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公开(公告)号：US11787127B2
公开(公告)日：2023-10-17
申请号：US16851750
申请日：2020-04-17
Applicant: Hutchinson
Inventor： Basile Guillaume , Jean-Christophe Rietsch , Kevin O'Brien Gaw , Thomas Patillaut
IPC: B29C70/02 , B29C43/14 , F02K1/64 , B29K63/00 , B29K79/00 , B29K105/12 , B29K307/04 , B29L31/30
CPC classification number: B29C70/021 , B29C43/146 , F02K1/64 , B29C2043/147 , B29C2793/0072 , B29C2793/0081 , B29K2063/00 , B29K2079/085 , B29K2105/12 , B29K2307/04 , B29L2031/3076
Abstract: The invention proposes a method for manufacturing a grille for a cascade type thrust reverser, of a jet engine, said method including the following steps:
a) manufacturing a first component comprising continuous or long fibres, pre-impregnated by a thermoplastic or thermosetting resin;
b) manufacturing, subsequently or together with step a), a series of second components each including discontinuous fibres, pre-impregnated by a thermoplastic or thermosetting resin, step b) being carried out such that the second components are, on the one hand, arranged transversally with respect to a longitudinal direction of the first component on at least one side of the first component and, on the other hand, spaced from one another according to this longitudinal direction, so as to form a comb-shaped structure, wherein the second components are consolidated to the first component.-
公开(公告)号：US20180340492A1
公开(公告)日：2018-11-29
申请号：US15605120
申请日：2017-05-25
Applicant: THE BOEING COMPANY
Inventor： Naimishkumar Harpal , Chen Chuck , Zachariah VanDeMark , Tunde A. Olaniyan , Minkoo Han
IPC: F02K1/54
CPC classification number: F02K1/54 , F02K1/64 , F02K1/72 , F05D2230/51 , F05D2230/60 , F05D2240/129 , F05D2240/40
Abstract: A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
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公开(公告)号：US09970388B2
公开(公告)日：2018-05-15
申请号：US15586386
申请日：2017-05-04
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.
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公开(公告)号：US09822734B2
公开(公告)日：2017-11-21
申请号：US14184368
申请日：2014-02-19
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: One embodiment includes a pivot thrust reverser. The pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly. A second tandem pivot door subassembly is included, spaced from the first tandem pivot door subassembly and comprising an inner panel and an outer panel. The inner panel and the outer panel are connected so as to rotate simultaneously about respective pivot axes that are each positionally fixed axes relative to the gas turbine engine assembly.
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公开(公告)号：US09752533B2
公开(公告)日：2017-09-05
申请号：US15029434
申请日：2014-10-16
Applicant: SNECMA
Abstract: A method for monitoring a locking system includes N locks, each lock being monitored by two locking sensors, each locking sensor being capable of indicating if the lock that it monitors is in a locked or unlocked state, each locking sensor being able to be in a valid or invalid status, the method including determining the state of the locking system on the basis of the state of the locks detected by the locking sensors; determining a reliability level associated with the state of the locking system on the basis of the number of valid locking sensors monitoring the locks that are in the same state as the locking system.
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Patent Agency Ranking
公开(公告)号：US20170234267A1
公开(公告)日：2017-08-17
申请号：US15586386
申请日：2017-05-04
Applicant: United Technologies Corporation
Inventor： Jesse M. Chandler , Gabriel L. Suciu
CPC classification number: F02K1/763 , B23P19/04 , B64D29/00 , B64D33/04 , F02K1/60 , F02K1/605 , F02K1/62 , F02K1/64 , F02K1/72 , F05D2260/50 , Y10T29/49229
Abstract: A pivot thrust reverser includes a first tandem pivot door subassembly comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a first sliding rail. A second tandem pivot door subassembly is included comprising an inner panel and an outer panel. The inner panel and outer panel are connected by a second sliding rail.
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7.发明申请DIELECTRIC ELASTOMER DEVICE TO FILL STEPS OR GAPS IN A THRUST REVERSER 有权电介质弹性体装置，用于在一个颠倒的反转器中填充步骤或GAPS公开(公告)号：US20160245231A1
公开(公告)日：2016-08-25
申请号：US14626547
申请日：2015-02-19
Applicant: Rohr, Inc.
Inventor： Joel H. Frank , Lubomir A. Ribarov
IPC: F02K1/76
CPC classification number: F02K1/72 , F02K1/64 , F02K1/66 , F02K1/68 , F02K1/70 , F02K1/74 , F02K1/76 , F05D2250/90 , Y02T50/672
Abstract: Aspects of the disclosure are directed to a thrust reverser of an aircraft, comprising: a wall having a first surface that partially forms a flow channel associated with an air flow, a blocker door having a second surface that partially forms the flow channel, and a dielectric elastomeric device that is configured to selectively expand and contract within a cavity formed between the wall and the blocker door where the cavity is substantially radially adjacent to the flow channel when the thrust reverser is in a stowed state.
