公开(公告)号：US20170284338A1

公开(公告)日：2017-10-05

申请号：US15087531

申请日：2016-03-31

Applicant: The Boeing Company

Inventor： Fedor Kleshchev ,  Kyle Thomas ,  Billy P. Tung ,  Michael Maffeo ,  Robert Shaun Farrell

IPC: F02K1/76 ,  B64D29/06 ,  B64D27/12 ,  F02K1/60 ,  F02C3/04

CPC classification number: F02K1/766 ,  B64D27/12 ,  B64D29/06 ,  F01D25/243 ,  F02C7/20 ,  F02K1/54 ,  F02K1/605 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2250/283 ,  F05D2260/30 ,  F05D2260/31 ,  F16B5/01 ,  F16B5/02 ,  Y02T50/672

Abstract: Systems and methods are provided for an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.

公开(公告)号：US09581108B2

公开(公告)日：2017-02-28

申请号：US14184376

申请日：2014-02-19

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler

IPC: F02K1/72 ,  F02K1/60 ,  F02K1/62 ,  F02K1/64 ,  B64D29/00 ,  B23P19/04 ,  F02K1/76

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 with a first pivot door with an upper linkage and a lower linkage and a second pivot door, spaced from the first pivot door, with an upper linkage and a lower linkage. A first actuator is located on a first side of an attachment location to drive the first pivot door. A second actuator is located on a second side of the attachment location to drive the second pivot door. A third actuator is located substantially radially opposite the attachment location to drive both the first pivot door and the second pivot door. The first pivot door is configured to be pivoted from a stowed position to a deployed position by both the first actuator and the third actuator. The second pivot door is configured to be pivoted from the stowed position to the deployed position by both the second actuator and the third actuator.

Abstract translation: 一个实施例包括枢转推力反向器，其具有带有上连杆的第一枢转门和下连杆以及与第一枢转门隔开的第二枢转门，具有上连杆和下连杆。 第一致动器位于附接位置的第一侧以驱动第一枢轴门。 第二致动器位于附接位置的第二侧以驱动第二枢转门。 第三致动器基本上位于与附接位置径向相对的位置，以驱动第一枢转门和第二枢转门。 第一枢转门构造成通过第一致动器和第三致动器由收起位置枢转到展开位置。 第二枢转门构造成通过第二致动器和第三致动器由收起位置枢转到展开位置。

公开(公告)号：US20160017844A1

公开(公告)日：2016-01-21

申请号：US14774896

申请日：2014-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L Suciu ,  Jesse M Chandler

IPC: F02K1/70 ,  B64D33/04 ,  B64D29/04 ,  F02K3/00

CPC classification number: F02K1/70 ,  B64D29/04 ,  B64D33/04 ,  F02C3/10 ,  F02K1/60 ,  F02K1/605 ,  F02K3/00 ,  F05D2250/314

Abstract: An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall.

Abstract translation: 发动机系统具有气体发生器，围绕气体发生器的至少一部分的双壁壁，围绕风扇的壳体，以及具有第一和第二推力反向器门的壳体，所述第一和第二推力反向器门处于展开位置彼此邻接并且所述双 -fi墙。

公开(公告)号：US20150121895A1

公开(公告)日：2015-05-07

申请号：US14187027

申请日：2014-02-21

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  T. David Bomzer

IPC: F02K1/32 ,  F02C3/04 ,  F02C7/20

CPC classification number: F02K1/605 ,  F01D25/24 ,  F02C3/04 ,  F02K1/60 ,  F02K1/62 ,  F02K1/625 ,  F02K1/64 ,  F02K1/70 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2240/14 ,  F05D2270/051

Abstract: A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.

Abstract translation: 燃气涡轮发动机包括静止的第一环形部分，并适于部分地围绕发动机芯。 第一环形部分包括前挂架连接部分。 燃气涡轮发动机还包括连接到前挂架并沿着后方向从第一环形部分延伸的轨道。 燃气涡轮发动机还包括第二环形部分，其布置在第一部分的后部并且联接到轨道。 第二环形部分可沿着发动机芯心中心线在关闭位置和至少一个打开位置之间移动。 第二环形部分构造成在关闭位置接合第一环形部分，从而提供对发动机芯的通路。 燃气涡轮发动机还包括布置在第二环形部分中的推力反向器。

公开(公告)号：US6151885A

公开(公告)日：2000-11-28

申请号：US159549

申请日：1998-09-24

Applicant: Fabrice Henri Emile Metezeau ,  Bernard Guy Vauchel

Inventor： Fabrice Henri Emile Metezeau ,  Bernard Guy Vauchel

IPC: F02K1/32 ,  F02K1/60

CPC classification number: F02K1/605 ,  Y02T50/671

Abstract: A turbojet-engine thrust reverser comprises a displaceable sub-assembly including two internal clamshells (12) mounted on stationary pivots (18) of a stationary structure (1) and an annular, axially displaceable structure (11). The displaceable structure forms the external, downstream part (13) of a cowling. In the forward-thrust mode, the displaceable structure forms a downstream portion (15) of a radial outer wall of the flow path and forms the entire trailing edge by covering the clamshells (12) such that the clamshells form part of the radial outer wall of the flow path.

