公开(公告)号：US10752557B2

公开(公告)日：2020-08-25

申请号：US15979079

申请日：2018-05-14

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: B23K20/00 ,  C04B37/02 ,  B23K20/02 ,  B23K20/16 ,  B23K20/233 ,  B23K20/04 ,  B32B7/04 ,  B32B15/04 ,  B23K103/16

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.

公开(公告)号：US20200023452A1

公开(公告)日：2020-01-23

申请号：US16126427

申请日：2018-09-10

Applicant: United Technologies Corporation

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

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

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.

公开(公告)号：US20190048727A1

公开(公告)日：2019-02-14

申请号：US16161265

申请日：2018-10-16

Applicant: United Technologies Corporation

Inventor： Gary Roberge ,  Grant O. Cook, III

IPC: F01D5/14 ,  F01D5/28 ,  F01D5/18 ,  B23K20/02 ,  B32B37/12 ,  B23K1/00 ,  B23P15/04 ,  B23K103/08 ,  B23K103/00 ,  B23K101/00 ,  B23K103/18

Abstract: A gas turbine engine component includes an airfoil that has first and second structural airfoil segments that are bonded to each other in at least one diffusion joint. The first and second structural airfoil segments are formed of, respectively, first and second materials. The first and second materials are: different base-metal metallic alloys, a metallic alloy and a ceramic-based material, or ceramic-based materials that differ by at least one of composition and microstructure. The first structural airfoil segment is a first skin and the second structural airfoil segment is a hollow core that has an airfoil shape.

公开(公告)号：US09586868B2

公开(公告)日：2017-03-07

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: B23K20/00 ,  B23K31/00 ,  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：US20160265363A1

公开(公告)日：2016-09-15

申请号：US15033933

申请日：2014-11-05

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/14 ,  F02C7/12 ,  F01D5/32 ,  F01D5/18 ,  F02C3/04 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D5/284 ,  F01D5/326 ,  F02C3/04 ,  F02C7/12 ,  F05D2220/32 ,  F05D2230/236 ,  F05D2230/51 ,  F05D2240/11 ,  F05D2240/12 ,  F05D2300/6033 ,  Y02T50/672

Abstract: An airfoil component includes a first segment that has a first piece of a mount and a first piece of an airfoil. The first segment is formed of a first ceramic-based material. A second segment includes a second piece of the mount and a second piece of the airfoil. The second segment is formed of a second ceramic-based material. The first and second segments are bonded together along a bond joint such that the first and second pieces of the mount are bonded to each other and the first and second pieces of the airfoil are bonded to each other.

Abstract translation: 机翼部件包括具有第一安装座和第一翼片的第一段。 第一段由第一陶瓷基材料形成。 第二段包括第二段安装件和第二段翼型件。 第二段由第二陶瓷基材料形成。 第一和第二段沿着接合接头结合在一起，使得第一和第二安装件彼此接合并且第一和第二翼片彼此接合。

公开(公告)号：US20140093384A1

公开(公告)日：2014-04-03

申请号：US13718134

申请日：2012-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Sergey Mironets ,  Wendell V. Twelves ,  Grant O. Cook, III ,  Robert P. Delisle ,  Agnes Klucha ,  William J. Ward

IPC: F01D5/14

CPC classification number: F01D5/147 ,  B22F5/009 ,  B22F5/04 ,  B22F2998/10 ,  B23P15/006 ,  B29C64/00 ,  B33Y10/00 ,  B33Y80/00 ,  C25D1/02 ,  F01D5/34 ,  F05D2230/22 ,  B29C67/00 ,  C25D1/00 ,  B22F2005/103 ,  B22F3/115 ,  B22F3/15

Abstract: A method of forming a complex shaped part includes the steps of forming a polymer core by an additive manufacturing process. A metal is plated about surfaces of the polymer core, and the polymer core is removed, leaving hollows within a plate core. Metal powder is deposited within the hollows. An integral blade rotor is also disclosed.

