公开(公告)号：US20240359803A1

公开(公告)日：2024-10-31

申请号：US18292114

申请日：2022-07-19

Applicant: AIRBUS OPERATIONS LIMITED

Inventor： Martin MUIR

IPC: B64D27/40 ,  B22F10/28 ,  B23K26/342 ,  B33Y10/00 ,  B33Y80/00 ,  B64D27/18

CPC classification number: B64D27/402 ,  B22F10/28 ,  B23K26/342 ,  B33Y10/00 ,  B33Y80/00 ,  B22F2998/10 ,  B64D27/18

Abstract: A multi-material component is provided including two members formed of different materials joined together at a multi-material join. The two members have complementary protrusions that form a multi-material join with a zig-zag interface, such that a tension between them is experienced in at least part as a shear force at the interface between the protrusions. The component further includes a third member connected to the first member by a lattice, which is capable of elastic deformation so as to substantially isolate the interface between the complementary protrusions from deformation of the third member such as that caused by thermal expansion. Methods of designing and constructing such a component in a single piece via additive manufacturing are provided. The component is particularly suitable for use in pylons connecting jet engines to aircraft wings.

公开(公告)号：US20240246689A1

公开(公告)日：2024-07-25

申请号：US18243049

申请日：2023-09-06

Applicant: JETOPTERA, INC.

Inventor： Andrei Evulet

IPC: B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C39/02 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64U30/00 ,  B64U30/10 ,  F02C3/04 ,  F02C6/04 ,  F02K1/00 ,  F02K1/36

CPC classification number: B64D33/04 ,  B64C9/38 ,  B64C15/00 ,  B64C15/14 ,  B64C21/00 ,  B64C21/04 ,  B64C23/00 ,  B64C23/005 ,  B64C39/024 ,  B64D27/10 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  F02C3/04 ,  F02C6/04 ,  F02K1/002 ,  F02K1/36 ,  B64C2230/04 ,  B64C2230/06 ,  B64C2230/16 ,  B64D2033/0273 ,  B64U30/00 ,  B64U30/10 ,  F05D2220/90 ,  Y02T50/10 ,  Y02T50/30 ,  Y02T50/40

Abstract: A propulsion system coupled to a vehicle. The system includes a convex surface, a diffusing structure coupled to the convex surface, and at least one conduit coupled to the convex surface. The conduit is configured to introduce to the convex surface a primary fluid produced by the vehicle. The system further includes an intake structure coupled to the convex surface and configured to introduce to the diffusing structure a secondary fluid accessible to the vehicle. The diffusing structure comprises a terminal end configured to provide egress from the system for the introduced primary fluid and secondary fluid.

公开(公告)号：US11851200B2

公开(公告)日：2023-12-26

申请号：US17253441

申请日：2019-06-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Hervé Simonotti

IPC: F02C7/25 ,  B64D27/26 ,  F02C7/20 ,  B64D27/18 ,  B64D45/00 ,  F02C7/28

CPC classification number: B64D27/26 ,  F02C7/20 ,  B64D27/18 ,  B64D2045/009 ,  F02C7/25 ,  F02C7/28 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2240/90

Abstract: A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.

公开(公告)号：US20230286661A1

公开(公告)日：2023-09-14

申请号：US18040444

申请日：2021-08-02

Applicant: MTU Aero Engines AG

Inventor： Hermann Klingels

IPC: B64D27/18 ,  B64D27/26 ,  B64D33/10 ,  B64D29/06 ,  F02C7/141 ,  F02C3/30

CPC classification number: B64D27/18 ,  B64D27/26 ,  B64D33/10 ,  B64D29/06 ,  F02C7/141 ,  F02C3/305 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2270/08

Abstract: The present invention relates to an aircraft comprising at least one wing, at least one flight propulsion drive, and a retainer, particularly an engine pylon, which interconnects the wing and the flight propulsion drive. The aircraft comprises at least one heat exchanger for cooling exhaust gas of the fight propulsion drive and/or at least one water removal channel having at least one removal apparatus for removing water from exhaust gas of the flight propulsion drive, especially after the exhaust gas has flowed through the heat exchanger. The removal apparatus is disposed on, more particularly in, the retainer or is connected to the wing by means of the retainer, and/or the flight propulsion drive is fastened to the retainer by means of at least one flight propulsion drive suspension means, and the heat exchanger is fastened, independently thereof, to the retainer by means of at least one heat exchanger suspension means.

公开(公告)号：US11746726B2

公开(公告)日：2023-09-05

申请号：US17307570

申请日：2021-05-04

Applicant: Rohr, Inc.