Abstract translation: 涡轮喷气发动机推力反向器包括可移动子组件，其包括安装在静止结构（1）的固定枢轴（18）上的两个内部蛤壳（12）和环形的可轴向移动的结构（11）。 可移动结构形成整流罩的外部和下游部分（13）。 在向前推力模式中，可移动结构形成流动路径的径向外壁的下游部分（15）并且通过覆盖蛤壳（12）形成整个后缘，使得蛤壳形成径向外壁的一部分 的流路。

公开(公告)号：US3655150A

公开(公告)日：1972-04-11

申请号：US3655150D

申请日：1970-06-17

Applicant: MESSERSCHMITT BOELKOW BLOHM

Inventor： HABERKORN ERICH J ,  ENGLAENDER KLAUS

IPC: B64C9/38 ,  F02K1/00 ,  F02K1/60 ,  B64D33/04

CPC classification number: F02K1/605 ,  B64C9/38 ,  F02K1/002 ,  F02K1/006 ,  F02K1/60 ,  Y02T50/32 ,  Y02T50/44

Abstract: Aircraft jet engine having a vectoring discharge for pitch and yaw control purposes including means for maintaining such control during low thrust or reversing jet operation. A vectoring nozzle is arranged on the exit of the jet tube in the manner of a ball joint for universal swiveling and the lateral and vertical control obtained thereby. Openings are provided for both the inner and outer portion of the cooperating spherical members such that when the vectoring nozzle swivels on the jet pipe more or less of the openings on the respective sides thereof come into register with each other. By directing the discharge from said openings in a reversing direction, same will function as reversing jets when the nozzle is closed and by swiveling thereof such discharge can be directed to one side or the other of the aircraft to obtain the desired directional control.

Abstract translation: 具有用于俯仰和偏航控制目的的矢量放电的飞机喷气发动机，包括用于在低推力或反向喷射操作期间保持该控制的装置。 引导喷嘴以用于通用旋转的球形接头的方式布置在喷射管的出口上，并且由此获得横向和垂直控制。 为配合的球形构件的内部和外部设置开口，使得当矢量喷嘴在喷射管上旋转时，其相应侧面上的开口的多或少几个彼此对准。 通过在反转方向上引导从所述开口排出，当喷嘴关闭时，它们将作为反转喷嘴起作用，并且通过使其旋转，这样的排放可以被引导到飞行器的一侧或另一侧以获得期望的方向控制。

公开(公告)号：US3434666A

公开(公告)日：1969-03-25

申请号：US3434666D

申请日：1966-02-24

Applicant: ROLLS ROYCE

Inventor： SHAW WILLIAM

IPC: F02K1/60 ,  F02K1/74 ,  A01G25/02 ,  B05B1/20

CPC classification number: F02K1/74 ,  F02K1/60 ,  F02K1/605

公开(公告)号：US3050937A

公开(公告)日：1962-08-28

申请号：US74072158

申请日：1958-06-09

Applicant: BOEING CO

Inventor： JAMES VARNELL L R ,  PEARSON RAYMOND E

IPC: F02K1/60 ,  F02K1/76

CPC classification number: F02K1/605 ,  F02K1/76 ,  Y02T50/671

公开(公告)号：US11767807B2

公开(公告)日：2023-09-26

申请号：US17402041

申请日：2021-08-13

Applicant: Safran Nacelles

Inventor： Pierre Caruel ,  Alexandre Descamps

IPC: F02K1/60 ,  F02K1/76

CPC classification number: F02K1/60 ,  F02K1/605 ,  F02K1/763 ,  F02K1/766

Abstract: A closing system that includes a closing actuator for doors of a thrust reverser, two sliding members, and a detection device. The closing actuator includes two first connecting rods. Each first connecting rod is configured to be connected to a first lateral edge of each door. The closing actuator is arranged to move each door at least towards the direct jet position. Each sliding member carries a second connecting rod configured to be connected to a second lateral edge of each door. The second connecting rods are arranged to be driven by the doors when the closing actuator moves the doors towards the direct jet position so as to displace the two sliding members. The detection device detects a defect of one of the first and second connecting rods. The detection device is configured to detect the relative position of the two sliding members in the direct jet position.

公开(公告)号：US20170226961A1

公开(公告)日：2017-08-10

申请号：US15019055

申请日：2016-02-09

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Danis Burton Smith ,  Robert Romano

IPC: F02K1/72

CPC classification number: F02K1/72 ,  F02K1/605 ,  F02K1/625 ,  F02K1/76 ,  F02K1/766 ,  F05D2300/501 ,  Y02T50/672

Abstract: A thrust reverser system for a turbine engine includes a support structure, a transcowl, a door, a lock, and a first elastic element. The transcowl is mounted on the support structure and is translatable between a stowed position, a deployed position, and an over-stow position. The door is pivotally coupled to the support structure and is rotatable between at least a first position, a second position, and a third position. The lock is movable between a locked position, to prevent transcowl translation toward the deployed position, and an unlocked position, to allow transcowl translation toward the deployed position. The lock is only able to move to the unlocked position when the transcowl is in the over-stow position. The first elastic element is disposed within the stowed position aperture and, when engaging both the support structure and the transcowl, supplies a force to the transcowl.