Abstract translation: 本公开的方面涉及飞机的推力反向器，包括：壁，其具有部分地形成与空气流相关联的流动通道的第一表面，具有部分形成流动通道的第二表面的阻塞门，以及 介质弹性体装置，其构造成在形成在壁和阻挡门之间的空腔内选择性地膨胀和收缩，其中当推力反向器处于收起状态时，腔基本上径向地邻近流动通道。
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8.发明申请公开(公告)号：US20160039528A1
公开(公告)日：2016-02-11
申请号：US14885422
申请日：2015-10-16
Applicant: AIRCELLE
Inventor： Pierre CARUEL
CPC classification number: B64D29/06 , B64D33/02 , B64D2033/0206 , B64D2033/0273 , F01D25/24 , F02C3/04 , F02C7/04 , F02K1/64 , F02K3/06 , F05D2220/323 , F05D2220/327 , F05D2260/96 , Y02T50/672
Abstract: A nacelle for an aircraft turbojet engine includes: a substantially cylindrical internal envelope, a substantially cylindrical external envelope, a downstream partition wall and an upstream partition wall secured to the cylindrical internal envelope and a front lip disposed forward of the upstream partition wall. The cylindrical internal envelope includes an upstream portion including an acoustic shroud connected, by an attachment flange, to a downstream portion including a fan casing. In particular, the front lip is extended and disposed over the upstream partition wall by presenting a downstream edge between the upstream and downstream partition walls in order to be secured to a homologous edge of the cylindrical external envelope so as to arrange a maintenance access to the attachment flange
Abstract translation: 用于飞行器涡轮喷气发动机的机舱包括：基本上圆柱形的内部封套，基本上圆柱形的外部封套，下游分隔壁和固定到圆柱形内部封套的上游分隔壁和设置在上游分隔壁前方的前唇缘。 圆柱形内封套包括上游部分，其包括通过附接凸缘连接到包括风扇壳体的下游部分的声罩。 特别地，前唇通过在上游和下游隔壁之间呈现下游边缘而延伸并设置在上游分隔壁上方，以便固定到圆柱形外壳的同源边缘，以便安排对 附件法兰
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公开(公告)号：US20150300293A1
公开(公告)日：2015-10-22
申请号：US14441633
申请日：2013-03-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Jesse Chandler
Abstract: A gas turbine engine has a fan inlet and a fan configured to deliver air to an exhaust nozzle. A core gas turbine engine. including in serial order extending further into the engine, a core turbine section, a combustor and a core compressor section. A core engine inlet duct is spaced from the fan inlet. A method is also described.
Abstract translation: 燃气涡轮发动机具有风扇入口和风扇，其构造成将空气输送到排气喷嘴。 核心燃气轮机。 包括进一步延伸到发动机中的串联顺序，核心涡轮部分，燃烧器和核心压缩机部分。 核心发动机入口管道与风扇入口间隔开。 还描述了一种方法。
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公开(公告)号：US09133790B2
公开(公告)日：2015-09-15
申请号：US13640070
申请日：2011-03-10
Applicant: Ingrid Pitiot , Nicolas Dezeustre
Inventor： Ingrid Pitiot , Nicolas Dezeustre
CPC classification number: F02K1/70 , F02K1/64 , F02K1/72 , Y02T50/671
Abstract: A propulsion system has a nacelle, and inside this nacelle, a dual flow turbojet engine includes a fan case in which are located a fan and an assembly of fixed flow-rectifying vanes. This propulsion system includes a thrust inverter located between the fan and the assembly of the fixed flow-rectifying vanes. In particular, the thrust inverter includes a plurality of windows formed in the fan case and thrust inversion flaps to send back the secondary airflow toward the outside and toward the front of the nacelle, through the windows. The thrust inversion flaps pivotally move between a normal operating position in which they allow the passage of the secondary airflow and block the windows, and a thrust inversion position in which they block the passage and clear the windows.
Abstract translation: 推进系统具有机舱，并且在该机舱的内部，双流涡轮喷气发动机包括风扇壳体，其中定位有风扇和固定的整流叶片的组件。 该推进系统包括位于风扇和固定流动整流叶片的组件之间的推力逆变器。 特别地，推力逆变器包括形成在风扇壳体和推力反转挡板中的多个窗口，以通过窗口将二次气流朝向外部并朝向机舱的前部发回。 推力反转挡板在其允许二次气流通过并阻挡窗户的正常操作位置和推力反转位置之间枢转地运动，在该推力反转位置中，阻止通道并清除窗户。
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