Abstract translation: 形成复杂成形部件的方法包括通过添加剂制造工艺形成聚合物芯的步骤。 金属围绕聚合物芯的表面被镀覆，并且聚合物芯被去除，留下中空在板芯内。 金属粉末沉积在凹槽内。 还公开了一体的叶片转子。

公开(公告)号：US11268526B2

公开(公告)日：2022-03-08

申请号：US14903996

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Roach ,  Barry Barnett ,  Grant O. Cook, III ,  Charles R. Watson ,  Shari L. Bugaj ,  Glenn LeVasseur ,  Wendell V. Twelves, Jr. ,  Christopher J. Hertel ,  Colin J. Kling ,  Matthew A. Turner ,  JinQuan Xu ,  Steven Clarkson ,  Michael Caulfield

IPC: F01D5/28 ,  F04D19/00 ,  F01D5/14 ,  B32B27/34 ,  B32B1/08 ,  B32B1/00 ,  B32B27/28 ,  B32B27/36 ,  F01D5/26 ,  F01D9/04 ,  F01D25/02 ,  F01D25/24 ,  F04D29/38 ,  F04D29/54

Abstract: Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

公开(公告)号：US10648482B2

公开(公告)日：2020-05-12

申请号：US16011979

申请日：2018-06-19

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F04D29/38 ,  B23P15/04 ,  B23K20/02 ,  B23K20/16 ,  F01D5/14 ,  F01D5/28 ,  F01D5/30 ,  F04D29/32 ,  F04D29/34 ,  B23K101/00 ,  B23K1/00

Abstract: The present disclosure relates to a method of manufacturing composite airfoils bonded to a metallic root. A composite body may be formed with a metallic co-molded member. The co-molded member may be transient liquid phase (TLP) bonded to a metallic root. The metallic root may allow the composite body to be attached to a rotor. The airfoil may also have a metallic edge which is TLP bonded to the composite body via a co-molded edge.

公开(公告)号：US10392949B2

公开(公告)日：2019-08-27

申请号：US14592942

申请日：2015-01-09

Applicant: United Technologies Corporation

Inventor： James T. Roach ,  Grant O. Cook, III ,  Colin J. Kling ,  James F. O'Brien ,  Shari L. Bugaj

IPC: F01D5/02 ,  F01D9/02 ,  F01D5/12 ,  F02C7/04 ,  B64C11/14

Abstract: A spinner for a gas turbine engine comprises an outer shell for defining an airflow path when mounted in a gas turbine engine. An inner surface is provided with a plurality of webs. A gas turbine engine and a fan section for a gas turbine engine are also disclosed.

公开(公告)号：US10227704B2

公开(公告)日：2019-03-12

申请号：US14903856

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wendell V. Twelves ,  Grant O. Cook, III

IPC: B64C1/00 ,  C25D5/56 ,  B33Y80/00 ,  B05D5/00 ,  B05D7/02 ,  B22C7/02 ,  B22C9/04 ,  B22C9/10 ,  B22F3/22 ,  B22F5/04 ,  B28B1/24 ,  B28B7/34 ,  B28B11/04 ,  B28B11/24 ,  B32B3/26 ,  B32B7/12 ,  B32B15/04 ,  B32B15/08 ,  B32B15/20 ,  B32B37/12 ,  B32B37/14 ,  B62D35/00 ,  B64C39/02 ,  C04B35/76 ,  C04B35/80 ,  C09D5/26 ,  C23C14/20 ,  C23C16/06 ,  C23C18/16 ,  C23C18/20 ,  C23C18/22 ,  C23C18/31 ,  C23C26/00 ,  C23C28/02 ,  C25D3/02 ,  C25D3/38 ,  C25D3/46 ,  C25D5/48 ,  C25D9/04 ,  C25D11/20 ,  F01D5/00 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/02 ,  F01D9/04 ,  F01D11/08 ,  F01D25/00 ,  F04D29/02 ,  F04D29/32 ,  F04D29/54 ,  F42B10/02 ,  B33Y10/00

Abstract: An airfoil is disclosed. The airfoil may comprise a leading edge, a body portion and a trailing edge formed from a high-modulus plating. The body portion of the airfoil may be formed from a material having a lower elastic modulus than the high-modulus plating. The high-modulus plating may improve the stiffness of the trailing edge, allowing for thinner trailing edges with improved fatigue life to be formed.