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公开(公告)号：US20240199193A1
公开(公告)日：2024-06-20
申请号：US18592141
申请日：2024-02-29
发明人： Phillip Greenberg , Ian Wells
CPC分类号： B64C7/02 , B64C29/0025
摘要： A lift nacelle may comprise an airflow generator; a sidewall system coupled to the airflow generator and spanning in a first direction, wherein the sidewall system defines a nacelle interior space, wherein the airflow generator defines one of a forward boundary or an aft boundary of the nacelle interior space; and a lift body disposed in the nacelle interior space and spanning substantially perpendicular to the first direction and substantially perpendicular to an upward lift direction. The airflow generator may be configured to accelerate airflow in an aft direction into the nacelle interior space through the forward boundary of the nacelle interior space. The airflow may contact and/or interact with the lift body creating lift in response.
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公开(公告)号：US12002298B2
公开(公告)日：2024-06-04
申请号：US17264074
申请日：2019-07-24
发明人： Tony Alain Roger Joel Lhommeau , Guillaume Philippe Camille Bastard , Hervé Jean Albert Mouton , Philippe Roger Jacques Canteau
CPC分类号： G07C5/006 , B64C7/02 , G06K17/0022 , G08G5/0004
摘要： A system for aircraft maintenance is disclosed, such as for monitoring parts mounted in a turbojet engine, the turbojet engine being accommodated in a nacelle compartment delimited by a nacelle wall. The system can verify parts, each of the parts being equipped with an RFID tag. The verification system includes an inner antenna accommodated in the nacelle compartment, the inner antenna being arranged to allow the exchange of radio frequency signals with each RFID tag, an interface device including an access point located outside the nacelle compartment, the interface device being arranged to be able to be connected to an interrogator device arranged to communicate with the RFID tag, and a transmission line connecting the interface device to the inner antenna.
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公开(公告)号：US11878786B2
公开(公告)日：2024-01-23
申请号：US17414513
申请日：2019-12-20
申请人： SAFRAN , SAFRAN AIRCRAFT ENGINES , SAFRAN NACELLES
CPC分类号： B64C11/001 , B64C7/02 , B64D29/06
摘要： A propulsion system for an aircraft, including at least one rotor and a nacelle cowling extending around the at least one rotor, said nacelle cowling being sectored and including at least one sector, which is fixed and sectors which are retractable in the peripheral direction relative to an axis of rotation of the rotor. The retractable sectors include at least a first series of sectors which are telescopically retractable in or on at least one fixed sector and at least a second series of sectors which are telescopically retractable in or on at least one fixed sector, the at least one fixed sector having an angular extent around the axis which is less than or equal to 90°.
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公开(公告)号：US11772806B2
公开(公告)日：2023-10-03
申请号：US17262631
申请日：2019-07-10
CPC分类号： B64D29/02 , B64C7/02 , B64D27/18 , B64D33/02 , B64D2033/0226 , B64D2033/0273
摘要： An aircraft engine nacelle for coupling to a wing of an aircraft is disclosed having a fore end, and an aft end that is immoveable relative to the fore end. The aft end includes a major axis Mj and a minor axis Mi, and the nacelle is configured such the minor axis Mi is closer to vertical V than the major axis Mj when the nacelle is coupled to the wing and the aircraft is stationary on the ground. An aircraft system and an aircraft are disclosed each including the aircraft engine nacelle.
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公开(公告)号：US11542865B2
公开(公告)日：2023-01-03
申请号：US16901733
申请日：2020-06-15
申请人： Safran Nacelles
发明人： Patrick Boileau , Caroline Coat-Lenzotti , Marc Versaevel , Virginie Emmanuelle Anne Marie Digeos , Pierre-François Behaghel
摘要： An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.
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公开(公告)号：US20220402592A1
公开(公告)日：2022-12-22
申请号：US17891344
申请日：2022-08-19
发明人： Phillip Greenberg , Ian Wells
摘要： A lift nacelle may comprise an airflow generator; a sidewall system coupled to the airflow generator and spanning in a first direction, wherein the sidewall system defines a nacelle interior space, wherein the airflow generator defines one of a forward boundary or an aft boundary of the nacelle interior space; and a lift body disposed in the nacelle interior space and spanning substantially perpendicular to the first direction and substantially perpendicular to an upward lift direction. The airflow generator may be configured to accelerate airflow in an aft direction into the nacelle interior space through the forward boundary of the nacelle interior space. The airflow may contact and/or interact with the lift body creating lift in response.
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公开(公告)号：US11370530B2
公开(公告)日：2022-06-28
申请号：US16672584
申请日：2019-11-04
申请人： ROLLS-ROYCE plc
发明人： Martin N. Goodhand
摘要： A boundary layer ingestion fan system for location aft of the fuselage of an aircraft is shown. It comprises a nacelle (501) defining a duct, and a fan located therewithin. The fan comprises a hub arranged to rotate around a rotational axis (A-A) and a plurality of blades attached thereto. Each blade has a span (r) from a root at the hub defining a 0 percent span position (r=0) to a tip defining a 100 percent span position (r=1) and a plurality of span positions therebetween (r ∈ [0, 1]), and leading and trailing edges defining, for each span position, a chord therebetween to having a chord length (c). For each of said plurality of blades, the ratio of chord length at the 0 percent span position (chub) to chord length at the 100 percent span position (ctip) is 1 or greater.
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公开(公告)号：US20220170418A1
公开(公告)日：2022-06-02
申请号：US17432853
申请日：2020-02-25
申请人： SAFRAN NACELLES
摘要： The invention relates to a de-icing device for an air intake of an aircraft turbojet engine nacelle extending along an X-axis in which an air stream flows from upstream to downstream, the air intake having an inner cavity, extending annularly about the X-axis, which comprises an inner wall facing the X-axis and an outer wall which is opposite the inner wall, the walls being connected by a leading edge, the de-icing device comprising at least one injector for injecting a stream of hot air into the inner cavity, the injector comprising a nozzle extending along a nozzle axis, the nozzle being configured to inject a stream of hot air having a dissymmetry along the nozzle axis.
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公开(公告)号：US11084596B2
公开(公告)日：2021-08-10
申请号：US16173190
申请日：2018-10-29
发明人： Eric Bouchet , Jérôme Colmagro , Michel Garcia
摘要： An aircraft which comprises a fuselage and at least one propulsion assembly linked to the fuselage by at least two connecting rods positioned at least partially in an inner zone of the air inlet of the nacelle of the propulsion assembly. Thus, the connecting rods do not interfere with the secondary flow flowing inside the nacelle and do not affect the aerodynamic performance levels of the propulsion assembly.
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10.发明授权公开(公告)号：US11034458B2
公开(公告)日：2021-06-15
申请号：US16293939
申请日：2019-03-06
发明人： Thierry Theron
摘要： A front fairing of a pylon of an aircraft includes a shroud, produced in a single piece, which extends over almost all the surface area of the front fairing and which is configured to occupy a closed position in which a peripheral edge of the shroud and a peripheral edge of the front fairing and/or of the nacelle are contiguous, and an open position in which the peripheral edge of the shroud is, at least partially, separated from the peripheral edge of the front fairing and/or of the nacelle. The front fairing includes at least one locking system to hold the shroud in closed position.
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