公开(公告)号：US10024333B2

公开(公告)日：2018-07-17

申请号：US14866194

申请日：2015-09-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Roach ,  Grant O. Cook, III

IPC: F01D5/14 ,  F04D29/38 ,  F01D5/28 ,  F01D5/30 ,  F04D29/32 ,  B23P15/04 ,  F04D29/34

Abstract: The present disclosure relates to composite airfoils bonded to a metallic root. A composite body (510) may be formed with a metallic co-molded detail (520). The co-molded detail (520) may be transient liquid phase (TLP) bonded to an attachment feature (530). The attachment feature (530) may allow the composite body (510) to be attached to a rotor (200). The airfoil (500) may also have a metallic edge (550) which is TLP bonded to the composite body (510) via a co-molded edge (540).

公开(公告)号：US20170015596A1

公开(公告)日：2017-01-19

申请号：US14601520

申请日：2015-01-21

Applicant: United Technologies Corporation

Inventor： Benjamin T. Fisk ,  Grant O. Cook, III

IPC: C04B37/02 ,  B32B7/04 ,  B32B15/04

CPC classification number: C04B37/026 ,  B23K20/02 ,  B23K20/021 ,  B23K20/16 ,  B23K20/2333 ,  B23K2103/16 ,  B32B7/04 ,  B32B15/04 ,  B32B2311/24 ,  B32B2315/02 ,  B32B2605/18 ,  C04B2237/121 ,  C04B2237/60

Abstract: A means for attaching a metallic component to a non-metallic component using a compliant material having thermal properties intermediate those of the metallic component to a non-metallic component is provided. The method can accommodate CTE mismatches and wear-type problems common to many assemblies of dissimilar materials. In particular, the method provides a sufficient wear surface to accommodate relative motion and provide a durable wear surface that does not excessively wear/gall/mico-weld itself together and provides the necessary damping and motion for proper operation in aeronautical applications.

Abstract translation: 提供了一种使用具有与金属成分相当的热性质的柔性材料将金属成分附着到非金属成分的方法。 该方法可以适应许多不同材料组件常见的CTE不匹配和磨损型问题。 特别地，该方法提供了足够的磨损表面以适应相对运动并且提供耐磨损的表面，其不会过度磨损/胆固醇/微焊接在一起，并为在航空应用中的正确操作提供必要的阻尼和运动。

公开(公告)号：US20160326891A1

公开(公告)日：2016-11-10

申请号：US15106608

申请日：2014-08-14

Applicant: United Technologies Corporation

Inventor： James T. Roach ,  Benjamin T. Fisk ,  Grant O. Cook, III

IPC: F01D5/28 ,  F01D25/00 ,  F01D11/08 ,  F01D25/24 ,  C23C16/44 ,  F01D9/04 ,  C23C24/04 ,  C23C18/16 ,  C23C14/22 ,  C09J5/00 ,  F01D5/30

Abstract: A compliant attachment for an organic matrix composite component that is configured to interface with a mating component is disclosed. The compliant attachment may comprise an inner surface configured to bond to an interfacing surface of a body portion of the organic matrix component, and an outer surface configured to interface with the mating component. The compliant attachment may have a coefficient of thermal expansion intermediate between a coefficient of thermal expansion of the body portion of the organic matrix composite component and a coefficient of thermal expansion of the mating component.

Abstract translation: 公开了一种配置成与配合部件相接合的有机基质复合部件的柔性附件。 柔性附件可以包括构造成结合到有机矩阵部件的主体部分的接合表面的内表面和被配置成与配合部件相接合的外表面。 柔性附件可以具有介于有机基质复合部件的主体部分的热膨胀系数与配合部件的热膨胀系数之间的热膨胀系数。

公开(公告)号：US20160236992A1

公开(公告)日：2016-08-18

申请号：US14912321

申请日：2014-08-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Grant O. Cook, III ,  Kevin W. Schlichting ,  Venkatarama K. Seetharaman

