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公开(公告)号：US20150198173A1
公开(公告)日：2015-07-16
申请号：US14597692
申请日：2015-01-15
Applicant: United Technologies Corporation
Inventor： Michael A. Weisse , Kwan Hui , Larry Foster
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.
Abstract translation: 提供了具有一侧露出一个或多个空腔的开口的风扇叶片和装配在开口上的复合盖。 复合盖具有由具有不同形状的覆盖层的层叠产生的可变厚度，并且被设计成实现具有最佳刚度水平的轻质风扇叶片。
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公开(公告)号：US11085456B2
公开(公告)日：2021-08-10
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 , F01D25/24 , F01D5/28 , F01D25/16 , F01D9/04 , B29C70/24 , F04D29/38 , F04D29/52 , F04D29/54 , F01D5/14 , B29L31/08
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.
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公开(公告)号：US20180243788A1
公开(公告)日：2018-08-30
申请号：US15964998
申请日：2018-04-27
Applicant: United Technologies Corporation
Inventor： Rajiv A. Naik , John D. Riehl , Larry Foster
CPC classification number: B05D3/12 , B29C70/081 , B32B7/08 , B32B27/08 , B32B2255/10 , B32B2255/20 , B32B2260/021 , B32B2260/046 , B32B2305/076
Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.
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公开(公告)号：US09987659B2
公开(公告)日：2018-06-05
申请号：US14886480
申请日：2015-10-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Rajiv A Naik , John D Riehl , Larry Foster
CPC classification number: B05D3/12 , B29C70/081 , B32B7/08 , B32B27/08 , B32B2255/10 , B32B2255/20 , B32B2260/021 , B32B2260/046 , B32B2305/076
Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.
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公开(公告)号：US11346363B2
公开(公告)日：2022-05-31
申请号：US15966109
申请日：2018-04-30
Applicant: United Technologies Corporation
Inventor： Larry Foster , John D. Riehl
IPC: F04D29/38 , B32B5/02 , B32B27/12 , B32B27/38 , F02K3/06 , F04D29/02 , F04D29/32 , B29C70/48 , B29K63/00 , B29K307/04 , B29L31/08
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.
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Patent Agency Ranking
公开(公告)号：US20200232329A1
公开(公告)日：2020-07-23
申请号：US16251537
申请日：2019-01-18
Applicant: United Technologies Corporation
Inventor： Eric W. Malmborg , Larry Foster
IPC: F01D5/14
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.
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公开(公告)号：US10717109B2
公开(公告)日：2020-07-21
申请号：US15964998
申请日：2018-04-27
Applicant: United Technologies Corporation
Inventor： Rajiv A. Naik , John D. Riehl , Larry Foster
Abstract: A composite article including a multiple of composite layers impregnated with a polymer matrix; and a nanotube material that facilitates a mechanical interlock between at least two of the multiple of composite layers. A method of manufacturing a composite article including a multiple of composite layers within a polymer matrix; and distributing a nanotube material between at least two of the multiple of composite layers to facilitate a mechanical interlock between the at least two of the multiple of composite layers adjacent an otherwise relatively low strength interlaminar interface region of the composite article.
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公开(公告)号：US20190136697A1
公开(公告)日：2019-05-09
申请号：US15803594
申请日：2017-11-03
Applicant: United Technologies Corporation
Inventor： Larry Foster
Abstract: An airfoil for a gas turbine engine includes a blade body, a leading edge sheath, and an energy absorbing insert. The blade body has a pressure side and a suction side that each between a forward portion and a trailing edge. The leading edge sheath has a leading edge portion that is spaced apart from the forward portion, a first arm that engages the pressure side, and a second arm that engages the suction side. A cavity is defined between the leading edge portion, the first arm, the second arm, and the forward portion. The energy absorbing insert is disposed within the cavity and improves the impact resistance of the airfoil.
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公开(公告)号：US09957972B2
公开(公告)日：2018-05-01
申请号：US14913709
申请日：2014-08-12
Applicant: United Technologies Corporation
Inventor： Larry Foster
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.
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公开(公告)号：US20180038382A1
公开(公告)日：2018-02-08
申请号：US15231058
申请日：2016-08-08
Applicant: United Technologies Corporation
Inventor： Larry Foster , Myron L. Klein
CPC classification number: F04D29/327 , F01D5/10 , F01D5/16 , F01D5/282 , F01D25/04 , F02C3/04 , F02K3/06 , F04D29/023 , F04D29/388 , F04D29/666 , F05D2220/36 , F05D2230/60 , F05D2240/35 , F05D2260/961 , F05D2300/603 , F05D2300/6034 , Y02T50/673
Abstract: A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.
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