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公开(公告)号：US20180066607A1
公开(公告)日：2018-03-08
申请号：US15258820
申请日：2016-09-07
Applicant: United Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Matthew Exner
Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a retaining member having a first end and a second end and defining a first aperture and a cavity, wherein the pivot is configured to extend at least partially into the first aperture and the cavity is configured to accommodate a portion of the link arm, and wherein the retaining member comprises an attachment aperture located at the first end and a lip extending from the retaining member at the second end, the attachment aperture configured to receive a fastener and the lip configured to be placed under a distal layer of an inner fixed structure (IFS).
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公开(公告)号：US20160025038A1
公开(公告)日：2016-01-28
申请号：US14770195
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott
CPC classification number: F02K1/72 , B64D29/06 , B64D33/04 , F01D5/02 , F01D15/12 , F01D17/105 , F01D25/24 , F02K1/70 , F05D2220/36 , F05D2260/40311
Abstract: A geared turbofan engine includes a fan, a low pressure turbine, a geared architecture, and a nacelle. The fan and low pressure turbine are capable of rotation about an axial centerline of the gas turbine engine. The geared architecture connects the fan to be driven by the low pressure turbine. The nacelle is disposed circumferentially around the fan and defines a portion of a bypass flow duct. The nacelle includes a thrust reverser assembly with one or more doors that pivot to block at least a portion of the bypass flow duct in a deployed position.
Abstract translation: 齿轮涡扇发动机包括风扇，低压涡轮机，齿轮架构和机舱。 风扇和低压涡轮机能够围绕燃气涡轮发动机的轴向中心线旋转。 齿轮架构将风扇连接到低压涡轮机驱动。 机舱围绕风扇周向设置并限定旁路流动管道的一部分。 机舱包括具有一个或多个门的推力反向器组件，其枢转以在展开位置阻挡旁路流动管道的至少一部分。
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公开(公告)号：US20150016965A1
公开(公告)日：2015-01-15
申请号：US14320829
申请日：2014-07-01
Applicant: United Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Matthew Exner
CPC classification number: F02K1/763 , F02K1/72 , Y02T50/672
Abstract: A flowpath channel has a blade pivotally connected along a longitudinal axis thereof, at opposing top and bottom ends thereof, to respective top and bottom portions of the flowpath channel. The chord axis of the blade, between leading and trailing edges thereof, is capable of pivoting parallel to and skewed from the flowpath. The top end of the blade and an attachment structure secured to the flowpath channel each include a race. A bearing is disposed therebetween, and the blade is rotatable about the longitudinal axis.
Abstract translation: 流路通道具有沿着其纵向轴线在其相对的顶部和底端处枢转地连接到流路通道的相应顶部和底部的叶片。 在叶片的前缘和后缘之间的叶片的弦线能够平行于和流动的方向转动。 叶片的顶端和固定到流道通道的附接结构各自包括一个座圈。 轴承设置在它们之间，并且叶片能够围绕纵向轴线旋转。
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公开(公告)号：US20200256253A1
公开(公告)日：2020-08-13
申请号：US16271213
申请日：2019-02-08
Applicant: United Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Federico Papa
IPC: F02C7/24
Abstract: A gas turbine engine system includes a gas turbine engine, a temperature-sensitive component, and a thermal protection structure. The gas turbine engine has an engine core that generates heat while operational and for a period after operation. The temperature-sensitive component is disposed at a component location proximate the engine core. The thermal protection structure is interposed between the temperature-sensitive component and the gas turbine-engine, and includes a phase change material (PCM) layer disposed to absorb a transient heat spike from the engine core.
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公开(公告)号：US20180065754A1
公开(公告)日：2018-03-08
申请号：US15258927
申请日：2016-09-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott , Matthew Exner
CPC classification number: B64D29/06 , B64D27/16 , F01D25/24 , F02K1/56 , F02K1/72 , F02K1/763 , F05D2220/323 , F05D2230/60 , F05D2260/50 , F16C11/045 , F16C2360/23 , Y02T50/672
Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a base member, and a retaining member at least partially defining a first aperture and a cavity. The pivot is configured to extend at least partially into the first aperture. The cavity is configured to accommodate a portion of the link arm.
