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公开(公告)号：EP3564487A1
公开(公告)日：2019-11-06
申请号：EP19172045.7
申请日：2019-04-30
Applicant: United Technologies Corporation
Inventor： FOSTER, Larry , RIEHL, John D.
IPC: F01D5/28
Abstract: An airfoil (160) for a gas turbine engine includes, an airfoil section (164) extending between a leading edge (L/E) and a trailing edge (T/E) in a chordwise direction and extending between a tip and a root section (166,162) in a spanwise direction (R). A composite core (168;168") defines the root section (162) and a portion of the airfoil section (164). First and second skins (170,172) extend along opposed sides of the composite core (168;168").
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公开(公告)号：EP3428399A1
公开(公告)日：2019-01-16
申请号：EP18192296.4
申请日：2013-04-29
Applicant: United Technologies Corporation
Inventor： MURON, Stephen P. , FOSTER, Larry
Abstract: A fan blade having a body with a dovetail and an airfoil extending radially outwardly. The airfoil includes a pair of skins spaced to form an internal core, which define a pressure side and a suction side, and extending from a radially inner end to a radially outer tip. The core receives a plurality of braided tubes, with the tubes extending with at least a component in a radially outward direction. A fan and an engine are also described.
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13.发明公开
公开(公告)号：EP3159157A1
公开(公告)日：2017-04-26
申请号：EP16194547.2
申请日：2016-10-19
Applicant: United Technologies Corporation
Inventor： NAIK, Rajiv A. , RIEHL, John D. , FOSTER, Larry
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 (24) including a multiple of composite layers (30) impregnated with a polymer matrix (40); and a nanotube material (50) that facilitates a mechanical interlock between at least two of the multiple of composite layers (30). A method of manufacturing a composite article (24) including a multiple of composite layers (30) within a polymer matrix (40); and distributing a nanotube material (50) between at least two of the multiple of composite layers (30) to facilitate a mechanical interlock between the at least two of the multiple of composite layers (30) adjacent an otherwise relatively low strength interlaminar interface region of the composite article (24).
Abstract translation: 包括多个浸渍有聚合物基体（40）的复合层（30）的复合制品（24）; 和促进所述多个复合层（30）中的至少两个之间的机械互锁的纳米管材料（50）。 一种制造包括聚合物基体（40）内的多个复合层（30）的复合制品（24）的方法; 以及在所述多个复合层（30）中的至少两个之间分布纳米管材料（50）以促进所述多个复合层（30）中的所述至少两个之间的机械互锁，所述复合层（30）中的其他相对低强度层间界面区域 复合制品（24）。
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Patent Agency Ranking
公开(公告)号：EP3480429A1
公开(公告)日：2019-05-08
申请号：EP18204095.6
申请日：2018-11-02
Applicant: United Technologies Corporation
Inventor： FOSTER, Larry
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：EP3282088A1
公开(公告)日：2018-02-14
申请号：EP17185368.2
申请日：2017-08-08
Applicant: United Technologies Corporation
Inventor： FOSTER, Larry , HERTEL, Christopher J.
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 (10) includes a blade body (48), a blade cover (56) secured to the blade body and an adhesive layer (58) 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.
Abstract translation: 用于燃气涡轮发动机（10）的风扇叶片组件包括叶片主体（48），固定到叶片主体的叶片盖（56）和将叶片盖固定到叶片主体的粘合剂层（58），粘合剂 层被配置成设置在环境温度下。 形成用于燃气涡轮发动机的风扇叶片组件的方法包括：形成叶片主体;形成与叶片主体分离的叶片盖;以及经由位于叶片主体和叶片之间的粘合层将叶片盖粘附至叶片主体 覆盖层，所述粘合剂层被构造成设定在环境温度下。
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16.发明公开FAN, GAS TURBINE ENGINE WITH A FAN, AND METHOD FOR CREATING A GAS TURBINE ENGINE FAN 审中-公开风扇，具有风扇的燃气涡轮发动机以及用于创建燃气涡轮发动机风扇的方法
公开(公告)号：EP3282087A1
公开(公告)日：2018-02-14
申请号：EP17185373.2
申请日：2017-08-08
Applicant: United Technologies Corporation
Inventor： FOSTER, Larry , KLEIN, Myron L.
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. A corresponding method of creating a gas turbine engine is also provided.
Abstract translation: 燃气涡轮发动机包括安装第一组叶片和第二组叶片的风扇。 第一组刀片和第二组刀片共享轮廓形状。 第一组叶片具有第一层压体组合物，第二组叶片具有不同于第一层压体组合物的第二层压体组合物。 第一组叶片的振动模式的频率偏离第二组叶片的振动模式的频率。 还提供了一种创建燃气涡轮发动机的相应方法。
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公开(公告)号：EP3044415A1
公开(公告)日：2016-07-20
申请号：EP14842050.8
申请日：2014-08-12
Applicant: United Technologies Corporation
Inventor： FOSTER, Larry
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：EP2867494A1
公开(公告)日：2015-05-06
申请号：EP13813106.5
申请日：2013-06-25
Applicant: United Technologies Corporation
Inventor： FINNIGAN, Peter , VOLETI, Sreenivasa R. , FOSTER, Larry , LUSSIER, Darin S. , AKSEL, Gulperi
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.
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