公开(公告)号：US20200018179A1

公开(公告)日：2020-01-16

申请号：US16036038

申请日：2018-07-16

Applicant: United Technologies Corporation

Inventor： Colin J. Kling

IPC: F01D11/00 ,  F04D29/32 ,  F01D5/02 ,  F01D5/30

Abstract: A fan rotor includes a fan hub and a plurality of fan blades extending radially outwardly from the fan hub. Platforms are positioned intermediate blade sides of adjacent ones of the fan blades. Seals are positioned between the blade sides and platform sides of the platform seals. The seals have an elongated bonding area bonded to one of the platform sides and the fan blade sides. The seal extends radially outwardly from the elongated bonding area to a wedge portion. A gas turbine engine and a seal are also disclosed.

公开(公告)号：US20190211705A1

公开(公告)日：2019-07-11

申请号：US15868289

申请日：2018-01-11

Applicant: United Technologies Corporation

Inventor： Colin J. Kling

IPC: F01D21/04 ,  F01D25/24 ,  B32B1/08 ,  B32B3/08 ,  B32B3/28 ,  B32B5/26 ,  D04C1/06

CPC classification number: F01D21/045 ,  B29C70/228 ,  B29C70/24 ,  B29C70/70 ,  B29C70/72 ,  B29D99/0014 ,  B32B1/08 ,  B32B3/08 ,  B32B3/28 ,  B32B5/26 ,  B32B2260/021 ,  D04C1/06 ,  D10B2401/063 ,  D10B2505/02 ,  F01D25/24 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2300/603 ,  F05D2300/6034

Abstract: A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

公开(公告)号：US20190128136A1

公开(公告)日：2019-05-02

申请号：US15797178

申请日：2017-10-30

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  Mark W. Costa

IPC: F01D21/04 ,  B29C63/34 ,  F01D25/24 ,  B29C53/56

CPC classification number: F01D21/045 ,  B29C53/562 ,  B29C63/34 ,  F01D21/04 ,  F01D25/24 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2250/15 ,  F05D2300/603

Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

公开(公告)号：US20160368238A1

公开(公告)日：2016-12-22

申请号：US14903880

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William Bogue ,  Grant O. Cook, III ,  Gary M. Lomasney ,  Joseph Parkos ,  Colin J. Kling ,  Charles R. Watson

IPC: B32B3/26 ,  B32B15/20 ,  C25D5/56 ,  C23C16/06 ,  C25D11/20 ,  C25D9/04 ,  B32B15/08 ,  C23C14/20

CPC classification number: C25D5/56 ,  B05D5/00 ,  B05D7/02 ,  B22C7/023 ,  B22C9/043 ,  B22C9/10 ,  B28B1/24 ,  B28B7/342 ,  B28B11/04 ,  B28B11/243 ,  B32B3/263 ,  B32B7/12 ,  B32B15/04 ,  B32B15/08 ,  B32B15/20 ,  B32B37/12 ,  B32B37/1284 ,  B32B37/14 ,  B32B2255/10 ,  B32B2307/202 ,  B32B2307/554 ,  B32B2603/00 ,  B33Y10/00 ,  B33Y80/00 ,  B62D35/00 ,  C04B35/76 ,  C04B35/806 ,  C09D5/26 ,  C23C14/20 ,  C23C16/06 ,  C23C18/1633 ,  C23C18/165 ,  C23C18/2013 ,  C23C18/22 ,  C23C18/31 ,  C23C26/00 ,  C23C28/02 ,  C25D3/02 ,  C25D3/38 ,  C25D3/46 ,  C25D5/48 ,  C25D9/04 ,  C25D11/20 ,  F01D5/00 ,  F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F01D5/288 ,  F01D9/02 ,  F01D9/041 ,  F01D11/08 ,  F01D25/005 ,  F04D29/023 ,  F04D29/324 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2230/312 ,  F05D2230/314 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2300/10 ,  F05D2300/11 ,  F05D2300/121 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/1616 ,  F05D2300/171 ,  F05D2300/177 ,  F05D2300/20 ,  F05D2300/30 ,  F05D2300/44 ,  F05D2300/501 ,  F05D2300/603 ,  F05D2300/611 ,  F05D2300/614 ,  F42B10/02

Abstract: A composite component and a plated polymer component are disclosed. The composite component may comprise a body portion formed from an organic matrix composite, a first metal coating applied to a surface of the body portion, and an outer metal layer on the first metal coating that is erosion-resistant. The plated polymer component may comprise a polymer substrate, a metal plating layer applied to a surface of the polymer substrate, and at least one selectively thickened region in the metal plating layer. The at least one selectively thickened region may assist in protecting the plated polymer component against wear and/or erosion.

