公开(公告)号：US10443617B2

公开(公告)日：2019-10-15

申请号：US15075245

申请日：2016-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peter Finnigan ,  Sreenivasa R. Voleti ,  Larry Foster ,  Darin S. Lussier ,  Gulperi Aksel

IPC: B32B1/08 ,  F04D29/52 ,  F01D21/04 ,  B29C70/24

Abstract: A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.

公开(公告)号：US20180038386A1

公开(公告)日：2018-02-08

申请号：US15230659

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  Christopher J. Hertel

IPC: F04D29/38 ,  F04D29/32 ,  F04D29/02

CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/282 ,  F01D25/005 ,  F02K3/06 ,  F04D29/023 ,  F04D29/324 ,  F04D29/325 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2300/437 ,  F05D2300/44 ,  F05D2300/603

Abstract: A fan blade assembly for a gas turbine engine includes a blade body, a blade cover secured to the blade body and an adhesive layer to secure the blade cover to the blade body, the adhesive layer configured to set at ambient temperature. A method of forming a fan blade assembly for a gas turbine engine includes forming a blade body, forming a blade cover separate from the blade body, and adhering the blade cover to the blade body via an adhesive layer located between the blade body and the blade cover, the adhesive layer configured to set at ambient temperature.

公开(公告)号：US11203936B2

公开(公告)日：2021-12-21

申请号：US16251537

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Eric W. Malmborg ,  Larry Foster

IPC: F01D5/14 ,  F16B5/06 ,  F16B13/02 ,  F16B13/00

Abstract: An airfoil includes a body that has rib nodes that each define a node cavity therein. A cover panel is carried on the body over the rib nodes. The cover panel includes tabs that project into the node cavities. Plugs are disposed in the node cavities and pinch the tabs against the node cavities to lock the cover panel on the body.

公开(公告)号：US10823190B2

公开(公告)日：2020-11-03

申请号：US14597692

申请日：2015-01-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael A. Weisse ,  Kwan Hui ,  Larry Foster

IPC: F04D29/32 ,  F04D19/00 ,  B32B37/18 ,  B32B38/00 ,  F01D5/14 ,  F01D5/28

Abstract: A fan blade having an opening on one side exposing one or more cavities, and a composite cover that fits over the opening, is provided. The composite cover has a variable thickness resulting from the layering of cover plies having different shapes, and is designed to achieve a lightweight fan blade having an optimal level of stiffness.

公开(公告)号：US09896941B2

公开(公告)日：2018-02-20

申请号：US14597812

申请日：2015-01-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kwan Hui ,  Michael A. Weisse ,  Larry Foster

IPC: F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F04D29/32

CPC classification number: F01D5/147 ,  F01D5/141 ,  F01D5/18 ,  F01D5/282 ,  F04D29/324 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/51 ,  F05D2230/60 ,  F05D2250/292 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673 ,  Y10T29/49337

Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening exposing at least one cavity to reduce the weight of the fan blade. The cover overlays the opening and includes a leading portion and a trailing portion that are tapered in the direction of the cover leading edge and cover trailing edge.

公开(公告)号：US20160281738A1

公开(公告)日：2016-09-29

申请号：US15075245

申请日：2016-03-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peter Finnigan ,  Sreenivasa R. Voleti ,  Larry Foster ,  Darin S. Lussier ,  Gulperi Aksel

IPC: F04D29/52 ,  F01D21/04

CPC classification number: F04D29/526 ,  B29C70/24 ,  F01D21/045 ,  F05D2220/32 ,  F05D2300/224 ,  F05D2300/6012 ,  F05D2300/6031 ,  F05D2300/6034 ,  F05D2300/614 ,  Y02T50/672

Abstract: A fan containment case for a gas turbine engine includes a first inner layer and a second layer outside the first inner layer, where the second layer is made of a first material having a first fabric architecture. The fan containment case also includes a third layer outside of the second layer, where the third layer is made of a second material having a second fabric architecture, and at least one of the first material and the first fabric architecture of the second layer is different from the second material and the second architecture, respectively, of the third layer. A fourth outer layer is located outside of the third layer.

