公开(公告)号：US20160160681A1

公开(公告)日：2016-06-09

申请号：US14903988

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Roach ,  Charles R. Watson ,  Grant O. Cook ,  Frederick M. Schwarz ,  Shari L. Bugaj ,  Kevin W. Schlichting

IPC: F01D25/00 ,  F02K1/54 ,  F04D29/02 ,  F01D25/24 ,  F04D29/52

CPC classification number: F01D25/005 ,  B64D29/00 ,  B64D2045/009 ,  C23C18/1641 ,  C23C18/31 ,  C25D1/00 ,  C25D5/56 ,  C25D7/00 ,  F01D5/282 ,  F01D5/3092 ,  F01D9/041 ,  F01D25/24 ,  F01D25/30 ,  F02C7/04 ,  F02K1/54 ,  F04D29/023 ,  F04D29/321 ,  F04D29/322 ,  F04D29/522 ,  F04D29/542 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/00 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/60 ,  F05D2250/283 ,  F05D2260/96 ,  F05D2300/10 ,  F05D2300/40 ,  F05D2300/43 ,  F05D2300/603 ,  F16C3/02 ,  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：US20180195402A1

公开(公告)日：2018-07-12

申请号：US15116713

申请日：2014-12-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  Shari L. Bugaj

IPC: F01D11/00 ,  F02K3/06 ,  F04D29/32 ,  F01D25/00

CPC classification number: F01D11/008 ,  F01D25/005 ,  F02K3/06 ,  F04D29/329 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2230/31 ,  F05D2230/80 ,  F05D2240/80 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/603 ,  Y02T50/672

Abstract: A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path between the plurality of airfoils. The platform may be configured to be disposable during a life of the gas turbine engine.

公开(公告)号：US10012150B2

公开(公告)日：2018-07-03

申请号：US15233142

申请日：2016-08-10

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F02C7/36 ,  F02K1/06 ,  F02K3/06 ,  F01D5/28 ,  F01D5/14 ,  F01D15/12 ,  F04D29/02 ,  F04D29/053 ,  F04D29/32 ,  F04D29/38 ,  F04D29/52 ,  F04D29/56

CPC classification number: F04D29/023 ,  F01D5/147 ,  F01D5/282 ,  F01D15/12 ,  F02C3/06 ,  F02C7/36 ,  F02K1/06 ,  F02K3/06 ,  F04D29/053 ,  F04D29/325 ,  F04D29/388 ,  F04D29/526 ,  F04D29/563 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2300/603 ,  Y02T50/672

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.

公开(公告)号：US20160258319A1

公开(公告)日：2016-09-08

申请号：US14546752

申请日：2014-11-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Andrew G. Alarcon ,  Shari L. Bugaj

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D9/041 ,  F05D2300/2102 ,  F05D2300/224 ,  F05D2300/434 ,  F05D2300/436 ,  F05D2300/6031 ,  F05D2300/614 ,  Y02T50/672

Abstract: The present disclosure relates generally to the field of guide vanes for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber composite inlet guide vane for a gas turbine engine.

Abstract translation: 本公开一般涉及用于燃气涡轮发动机的导向叶片领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩短切纤维复合材料入口引导叶片。

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：US20150013480A1

公开(公告)日：2015-01-15

申请号：US14331771

申请日：2014-07-15

Applicant: United Technologies Corporation

Inventor： Shari L. Bugaj ,  Wendell V. Twelves, JR. ,  Grant O. Cook, III

IPC: G01D11/00 ,  C23C18/31 ,  C25D5/48

CPC classification number: C25D5/48 ,  C23C18/1605 ,  C23C18/1608 ,  C23C18/1653 ,  C23C18/30 ,  C25D5/02 ,  C25D5/022 ,  C25D5/10 ,  C25D7/00 ,  G01D5/2086

Abstract: A component comprises a non-metallic core having an outer surface, a first catalyst deposited onto at least a first portion of the outer surface of the non-metallic core, a second catalyst deposited onto at least a second portion of the outer surface of the non-metallic core, an electrical interface, and a metallic coating. The electrical interface is plated onto the first catalyst, and includes a first interface layer electroless plated onto the first catalyst. The metallic coating is plated onto the second catalyst.

Abstract translation: 组件包括具有外表面的非金属芯，沉积在非金属芯的外表面的至少第一部分上的第一催化剂，沉积在第二催化剂的外表面的至少第二部分上的第二催化剂 非金属芯，电接口和金属涂层。 电接口被电镀到第一催化剂上，并且包括无电镀在第一催化剂上的第一界面层。 将金属涂层镀在第二催化剂上。

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：US10533435B2

公开(公告)日：2020-01-14

申请号：US15039880

申请日：2014-11-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Charles W. Brown ,  Andrew G. Alarcon ,  Shari L. Bugaj ,  Charles R. Watson

IPC: F01D5/30 ,  F01D11/00 ,  F01D5/14

Abstract: In a featured embodiment, a fan rotor includes a platform. Clevises extend radially inwardly of the platform. Each clevis has an aperture. A hub has hub lugs positioned intermediate spaced ends of the clevises, and apertures. A pin extends through the apertures in the hub and the clevises to connect the platform to the hub. The apertures in the clevises are formed to have an inner surface for supporting the pin. A method of forming a fan blade platform is also disclosed.

公开(公告)号：US10472048B2

公开(公告)日：2019-11-12

申请号：US14930760

申请日：2015-11-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Colin J. Kling ,  Shari L. Bugaj ,  James T. Roach

IPC: B64C11/14 ,  F02C7/04 ,  B29C70/46 ,  B29C70/14 ,  B29K101/10 ,  B29K105/12 ,  B29K307/04 ,  B29L31/00

Abstract: A spinner for a gas turbine engine is disclosed. The spinner may include a body extending between a first and second end comprised of a cured chopped unidirectional fiber pre-impregnated material. The body may have a generally conical shape and may further be plated with a metal or metal alloy.

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.