公开(公告)号：US20240067349A1

公开(公告)日：2024-02-29

申请号：US18062977

申请日：2022-12-07

申请人： General Electric Company

发明人： Kudum Shinde ,  Mahesh Khandeparker

IPC分类号： B64D27/26 ,  B64D13/08

CPC分类号： B64D27/26 ,  B64D13/08 ,  B64D2013/0607 ,  B64D2027/262

摘要： Example engine apparatus and associated control methods are disclosed. An example engine apparatus includes: a frame; a lug to attach the frame to an aircraft; a mount cover positioned over the lug; and a heating mechanism to regulate a temperature of the lug under the mount cover.

公开(公告)号：US20240052781A1

公开(公告)日：2024-02-15

申请号：US18260923

申请日：2022-01-13

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Guillaume GLEMAREC ,  Jean-Baptiste VIGNES ,  Romuald Muriel GENTILS ,  Valerio CAPASSO

IPC分类号： F02C7/20 ,  F01D25/04 ,  B64D27/26

CPC分类号： F02C7/20 ,  F01D25/04 ,  B64D27/26 ,  F05D2260/96 ,  B64D2027/262

摘要： Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.

公开(公告)号：US11858645B2

公开(公告)日：2024-01-02

申请号：US17752450

申请日：2022-05-24

申请人： The Boeing Company

发明人： Jonathan P. Boas

IPC分类号： F02C7/20 ,  B64D27/26 ,  F16B7/06 ,  F16G11/12

CPC分类号： B64D27/26 ,  F02C7/20 ,  F16B7/06 ,  F16G11/12 ,  B64D2027/262 ,  Y10T403/295

摘要： Adjustable support links for aircraft are disclosed herein. An adjustable support link includes a first rod end including a first shaft with first external threads, a second rod end including a second shaft with a bore having first internal threads, and a barrel nut at least partially disposed in the bore of the second rod end. The barrel nut has second external threads engaged with the first internal threads. The barrel nut having a channel. The first shaft is at least partially disposed in the channel. The channel has second internal threads engaged with the first external threads of the first rod end, such that rotation of the barrel nut in a first direction causes the first and second rod ends to move toward each other and rotation of the barrel nut in a second direction causes the first and second rod ends to move away from each other.

公开(公告)号：US11851201B2

公开(公告)日：2023-12-26

申请号：US17283742

申请日：2019-10-04

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Quentin Matthias Emmanuel Garnaud ,  Guillaume Glemarec ,  Hervé Jean Albert Mouton ,  Guilhem Seize ,  Benoit Bernard René Leclerc

IPC分类号： B64D27/26 ,  B64D27/16

CPC分类号： B64D27/26 ,  B64D27/16 ,  B64D2027/262

摘要： The invention relates to a turbomachine (1) extending along an axis (X), comprising a high-pressure body with a high-pressure compressor (4) coupled in rotation to a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled in rotation to a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and means of suspension (12, 13) for the turbomachine (1), intended for attaching the turbomachine (1) to an aircraft pylon (11).

公开(公告)号：US11834187B2

公开(公告)日：2023-12-05

申请号：US16998893

申请日：2020-08-20

申请人： Safran Nacelles ,  Safran Aircraft Engines

发明人： Patrick Boileau ,  Bruno Beutin

IPC分类号： B64D29/06 ,  B64F5/50 ,  B64D27/26 ,  F02K1/70 ,  F02K1/76

CPC分类号： B64D29/06 ,  B64D27/26 ,  B64F5/50 ,  F02K1/70 ,  F02K1/763 ,  B64D2027/262 ,  F05D2220/323 ,  F05D2260/02

摘要： A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.

公开(公告)号：US11649043B2

公开(公告)日：2023-05-16

申请号：US17406174

申请日：2021-08-19

申请人： Bell Textron Inc.

发明人： Carlos Alexander Fenny ,  Jouyoung Jason Choi

IPC分类号： B64C27/08 ,  B64C39/06 ,  B64D27/26 ,  G05D1/02 ,  G05D1/08

CPC分类号： B64C27/08 ,  B64C39/062 ,  B64D27/26 ,  G05D1/0202 ,  G05D1/0808 ,  B64D2027/262

摘要： An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.