Abstract translation: 用于燃气涡轮发动机的风扇容纳箱包括第一内层和第一内层外的第二层，其中第二层由具有第一织物结构的第一材料制成。 风扇容纳壳体还包括在第二层外侧的第三层，其中第三层由具有第二织物结构的第二材料制成，并且第二层的第一材料和第一织物结构中的至少一个是不同的 分别来自第三层的第二材料和第二结构。 第四外层位于第三层的外侧。

公开(公告)号：US20160201480A1

公开(公告)日：2016-07-14

申请号：US14913709

申请日：2014-08-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Larry Foster

IPC: F01D5/28 ,  F04D29/38 ,  F04D29/32 ,  F01D9/04 ,  F01D15/12

CPC classification number: F04D29/023 ,  B29D99/0014 ,  B29D99/0028 ,  B29L2031/08 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D15/12 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2230/60 ,  F05D2240/303 ,  F05D2250/11 ,  F05D2250/23 ,  F05D2300/6012 ,  F05D2300/603 ,  F05D2300/6034 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, a main body extending between a leading edge and a trailing edge separated in a chordwise direction and extending between a tip and a root in a spanwise direction. The main body defines a suction side and a pressure side separated in a thickness direction and a plurality of channels extending inwardly from at least one of said suction and pressure sides. A composite cover is attached to the main body. The composite cover includes a plurality of stiffeners each received within one of the channels. A cover skin is adjacent the stiffeners, and an over-wrap surrounds the stiffeners and the cover skin.

Abstract translation: 根据本公开的示例性方面的翼型件包括主体，其在沿翼弦方向分离并在翼展方向上在尖端和根部之间延伸的前缘和后缘之间延伸。 主体限定了沿厚度方向分离的吸力侧和压力侧以及从所述吸入侧和压力侧中的至少一个向内延伸的多个通道。 复合盖附接到主体。 复合盖包括多个加强件，每个加强件都在一个通道内容纳。 覆盖皮肤与加强件相邻，并且覆盖物包围加强件和覆盖物皮肤。

公开(公告)号：US20190331127A1

公开(公告)日：2019-10-31

申请号：US15966109

申请日：2018-04-30

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  John D. Riehl

IPC: F04D29/38 ,  F04D29/02 ,  F04D29/32 ,  F02K3/06 ,  B32B5/02 ,  B32B27/12 ,  B32B27/38

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip and a root section in a spanwise direction. A composite core defines the root section and a portion of the airfoil section. First and second skins extend along opposed sides of the composite core. 12. A method of forming a composite airfoil is also disclosed.

公开(公告)号：US10260374B2

公开(公告)日：2019-04-16

申请号：US14875627

申请日：2015-10-05

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  Darin S. Lussier

IPC: F01D25/24 ,  B32B5/08 ,  B32B1/08 ,  D04C1/00 ,  F04D29/40 ,  F04D29/02 ,  F04D29/52 ,  B32B5/26 ,  B65H81/02 ,  F01D21/04 ,  F02K1/78 ,  F02C7/04 ,  B29C70/22

Abstract: A preform sheet for a composite component comprises a body section and a flange section. The preform body section includes a plurality of axial tows braided with at least a plurality of first bias tows and a plurality of second bias tows. The preform flange section includes a first braided flange layer and a second braided flange layer. The first braided flange layer is defined by the first and second braided bias tows of the preform body section extending into the flange section. Neither the first nor second braided flange layers have axial tows.

公开(公告)号：US20180051705A1

公开(公告)日：2018-02-22

申请号：US15243066

申请日：2016-08-22

Applicant: United Technologies Corporation

Inventor： Larry Foster ,  Rajiv A. Naik ,  John D. Riehl

IPC: F04D29/02 ,  F04D29/38 ,  F04D29/52 ,  F04D29/54

CPC classification number: F04D29/023 ,  B29C70/24 ,  B29L2031/08 ,  F01D5/147 ,  F01D5/282 ,  F01D5/288 ,  F01D9/041 ,  F01D25/162 ,  F01D25/24 ,  F04D29/38 ,  F04D29/522 ,  F04D29/542 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2240/12 ,  F05D2240/14 ,  F05D2240/30 ,  F05D2300/6034

Abstract: A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction.