frame members can be made of ceramic matrix composite. A coating can be provided around at least a portion of the skeleton. Preferably, the coating is a refractory material, such as refractory ceramic. Examples of turbine engine components that can be constructed according to aspects of the invention are airfoils with or without platforms, blade rings, combustor tiles and heat shields. A component according to aspects of the invention can be made using low cost fabrication and construction methods.

Abstract translation: 本发明的方面涉及用于诸如涡轮发动机的热气路径部件的高温环境中的部件的构造系统和方法。 这样的组分可以包括骨架和涂层。 骨架可以由多个互连的框架构件形成，这可以使构件具有其大致形状。 框架构件可以由陶瓷基复合材料制成。 可以在骨架的至少一部分周围设置涂层。 优选地，涂层是耐火材料，例如难熔陶瓷。 可以根据本发明的方面构造的涡轮发动机部件的实例是具有或不具有平台，叶片环，燃烧器瓦片和隔热罩的翼型件。 可以使用低成本的制造和施工方法制造根据本发明的方面的部件。

公开(公告)号：US20070020105A1

公开(公告)日：2007-01-25

申请号：US11169477

申请日：2005-06-29

Applicant: Harry Albrecht ,  Yevgeniy Shteyman ,  Jay Morrison ,  Daniel Thompson

Inventor： Harry Albrecht ,  Yevgeniy Shteyman ,  Jay Morrison ,  Daniel Thompson

IPC: B64C27/46

CPC classification number: F01D5/147 ,  F04D29/388 ,  F05D2230/23 ,  F05D2300/601 ,  F05D2300/603 ,  F05D2300/614

Abstract: A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperating interlock features (30, 32) formed on the lamella and on the support structure respectively. Mating load-transferring surfaces (34, 36) of the interlock features are disposed in a plane (44) oblique to local axes of thermal growth (38, 40) in order to accommodate differential thermal expansion there between with delta alpha zero expansion (DAZE). Reinforcing fibers (62) within the CMC material may be oriented in a direction optimized to resist forces being transferred through the interlock features. Individual lamellae may all have the same structure or different interlock feature shapes and/or locations may be used in different groups of the lamellae. Applications for this invention include an airfoil assembly (10) and a ring segment assembly (82).

公开(公告)号：US20060120874A1

公开(公告)日：2006-06-08

申请号：US11031797

申请日：2005-01-07

Applicant: Michael Burke ,  Jay Morrison ,  Steven Vance ,  Daniel Thompson ,  Vijay Parthasarathy ,  Gary Merrill ,  Douglas Keller

Inventor： Michael Burke ,  Jay Morrison ,  Steven Vance ,  Daniel Thompson ,  Vijay Parthasarathy ,  Gary Merrill ,  Douglas Keller

IPC: F04D29/38

CPC classification number: F01D5/147 ,  F01D5/284 ,  F04D29/388 ,  F05D2230/23 ,  F05D2300/601 ,  F05D2300/603 ,  F05D2300/614

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06648597B1

公开(公告)日：2003-11-18

申请号：US10158966

申请日：2002-05-31

Applicant: Scott M. Widrig ,  Jay Morrison ,  Harry A. Albrecht ,  Yevgeniy Shteyman ,  Steven C. Butner

Inventor： Scott M. Widrig ,  Jay Morrison ,  Harry A. Albrecht ,  Yevgeniy Shteyman ,  Steven C. Butner

IPC: F01D904

CPC classification number: C04B37/001 ,  C04B37/005 ,  C04B2237/06 ,  C04B2237/068 ,  C04B2237/341 ,  C04B2237/343 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/61 ,  C04B2237/765 ,  C04B2237/80 ,  C04B2237/84 ,  F01D5/284 ,  F01D9/044 ,  F05D2230/22 ,  F05D2300/6033

Abstract: A ceramic matrix composite material (CMC) vane for a gas turbine engine wherein the airfoil member (12) and the platform member (14) are formed separately and are then bonded together to form an integral vane component (10). Airfoil member and the platform member may be bonded together by an adhesive (20) after being fully cured. Alternatively, respective joint surfaces (16, 18) of the green body state airfoil member and platform member may be co-fired together to form a sinter bond (30). A mechanical fastener (38) and/or a CMC doubler (42) may be utilized to reinforce the bonded joint (40). A matrix infiltration process (50) may be used to create or to further strengthen the bond.

Abstract translation: 一种用于燃气涡轮发动机的陶瓷基体复合材料（CMC）叶片，其中所述翼型件（12）和所述平台构件（14）分别形成，然后结合在一起以形成一体式叶片部件（10）。 在完全固化之后，翼型构件和平台构件可以通过粘合剂（20）结合在一起。 或者，可以将生坯状态翼型构件和平台构件的各个接合面（16,18）共烧在一起形成烧结层（30）。 机械紧固件（38）和/或CMC倍增器（42）可用于加强接合接头（40）。 矩阵渗透过程（50）可用于产生或进一步加强粘结。

公开(公告)号：US20150040409A1

公开(公告)日：2015-02-12

申请号：US14455445

申请日：2014-08-08

Applicant: Jay Morrison

Inventor： Jay Morrison

IPC: F41G1/467

CPC classification number: F41G1/467 ,  F41B5/1492 ,  F41G1/35

Abstract: A multiple laser sight system for an archery bow or the like configured so that the multiple laser systems can be calibrated together and having features such that the user can use one laser system during the day and one laser system during the light. The laser sight is further configured to not interfere with the optional use of conventional sighting pins and the use of evening infrared systems, like the prior art use of night vision goggles.

Abstract translation: 用于射箭弓等的多重激光瞄准系统被配置为使得多个激光系统可以被校准在一起并且具有这样的特征，使得用户可以在白天使用一个激光系统，并且在光线期间使用一个激光系统。 激光瞄准器被进一步构造成不干扰常规瞄准杆的可选使用以及晚上红外系统的使用，如现有技术使用夜视镜。

公开(公告)号：US20070140835A1

公开(公告)日：2007-06-21

申请号：US11002030

申请日：2004-12-02

Applicant: Harry Albrecht ,  Yevgeniy Shteyman ,  Steven Vance ,  Jay Morrison

Inventor： Harry Albrecht ,  Yevgeniy Shteyman ,  Steven Vance ,  Jay Morrison

IPC: F03B11/00

CPC classification number: F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F05D2260/201 ,  F05D2300/501 ,  F05D2300/603 ,  F05D2300/702

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20070128043A1

公开(公告)日：2007-06-07

申请号：US11040464

申请日：2005-01-21

Applicant: Jay Morrison ,  Gary Merrill ,  Steven Vance ,  Harry Albrecht ,  Yevgeniy Shteyman

Inventor： Jay Morrison ,  Gary Merrill ,  Steven Vance ,  Harry Albrecht ,  Yevgeniy Shteyman

IPC: F03B3/12

CPC classification number: F01D5/284 ,  F01D5/147 ,  F01D5/282 ,  Y10T29/49337 ,  Y10T29/49339

Abstract: An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.

Abstract translation: 由多个预烧结构的CMC板（46,48,50,52）形成的翼型件（44）。 每个板形成为具有相对端（54）的开放形状，其在CMC材料的干燥，固化和/或烧制期间自由移动，以便最小化由各向异性烧结收缩引起的层间应力。 在连接在一起以形成期望的结构之前，板至少部分地预收缩，例如用于燃气涡轮发动机的翼型件（42）。 例如，使用凸缘端部（54）和夹具（56）和/或与粘合材料（36）一起使用背衬构件（30）将面板连接在一起。