公开(公告)号：US20190217964A1

公开(公告)日：2019-07-18

申请号：US15873128

申请日：2018-01-17

申请人： HONEYWELL INTERNATIONAL INC.

发明人： Shawn Alstad ,  Jeff Guymon ,  Justin C. Mickelsen

IPC分类号： B64D27/26 ,  F16M13/02 ,  F16F15/08 ,  F16F15/06 ,  B64D27/20

CPC分类号： B64D27/26 ,  B64D27/20 ,  B64D2027/262 ,  F16F15/06 ,  F16F15/085 ,  F16M13/02

摘要： A mount system provides vibration isolation and support through a hybrid hard-soft configuration. The mount system includes a frame and a body connected with the frame. A first coupling element is provided on the body and defines a first opening. A second coupling element is provided on the frame and defines a second opening. A pin extends through the first and second openings to couple the body to the frame. At least one of the first and/or second openings operates as a damping hole with a series of slits disposed about the damping hole, so that the damping hole with the slits is configured to deflect to reduce the transmission of vibrations between the body and the frame.

公开(公告)号：US10060354B2

公开(公告)日：2018-08-28

申请号：US15445521

申请日：2017-02-28

申请人： United Technologies Corporation

发明人： Gabriel L. Suciu ,  Ioannis Alvanos ,  Brian Merry

IPC分类号： B64D27/10 ,  F02C7/20 ,  B64D27/26

CPC分类号： F02C7/20 ,  B64D27/10 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/266 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/90 ,  Y02T50/44 ,  Y10T29/49947

摘要： A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.

公开(公告)号：US20180223944A1

公开(公告)日：2018-08-09

申请号：US15423719

申请日：2017-02-03

申请人： HUTCHINSON AEROSPACE & INDUSTRY Inc.

发明人： Iman SHAHOSSEINI ,  John NALL ,  Ivan ROSAN

IPC分类号： F16F13/10 ,  F16F15/02 ,  F16F15/023 ,  B64D27/26

CPC分类号： F16F13/10 ,  B60K5/1208 ,  B60K5/1283 ,  B60Y2200/51 ,  B64D27/12 ,  B64D27/26 ,  B64D2027/262 ,  B64D2027/264 ,  F02C7/20 ,  F16F9/28 ,  F16F15/022 ,  F16F15/023

摘要： A hydraulic torque compensation device comprises a pair of housings, a first housing including a first high pressure liquid chamber and a second low pressure liquid chambers, a second housing having a third high pressure liquid chamber, a fourth accumulator chamber, and a fifth low pressure chamber that is defined by a wall and an end of the second housing. A first main duct links the first chamber of the first housing to the third chamber of the second housing. A second main duct links the second chamber of the first housing to the fifth chamber of the second housing. Each housing also include a piston, the first chamber between a first piston body and an end of the first housing and the third chamber between a second piston body and the wall. The device ensures a counter action to engine loads when a positive torque is applied.

公开(公告)号：US20180163631A1

公开(公告)日：2018-06-14

申请号：US15831503

申请日：2017-12-05

申请人： MITSUBISHI AIRCRAFT CORPORATION

发明人： Akira Takeuchi

IPC分类号： F02C7/25 ,  B64D27/26 ,  B64D29/00 ,  B64D45/00

CPC分类号： F02C7/25 ,  B64C1/40 ,  B64D27/26 ,  B64D29/00 ,  B64D29/02 ,  B64D29/06 ,  B64D33/00 ,  B64D33/02 ,  B64D45/00 ,  B64D2027/262 ,  B64D2045/009 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2240/59 ,  Y02T50/671

摘要： A fire seal structure prevents flame from coming out of a fire-prevention region of an aircraft. The fire seal structure includes: a plurality of walls including: a first wall provided on a first partitioning member; and a second wall provided on a second partitioning member. One of the plurality of walls is a spring wall that functions as a spring. The first and the second partitioning members define the fire-prevention region. The plurality of walls forms a labyrinth-shaped gap between the first and the second partitioning members. Each of the plurality of walls contains a refractory material and includes a front end part. When the first and the second partitioning members are stationary with respect to each other, the front end part is not in contact with another member, and the spring wall is disposed closest to a facing member, among the plurality of walls.