IPC: C04B37/00 ,  B23K20/16

CPC classification number: B23K20/16 ,  B23K20/00 ,  B23K35/3053 ,  B23K35/32 ,  B23K35/327 ,  B23K35/3601 ,  B23K35/3602 ,  B23K35/3606 ,  B32B15/01 ,  C04B37/001 ,  C04B37/003 ,  C04B37/006 ,  C04B37/023 ,  C04B37/026 ,  C04B2235/5224 ,  C04B2235/524 ,  C04B2235/5244 ,  C04B2235/5248 ,  C04B2237/122 ,  C04B2237/123 ,  C04B2237/124 ,  C04B2237/125 ,  C04B2237/16 ,  C04B2237/343 ,  C04B2237/348 ,  C04B2237/36 ,  C04B2237/365 ,  C04B2237/368 ,  C04B2237/38 ,  C04B2237/40 ,  C04B2237/401 ,  C04B2237/402 ,  C04B2237/403 ,  C04B2237/405 ,  C04B2237/406 ,  C04B2237/595 ,  C04B2237/60 ,  C04B2237/62 ,  C04B2237/64 ,  C04B2237/72 ,  F01D5/12 ,  F01D5/288 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/236 ,  F05D2240/35 ,  F05D2300/21 ,  F05D2300/2112 ,  F05D2300/2118 ,  F05D2300/22 ,  F05D2300/224 ,  F05D2300/2261 ,  F05D2300/2263 ,  F05D2300/2283 ,  F05D2300/2284 ,  F05D2300/5023 ,  F05D2300/5024 ,  F05D2300/6032 ,  F05D2300/6033

Abstract: A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

Abstract translation: 用于连接发动机部件的方法包括将第一多个热保护结构定位在第一热保护表面和第二热保护表面之间的热保护空间上。 第一和第二发动机部件通过在第一热保护表面和第二热保护表面之间形成第一多个瞬态液相（TLP）或部分瞬时液相（PTLP）键， 热保护面。 第二热保护表面由与第一热保护表面的第一表面材料不同的第二表面材料形成。

公开(公告)号：US20160075119A1

公开(公告)日：2016-03-17

申请号：US14890328

申请日：2014-02-27

Applicant: United Technologies Corporation

Inventor： Grant O. Cook, III

IPC: B32B37/06 ,  C04B37/02 ,  B32B7/04 ,  B32B7/02 ,  B32B37/14 ,  B32B15/01

CPC classification number: B32B37/06 ,  B32B7/02 ,  B32B7/04 ,  B32B9/005 ,  B32B9/041 ,  B32B15/01 ,  B32B37/04 ,  B32B2255/00 ,  B32B2255/06 ,  B32B2255/20 ,  B32B2255/205 ,  B32B2307/306 ,  B32B2307/308 ,  B32B2307/536 ,  B32B2307/718 ,  B32B2311/00 ,  B32B2315/02 ,  B32B2605/00 ,  B32B2605/18 ,  C04B37/026 ,  C04B2237/12 ,  C04B2237/122 ,  C04B2237/72

Abstract: A precipitation-hardened partial transient liquid phase bond and method of making same is provided. The bond is created at a bonding temperature and then, based on the phase diagrams corresponding to the materials in the interlayer between the bonded materials, the bond is held at a lower heat-treatment temperature to achieve a precipitation-hardened structure.

Abstract translation: 提供了一种沉淀硬化的部分瞬态液相键及其制备方法。 在键合温度下产生粘结，然后根据对应于粘结材料中间层的材料的相图，将粘结保持在较低的热处理温度，以达到沉淀硬化结构。

公开(公告)号：US20160032735A1

公开(公告)日：2016-02-04

申请号：US14775535

申请日：2014-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael G. McCaffrey ,  Michael G. Abbott ,  Grant O. Cook, III

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/284 ,  F01D5/147 ,  F01D5/225 ,  F01D5/282 ,  F01D11/08 ,  F05D2240/307 ,  F05D2300/6033

Abstract: A composite ceramic turbine blade includes a ceramic airfoil portion and a ceramic outer tip shroud portion. The ceramic outer tip shroud portion is joined to the ceramic airfoil portion by a bonding means. In an embodiment, the bonding means comprises partial transient liquid phase bonding. In another embodiment, the airfoil portion is a fiber reinforced ceramic.