Abstract translation: 公开了复合组分和镀覆聚合物组分。 复合部件可以包括由有机基质复合材料形成的主体部分，施加到主体部分的表面上的第一金属涂层以及耐腐蚀的第一金属涂层上的外部金属层。 镀覆的聚合物组分可以包括聚合物基材，施加到聚合物基材的表面的金属镀层，以及金属镀层中的至少一个选择性增稠区域。 所述至少一个选择性增稠的区域可有助于保护镀覆的聚合物组分免受磨损和/或侵蚀。

公开(公告)号：US20160273451A1

公开(公告)日：2016-09-22

申请号：US15032517

申请日：2014-10-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Colin J. Kling ,  Charles W. Brown

IPC: F02C7/04

CPC classification number: F02C7/04 ,  B64C11/14 ,  F05D2230/72 ,  F05D2250/73 ,  F05D2300/43 ,  F05D2300/433 ,  F05D2300/436

Abstract: The present disclosure relates generally to a nosecap for a gas turbine engine. The nosecap may be injection molded in an embodiment. The nosecap may have bolt holes surrounded by bolt pockets that are asymmetric about a plane passing through a geometric center of the nosecap and passing through and dividing the bolt hole in an embodiment.

Abstract translation: 本公开总体上涉及燃气涡轮发动机的喷嘴。 在一个实施例中，可以注射成型。 螺栓孔可以具有螺栓孔，螺栓孔围绕穿过螺栓孔的几何中心的平面不对称，并且在一个实施例中通过并分隔螺栓孔。

公开(公告)号：US09353685B2

公开(公告)日：2016-05-31

申请号：US13725359

申请日：2012-12-21

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  James J. McPhail ,  Matthew R. Rader

IPC: B64C11/14 ,  F02C7/05

CPC classification number: F02C7/05 ,  B64C11/14

Abstract: An assembly for a turbine engine including a nosecone that extends along an axis between a tip end and a second end. The nosecone includes a base region and a deformation region configured integral with the base region. The base region is arranged axially between the deformation region and the second end. The deformation region is adapted to deform relative to the base region upon impact of an object, and includes a stress concentrator.

Abstract translation: 一种用于涡轮发动机的组件，其包括沿尖端和第二端之间的轴线延伸的鼻锥体。 鼻锥包括基部区域和与基部区域一体形成的变形区域。 基部区域轴向地布置在变形区域和第二端部之间。 变形区域适于在物体撞击时相对于基底区域变形，并且包括应力集中器。

公开(公告)号：US11519291B2

公开(公告)日：2022-12-06

申请号：US15868289

申请日：2018-01-11

Applicant: United Technologies Corporation

Inventor： Colin J. Kling

IPC: F01D21/04 ,  F01D25/24 ,  B32B3/08 ,  B32B1/08 ,  B32B3/28 ,  B32B5/26 ,  B29C70/24 ,  B29C70/22 ,  B29D99/00 ,  B29C70/70 ,  D04C1/06 ,  B29C70/72

Abstract: A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.

公开(公告)号：US10533450B2

公开(公告)日：2020-01-14

申请号：US15797178

申请日：2017-10-30

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  Mark W. Costa

IPC: F01D21/04 ,  F01D25/24 ,  B29C53/56 ,  B29C63/34

Abstract: A gas turbine engine is provided. The gas turbine engine comprising: a fan section having a fan; and a containment zone encircling the fan, the containment zone comprising: a ballistic liner composed of a plurality of ring segments located radially outward of the fan; wherein each of the plurality of ring segments include two opposing circumferential ends, and wherein the plurality of ring segments are arranged circumferentially around the fan section and the circumferential ends of each of the plurality of ring segments meet at joints to form the ballistic liner.

公开(公告)号：US10472049B2

公开(公告)日：2019-11-12

申请号：US15030787

申请日：2014-05-23

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Scot A. Webb ,  James J. McPhail

IPC: B64C11/14 ,  F02C3/04

Abstract: A fan assembly of a gas turbine engine, a method for fabricating a fan assembly for a gas turbine engine, and a gas turbine engine are disclosed. The fan assembly of the gas turbine engine may include a spinner section, a fan hub section aft of the spinner section, and a joint therebetween. The fan assembly may further include a support ring for internally supporting the spinner, the support ring including a first portion facing the fan hub and a second portion connected to the spinner at the joint, wherein the connection between the second portion and the joint is a bonded connection.

公开(公告)号：US20190085856A1

公开(公告)日：2019-03-21

申请号：US15707165

申请日：2017-09-18

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier

IPC: F04D29/02 ,  F01D21/04 ,  F04D29/52 ,  F02C3/04 ,  B32B15/092

Abstract: A hybrid composite-metallic containment system may comprise a first composite layer, a first metallic layer, a second composite layer and a resin. The hybrid composite-metallic containment system may further comprise a second metallic layer. The first composite layer may be proximate the first metallic layer and the second composite layer may be proximate the second metallic layer. The first metallic layer may comprise a perforation.