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Patent Agency Ranking
公开(公告)号：US20180051715A1
公开(公告)日：2018-02-22
申请号：US15239869
申请日：2016-08-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott
Abstract: A fan duct seal for a gas turbine engine has at least one seal body with a hollow center. A first opening is formed in the seal body that is in fluid communication with the hollow center. The first opening is configured to receive fan air flow. A second opening is formed in the seal body that is in fluid communication with the hollow center such that cooling flow enters the first opening, moves through the seal body and exits from the second opening. A fan duct for a gas turbine engine and a method of cooling a fan duct seal assembly are also disclosed.
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公开(公告)号：US20150369078A1
公开(公告)日：2015-12-24
申请号：US14765037
申请日：2014-02-27
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott , Constantino V. Loffredo
CPC classification number: F01D17/14 , F01D9/04 , F01D25/24 , F02K1/09 , F02K1/1261 , F02K1/15 , F02K1/70 , F02K1/72 , F02K1/763 , F02K3/075 , F05D2220/32 , F05D2270/62 , F05D2270/64 , F05D2270/65
Abstract: A gas turbine engine includes a nacelle assembly having a core nacelle defined about an engine axis and a fan nacelle assembly mounted at least partially around the core nacelle to define a fan bypass flow path. The fan nacelle assembly includes a fan duct nacelle section and a fan nozzle nacelle section moveable relative to the fan duct nacelle section. A thrust reverser system includes a plurality of pivot doors movable relative to the fan nacelle assembly between stowed and deployed positions. A variable area fan nozzle is in communication with the fan bypass flow path. A first actuator is mounted to the fan duct nacelle section to actuate the pivot door thrust reverser system, and a second actuator is mounted to the fan duct nacelle section to move the fan nozzle nacelle section relative to the fan duct nacelle section to vary a fan nozzle exit area.
Abstract translation: 燃气涡轮发动机包括具有围绕发动机轴线限定的核心机舱的机舱组件和至少部分地安装在核心机舱周围的风扇机舱组件，以限定风扇旁路流动路径。 风扇机舱组件包括风扇管道机舱部分和相对于风扇管道机舱部分可移动的风扇喷嘴机舱部分。 推力反向器系统包括在收起和展开位置之间可相对于风扇机舱组件移动的多个枢轴门。 可变区域风扇喷嘴与风扇旁路流路连通。 第一致动器安装到风扇管道机舱部分以致动枢转门推力反向器系统，并且第二致动器安装到风扇管道机舱部分以相对于风扇管道机舱部分移动风扇喷嘴机舱部分以改变风扇 喷嘴出口区域。
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公开(公告)号：US10814993B2
公开(公告)日：2020-10-27
申请号：US15681987
申请日：2017-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott , Frederick M. Schwarz
Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.
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公开(公告)号：US10563671B2
公开(公告)日：2020-02-18
申请号：US15239869
申请日：2016-08-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Nigel David Sawyers-Abbott
Abstract: A fan duct seal for a gas turbine engine has at least one seal body with a hollow center. A first opening is formed in the seal body that is in fluid communication with the hollow center. The first opening is configured to receive fan air flow. A second opening is formed in the seal body that is in fluid communication with the hollow center such that cooling flow enters the first opening, moves through the seal body and exits from the second opening. A fan duct for a gas turbine engine and a method of cooling a fan duct seal assembly are also disclosed.
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公开(公告)号：US10480453B2
公开(公告)日：2019-11-19
申请号：US15258820
申请日：2016-09-07
Applicant: United Technologies Corporation
Inventor： Nigel David Sawyers-Abbott , Matthew Exner
Abstract: A linkage system for a nacelle may comprise a pivot configured to extend through a second aperture disposed in a link arm, a retaining member having a first end and a second end and defining a first aperture and a cavity, wherein the pivot is configured to extend at least partially into the first aperture and the cavity is configured to accommodate a portion of the link arm, and wherein the retaining member comprises an attachment aperture located at the first end and a lip extending from the retaining member at the second end, the attachment aperture configured to receive a fastener and the lip configured to be placed under a distal layer of an inner fixed structure (IFS).
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