Abstract translation: 复合陶瓷涡轮机叶片包括陶瓷翼型部分和陶瓷外部末端护罩部分。 陶瓷外端护罩部分通过接合装置连接到陶瓷翼型件部分。 在一个实施例中，接合装置包括部分瞬时液相结合。 在另一个实施例中，翼型部分是纤维增强陶瓷。

公开(公告)号：US20160024944A1

公开(公告)日：2016-01-28

申请号：US14775730

申请日：2014-02-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Ioannis Alvanos ,  Grant O. Cook, III ,  Mark F. Zelesky ,  Dilip M. Shah

IPC: F01D5/30 ,  F02C3/04 ,  F01D5/18

CPC classification number: F01D5/30 ,  B23K20/16 ,  B23K2101/001 ,  F01D5/18 ,  F01D5/3061 ,  F02C3/04 ,  Y02T50/672

Abstract: A rotor assembly for a turbine engine includes a rotor disk constructed of a first material. Multiple rotor blades constructed of a second material are connected to the rotor disk via a diffusion material.

Abstract translation: 用于涡轮发动机的转子组件包括由第一材料构成的转子盘。 由第二材料构成的多个转子叶片通过扩散材料连接到转子盘。

公开(公告)号：US20150202707A1

公开(公告)日：2015-07-23

申请号：US14510553

申请日：2014-10-09

Applicant: United Technologies Corporation

Inventor： Grant O. Cook, III ,  James T. Roach

IPC: B23K1/00 ,  F04D19/00 ,  F04D29/38 ,  B23K1/19

CPC classification number: B23K1/0018 ,  B23K1/19 ,  B23K2101/001 ,  F01D5/282 ,  F01D5/3061 ,  F01D5/3092 ,  F02K3/06 ,  F04D29/322 ,  F05D2220/36 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2300/433 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/437 ,  F05D2300/44 ,  F05D2300/48 ,  F05D2300/50212

Abstract: Methods of bonding first structures to second structures are disclosed wherein the first and second structures are fabricated materials having different physical characteristics. For example, the first structure may be a composite fan blade and the second structure may be a composite or metallic rotor, both for use in gas turbine engines. The method includes providing the first and second structures and plating or otherwise coating a portion of the first structure with a metal to provide a metal-coated portion. The method includes applying at least one intermediate material onto the metal-coated portion of the first structure. The method further includes bonding the metal-coated portion of the first structure and the intermediate material to the second structure. The bonding is carried out using a relatively low-temperature process, such as liquid phase bonding, including TLP and PTLP bonding. Brazing is also a suitable technique, depending on the materials chosen for the first and second structures.

Abstract translation: 公开了将第一结构粘合到第二结构的方法，其中第一和第二结构是具有不同物理特性的制造材料。 例如，第一结构可以是复合风扇叶片，并且第二结构可以是用于燃气涡轮发动机的复合或金属转子。 该方法包括提供第一和第二结构，并用金属电镀或以其他方式涂覆第一结构的一部分以提供金属涂覆部分。 该方法包括将至少一种中间材料施加到第一结构的金属涂覆部分上。 该方法还包括将第一结构的金属涂覆部分和中间材料结合到第二结构。 使用包括TLP和PTLP结合在内的相对低温的方法，例如液相结合来进行结合。 取决于为第一和第二结构选择的材料，钎焊也是合适的技术。

公开(公告)号：US10968758B2

公开(公告)日：2021-04-06

申请号：US16126427

申请日：2018-09-10

Applicant: United Technologies Corporation

Inventor： Grant O. Cook, III ,  James T. Roach

IPC: F01D5/30 ,  B23K1/00 ,  B23K1/19 ,  F01D5/28 ,  F04D29/32 ,  B23K101/00 ,  F02K3/06

Abstract: A rotor assembly for a gas turbine engine is disclosed. The assembly includes: a composite fan blade, the fan blade including a root; a metallic rotor including a slot for receiving the root; the root being at least partially coated with a metal to form a metal-coated portion; the metal-coated portion of the root being at least partially covered with an intermediate material; and the root, metal-coated portion and intermediate material being received in the slot and bonded to the rotor.

公开(公告)号：US20200240639A1

公开(公告)日：2020-07-30

申请号：US16827200

申请日：2020-03-23

Applicant: United Technologies Corporation

Inventor： Gary D. Roberge ,  Grant O. Cook, III

IPC: F23R3/00 ,  F23R3/06 ,  F02C7/18

Abstract: A combustor wall is provided for a turbine engine. The combustor wall includes a shell, a heat shield and a combustion chamber. The heat shield is connected to the shell by a bonded connection, and defines a portion of the combustion chamber. A cooling cavity is defined between the shell and the heat shield.