Inventor： Adam Saunders ,  Bryce T. Kelford ,  Travis M. Frazier ,  Richard Haslim ,  Richard S. Alloway ,  Vijay V. Pujar

IPC: F02K1/52 ,  B64D29/06 ,  F02K1/80 ,  F02K1/04 ,  F02K1/82 ,  F02K1/38 ,  B64D27/26 ,  B64D27/18 ,  F02K3/06

CPC classification number: F02K1/52 ,  B64D27/18 ,  B64D29/06 ,  F02K1/805 ,  F02K3/06 ,  B64D27/26 ,  F05D2220/323 ,  F05D2240/128

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.

公开(公告)号：US20180334259A1

公开(公告)日：2018-11-22

申请号：US15981054

申请日：2018-05-16

Applicant: Rohr, Inc.

Inventor： Michael Aten ,  Anthony Lacko

IPC: B64D27/26 ,  B64D27/18

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/264

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft propulsion system and a pylon configured to mount the aircraft propulsion system to an airframe member. The pylon includes a first pylon structure and a second pylon structure. The first pylon structure is configured to mount to the airframe member. The second pylon structure is mounted to the aircraft propulsion system. The second pylon structure is configured to disconnect from the first pylon structure while mounted to the airframe member.

公开(公告)号：US20180305032A1

公开(公告)日：2018-10-25

申请号：US15956154

申请日：2018-04-18

Applicant: Airbus Operations SAS

Inventor： Guillaume GALLANT ,  Olivier GLEIZE

IPC: B64D27/26 ,  F02C7/20

CPC classification number: B64D27/26 ,  B64D27/12 ,  B64D27/18 ,  B64D2027/266 ,  F02C7/20

Abstract: An engine assembly for an aircraft, comprising an engine mounting pylon comprising a primary structure forming a box closed by a front closing rib, a front engine mount comprising at least two connecting link rods that are disposed laterally on either side of the box and each comprise a first end mounted on a first fitting of the casing. The rib forms a part of the front mount, comprising at least one transverse fitting made in one piece so as to close a front end of the box and to have lugs protruding laterally on each side of the box, each lug being provided with a first orifice for mounting a second end of one of the link rods.

公开(公告)号：US20180238186A1

公开(公告)日：2018-08-23

申请号：US15439122

申请日：2017-02-22

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Thomas Ory Moniz ,  Monty Lee Shelton ,  Joel Francis Kirk ,  Jeffrey Donald Clements

IPC: F01D9/06 ,  F01D5/02 ,  F01D9/04 ,  F02K3/06 ,  B64D27/10

CPC classification number: B64D27/10 ,  B64D27/18 ,  F02C7/20 ,  F02K3/06 ,  F05D2250/323 ,  F05D2250/52 ,  F05D2250/712 ,  Y02T50/672

Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a low pressure (LP) turbine defining an outer flowpath. The outer flowpath defines a first outer flowpath radius at an upstream-most end of the LP turbine, a last outer flowpath radius disposed at a downstream-most end of the LP turbine, a middle outer flowpath radius disposed therebetween along the longitudinal direction. The middle outer flowpath radius is greater than the last outer flowpath radius.

公开(公告)号：US10017270B2

公开(公告)日：2018-07-10

申请号：US14879217

申请日：2015-10-09

Applicant: General Electric Company

Inventor： Thomas Lee Becker ,  Kurt David Murrow ,  Patrick Michael Marrinan ,  Brandon Wayne Miller

IPC: B64D33/02 ,  B64D27/18 ,  B64D27/24 ,  B64D27/26 ,  F01D15/10 ,  F02C7/32 ,  F02K3/062 ,  F04D29/32 ,  F04D29/36 ,  F04D29/52 ,  F04D29/54 ,  B64C1/16 ,  B64C21/06 ,  B64D27/20 ,  B64D29/04 ,  B64D27/02

CPC classification number: B64D33/02 ,  B64C1/16 ,  B64C21/06 ,  B64D27/18 ,  B64D27/20 ,  B64D27/24 ,  B64D27/26 ,  B64D29/04 ,  B64D2027/026 ,  B64D2033/0226 ,  F01D15/10 ,  F02C7/32 ,  F02K3/062 ,  F04D29/325 ,  F04D29/36 ,  F04D29/522 ,  F04D29/542 ,  F05D2220/323 ,  Y02T50/166

Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.

公开(公告)号：US20180170562A1

公开(公告)日：2018-06-21

申请号：US15892334

申请日：2018-02-08

Applicant: The Boeing Company

Inventor： Omid B. Nakhjavani ,  Robert H. Willie ,  Paul S. Park ,  Mohammad Ali Heidari ,  Leonard J. Hebert ,  Milan Stefanovic ,  Parminder Singh ,  Naimishkumar B. Harpal ,  Andrew Y. Na

IPC: B64D27/18 ,  B64D27/26

CPC classification number: B64D27/18 ,  B64D27/26 ,  B64D2027/264 ,  Y02T50/44

Abstract: In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.