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公开(公告)号：US20240239504A1
公开(公告)日：2024-07-18
申请号：US18307172
申请日：2023-04-26
摘要： An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction, a leading edge, a trailing edge, and a chord extending from the leading edge to the trailing edge, the pylon fairing including a maximum thickness portion along the lengthwise direction of the pylon fairing located between 10% and 60% of the chord.
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2.发明公开公开(公告)号：US20240150028A1
公开(公告)日：2024-05-09
申请号：US18502248
申请日：2023-11-06
IPC分类号： B64D27/26
CPC分类号： B64D27/26 , B64D2027/264
摘要： An assembly including a wing with a pressure-side panel and a suction-side panel through which two bores pass, an engine pylon including a blade with three bores and two fastening lugs, each of which has a sixth bore, two first shackles fastened between the blade and the suction-side panel, two second shackles fastened between the blade and the suction-side panel and two fittings, which are fastened beneath the pressure-side panel and each have a female clevis for housing a fastening lug therein.
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公开(公告)号：US20240124147A1
公开(公告)日：2024-04-18
申请号：US17964982
申请日：2022-10-13
发明人： William Joseph Bowden , Jonathan Edward Coleman , Sharad Tiwari , Srinivas Addagatla , Sara Elizabeth Carle
CPC分类号： B64D27/12 , B64D27/26 , F02C7/20 , F05D2220/323 , F05D2240/90
摘要： A gas turbine engine includes an aft frame and a forward frame disposed upstream from the aft frame. The forward frame includes an outer ring. The outer ring includes an inner surface that is radially spaced from an outer surface. A first indention is defined in the outer surface, and a first engine mount flange protrudes radially outwardly from the first indention.
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公开(公告)号：US11952135B2
公开(公告)日：2024-04-09
申请号：US17851407
申请日：2022-06-28
发明人： Cédric Poupon , Olivier Pautis , Jonathan Blanc
CPC分类号： B64D27/26 , F16C11/0628 , B64D2027/262
摘要： A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.
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公开(公告)号：US11884410B2
公开(公告)日：2024-01-30
申请号：US17665286
申请日：2022-02-04
发明人： Srinivas Addagatla , Ravindra Shankar Ganiger , Anil Soni , Sharad Tiwari , Jonathan E. Coleman
CPC分类号： B64D27/26 , F01D25/28 , B64D2027/262 , B64D2027/268 , F05D2220/323 , F05D2240/90
摘要： Dual function links for gas turbine engine mounts are disclosed. An example apparatus for mounting a casing of a gas turbine engine to a pylon, the apparatus includes a first pin and a linkage including a first linkage portion including the first pin, a second linkage portion, the second linkage portion forming a first load path between the gas turbine engine and the pylon, the second linkage portion arranged with respect to the first linkage portion such that a gap prevents the first linkage portion from forming a second load path between the gas turbine engine and the pylon.
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公开(公告)号：US11866205B2
公开(公告)日：2024-01-09
申请号：US17714096
申请日：2022-04-05
IPC分类号： B64D27/26 , B64C29/02 , B64C11/46 , B64U50/19 , B64U80/00 , B64U30/293 , B64U10/25 , B64U30/20
CPC分类号： B64U30/293 , B64C11/46 , B64C29/02 , B64D27/26 , B64D2027/262 , B64U10/25 , B64U30/20 , B64U50/19 , B64U80/00 , B64U2201/10 , B64U2201/20
摘要： An unmanned aircraft system operable for wing-borne lift in a flying wing orientation. The unmanned aircraft system includes an airframe having a leading edge, a trailing edge, first and second wingtips and a root chord. The airframe has an airfoil cross-section along chord stations thereof. A thrust array is coupled to the airframe including first and second motor mounts coupled to the leading edge respectively between the root chord and the first and second wingtips. The motor mounts each have first and second propulsion assemblies coupled to respective first and second distal ends thereof. The motor mounts each have a flight configuration substantially perpendicular with the leading edge forming a two-dimensional distributed thrust array such that the airframe extends outboard of the first and second motor mounts. The unmanned aircraft system includes an electric power system and a flight control system that are operably associated with the thrust array.
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公开(公告)号：US11840347B2
公开(公告)日：2023-12-12
申请号：US17114703
申请日：2020-12-08
发明人： Jérôme Colmagro , Paolo Messina
CPC分类号： B64D27/26 , B64F5/10 , F16C11/045 , B64D2027/268 , Y10T403/32909
摘要： An assembly including a link axis supported by first and second guiding rings positioned in first and second branches of a clevis, one of the guiding rings including a tubular extension, protruding with respect to an outer face of one of the branches, which has a threaded portion on its outer circumferential face. Complementing this, the assembly includes a nut configured to be screwed onto the threaded portion of the tubular extension and an immobilization system configured to immobilize the nut in translation and/or in rotation, the nut and the link axis being linked by a complete link that is non-removable or that forms a single-piece part. This solution makes it possible to reduce the number of parts forming the assembly. Also provided are an engine attachment and an aircraft including such an assembly.
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公开(公告)号：US20230374913A1
公开(公告)日：2023-11-23
申请号：US17746514
申请日：2022-05-17
发明人： Nicholas Guglielmin
CPC分类号： F01D25/243 , B64D27/26
摘要： A structure is provided for a gas turbine engine. This gas turbine engine structure includes an engine case, an engine pylon and an engine line. The engine case includes a base, a mounting boss and a first support element. The base extends axially along and circumferentially about an axial centerline of the engine case. The mounting boss projects radially out from the base. The first support element projects radially out from the base and laterally out from the mounting boss. The first support element is configured as or otherwise includes a peripheral boss. The engine pylon is mounted to the mounting boss. The engine line is coupled to the peripheral boss.
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公开(公告)号：US11820510B2
公开(公告)日：2023-11-21
申请号：US16807521
申请日：2020-03-03
申请人： EMBRAER S.A.
CPC分类号： B64C7/00 , B64C1/22 , F16C11/045 , F16M13/02 , B64D27/26 , Y10T403/32893
摘要： Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.
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10.发明授权公开(公告)号：US11807373B2
公开(公告)日：2023-11-07
申请号：US17081193
申请日：2020-10-27
发明人： Julien Allain , Stéphane Dida , Jérome Colmagro , Olivier Dubois , Julien Moulis , Jacky Puech , Laurent Lafont
CPC分类号： B64D27/26 , B64F5/10 , F16B5/08 , B64D2027/266
摘要： The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.
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