公开(公告)号：US20160159488A1

公开(公告)日：2016-06-09

申请号：US14903987

申请日：2014-07-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James T. Roach ,  Colin J. Kling ,  Grant O. Cook ,  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 ,  F01D25/28 ,  F01D5/02

CPC classification number: B64D29/00 ,  B29D22/00 ,  F01D5/02 ,  F01D25/28 ,  F02K3/04 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2300/10 ,  F05D2300/43 ,  F05D2300/603 ,  Y02T50/672

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：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：US20150315922A1

公开(公告)日：2015-11-05

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: F01D9/02 ,  F01D5/12 ,  F01D5/02

CPC classification number: F01D9/02 ,  B64C11/14 ,  F01D5/02 ,  F01D5/12 ,  F02C7/04 ,  F05D2220/32 ,  F05D2300/10 ,  F05D2300/603 ,  F05D2300/6034 ,  Y02T50/672

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.

Abstract translation: 用于燃气涡轮发动机的旋转器包括用于在安装在燃气涡轮发动机中时限定气流路径的外壳。 内表面设置有多个腹板。 还公开了一种燃气涡轮发动机和用于燃气涡轮发动机的风扇部分。

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：US20160369812A1

公开(公告)日：2016-12-22

申请号：US15185573

申请日：2016-06-17

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  James F. O'Brien

IPC: F04D29/52 ,  F04D29/02 ,  F04D29/66

CPC classification number: F04D29/526 ,  B29C70/86 ,  B29C70/885 ,  F01D21/045 ,  F04D29/023 ,  F04D29/664 ,  F05D2300/224 ,  F05D2300/433 ,  F05D2300/603 ,  Y02T50/672

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

Abstract translation: 制造用于燃气涡轮发动机的风扇壳体的方法限定了包括外表面和内表面的金属环。 围绕金属环的外表面组装第一复合材料。 围绕第一复合材料组装第二复合材料。 第一复合材料和第二材料围绕工具中的金属环固化以形成第一子组件。 第一个子组件从工具中移除。 还公开了一种用于燃气涡轮发动机和燃气涡轮发动机的风扇壳体组件。

公开(公告)号：US11236765B2

公开(公告)日：2022-02-01

申请号：US16663479

申请日：2019-10-25

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  James F. O'Brien

IPC: F01D21/04 ,  F04D29/52 ,  F04D29/66 ,  F04D29/02 ,  B29C70/88 ,  F01D5/28 ,  B29C70/02 ,  B29C70/72 ,  F01D25/24 ,  B29C70/86

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

公开(公告)号：US20200056626A1

公开(公告)日：2020-02-20

申请号：US16663479

申请日：2019-10-25

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  James F. O'Brien

IPC: F04D29/52 ,  F04D29/02 ,  F04D29/66 ,  B29C70/86 ,  F01D25/24 ,  F01D21/04 ,  B29C70/72 ,  B29C70/02 ,  F01D5/28 ,  B29C70/88

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.

公开(公告)号：US10458433B2

公开(公告)日：2019-10-29

申请号：US15185573

申请日：2016-06-17

Applicant: United Technologies Corporation

Inventor： Colin J. Kling ,  Darin S. Lussier ,  James F. O'Brien

IPC: F04D29/52 ,  F04D29/66 ,  F04D29/02 ,  B29C70/72 ,  B29C70/02 ,  F01D21/04 ,  F01D5/28 ,  F01D25/24 ,  B29C70/86 ,  B29C70/88

Abstract: A method of fabricating a fan case for a gas turbine engine defines a metallic ring including an outer surface and an inner surface. A first composite material is assembled about the outer surface of the metallic ring. A second composite material is assembled about the first composite material. The first composite material and the second material are cured about the metallic ring within a tool to form a first subassembly. The first subassembly is removed from the tool. A fan case assembly for a gas turbine engine and a gas turbine engine are also disclosed.