公开(公告)号：US10113559B2

公开(公告)日：2018-10-30

申请号：US14850438

申请日：2015-09-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Colin J. Kling ,  David A. Topol

IPC: F04D29/52 ,  F01D21/04 ,  F02C7/045 ,  F01D5/02 ,  F02C3/04 ,  F04D29/32

Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.

公开(公告)号：US20160160863A1

公开(公告)日：2016-06-09

申请号：US14903996

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F04D19/00 ,  F04D29/54 ,  F01D25/24 ,  F01D5/28 ,  F01D5/26 ,  F01D25/02 ,  F04D29/38 ,  F01D9/04

CPC classification number: F04D19/002 ,  B32B1/00 ,  B32B1/08 ,  B32B27/281 ,  B32B27/285 ,  B32B27/34 ,  B32B27/36 ,  B32B2255/10 ,  B32B2255/205 ,  B32B2262/101 ,  B32B2262/103 ,  B32B2262/106 ,  B32B2270/00 ,  B32B2307/554 ,  F01D5/147 ,  F01D5/26 ,  F01D5/282 ,  F01D5/286 ,  F01D9/041 ,  F01D25/02 ,  F01D25/24 ,  F04D29/388 ,  F04D29/541 ,  F05D2220/32 ,  F05D2230/90 ,  F05D2240/00 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/96 ,  F05D2300/10 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

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.

Abstract translation: 公开了用于制造轻质电镀聚合物燃气涡轮发动机部件的电镀聚合物燃气涡轮发动机部件和方法。 这些部件包括镀有一个或多个金属层的聚合物基材。 聚合物基材的聚合材料可以用可以包括碳，金属或玻璃的材料在结构上加强。 聚合物基底还可以包括多个层以形成复合铺层结构。

公开(公告)号：US20160032831A1

公开(公告)日：2016-02-04

申请号：US14693488

申请日：2015-04-22

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier

IPC: F02C7/04 ,  B29C43/02 ,  F02C3/04

CPC classification number: F02C7/04 ,  B29C43/021 ,  B29C2043/026 ,  B29K2101/00 ,  B29L2031/7504 ,  B64C11/14 ,  F02C3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2240/20 ,  F05D2240/35 ,  F05D2300/43 ,  Y02T50/671

Abstract: A spinner for a fan assembly of a gas turbine engine, a method of fabricating a spinner for a fan assembly of a gas turbine engine, and a gas turbine engine are disclosed. The fan section may include a nosecap. The spinner may include a forward end, an aft end, and a return flange associated with the forward end. The return flange may include a forward flange extending forward towards the nosecap and an aft flange extending aft towards the aft end.

Abstract translation: 公开了一种用于燃气涡轮发动机的风扇组件的旋转器，制造用于燃气涡轮发动机的风扇组件的旋转器和燃气涡轮发动机的方法。 风扇部分可以包括nosecap。 旋转器可以包括前端，后端和与前端相关联的返回凸缘。 返回凸缘可以包括向前朝向鼻尖延伸的前凸缘和向后端向后延伸的后凸缘。

公开(公告)号：US20140255202A1

公开(公告)日：2014-09-11

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

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：US11267576B2

公开(公告)日：2022-03-08

申请号：US14903987

申请日：2014-07-09

Applicant: United Technologies Corporation

Inventor： James T. Roach ,  Colin J. Kling ,  Grant O. Cook, III ,  James J. McPhail ,  Shari L. Bugaj ,  James F. O'Brien ,  Majidullah Dehlavi ,  Scott A. Smith ,  Matthew R. Rader ,  Matthew A. Turner ,  JinQuan Xu

IPC: B64D29/00 ,  B29D22/00 ,  F02K3/04 ,  F01D5/02 ,  F01D25/28

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：US11156126B2

公开(公告)日：2021-10-26

申请号：US16369376

申请日：2019-03-29

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier

IPC: F01D25/24 ,  B29C70/22 ,  B29C70/32 ,  B29L31/00

Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.

公开(公告)号：US10935046B2

公开(公告)日：2021-03-02

申请号：US15957432

申请日：2018-04-19

Applicant: United Technologies Corporation

Inventor： David R. Lyders ,  Colin J. Kling

IPC: F01D25/28 ,  F04D29/52 ,  B32B5/02 ,  B32B5/26 ,  B32B7/12 ,  B32B15/14 ,  F04D29/02

Abstract: A gas turbine engine fan case may comprise a plurality of wound layers that form a laminate and have a nominal radial fan case thickness, where the laminate includes a plurality of discrete fan case radial locations comprising a plurality of radially stacked composite plies that form a radial integral build up in comparison to the nominal radial fan case thickness.

公开(公告)号：US20200025034A1

公开(公告)日：2020-01-23

申请号：US16369376

申请日：2019-03-29

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier

IPC: F01D25/24 ,  B29C70/22 ,  B29C70/32

Abstract: A fan case for a gas turbine engine includes an annular liner and an annular case body. The liner has a plurality of liner fiber layers. The case body surrounds the liner. The case body includes a plurality of first and second fiber layers. The first fiber layers extend axially beyond the second fiber layers in axially forward and aft directions and the second fiber layers are interleaved with the first fiber layers. The first fiber layers each have a first fiber architecture and the second fiber layers each have a second, different fiber architecture.

公开(公告)号：US10214824B2

公开(公告)日：2019-02-26

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: B21D39/00 ,  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: 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.

公开(公告)号：US10132174B2

公开(公告)日：2018-11-20

申请号：US14685030

申请日：2015-04-13

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Thomas J. Robertson ,  Carney R. Anderson ,  James J. McPhail

IPC: F01D5/32 ,  F01D5/28 ,  F01D5/30 ,  F02K7/06

Abstract: The present disclosure provides devices related to aircraft engine fan assemblies and blade lock retainers. In various embodiments, a blade lock retainer is formed from sheet metal and comprises an annular ring portion, an outer retainer tab portion, and an inner tab portion. In various embodiments, the outer retainer tab portion is disposed on an outer circumference of the annular ring portion, oriented substantially perpendicular to the annular ring portion, and extends in an aft direction from the annular ring portion. In various embodiments, the inner retainer tab portion is disposed on an inner circumference of the annular ring portion and radially aligned with the outer retainer tab portion, oriented substantially perpendicular to the annular ring portion, and extends in a forward direction from the annular ring portion.