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1.发明申请公开(公告)号：US20220228541A1
公开(公告)日：2022-07-21
申请号：US17580110
申请日：2022-01-20
发明人： Alain PORTE , Lionel CZAPLA , Benjamin THUBERT
IPC分类号： F02K3/02
摘要： A turbofan engine with a nacelle and a flow path, in which the nacelle comprises a movable cowl that makes it possible to define a window between the flow path and the outside, veils with a first edge fixed to the movable cowl and alternately assuming a folded position or a deployed position across the flow path, and a pneumatic system displacing a second edge of the veils from the folded position to the deployed position and vice versa. The pneumatic system comprises a rigid main roll, for each veil, at least one extendable secondary roll fixed to a second edge of the veil, and a pressurization and depressurization system which, alternately, generates a pressure or a depression in each secondary roll. Replacing the reverse doors and their driving mechanisms with flexible veils and a pneumatic system allows for a weight reduction.
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2.发明申请公开(公告)号：US20210107670A1
公开(公告)日：2021-04-15
申请号：US16990298
申请日：2020-08-11
发明人： Alain PORTE , Frédéric VINCHES
IPC分类号： B64D33/02
摘要： An anterior part of a nacelle of a propulsion assembly of an aircraft, having an air intake lip and a front frame disposed at the rear of the air intake lip that connects an outer part to an inner part of the air intake lip. A de-icing duct is formed in front of the front frame. The front frame is shaped so that the de-icing duct has a main cavity and a thermal transition region formed behind the main cavity between an internal face of the outer part of the air intake lip and the front frame. The thermal transition region extends over a longitudinal dimension greater than its average radial dimension, the front frame forming, with respect to the internal face of the outer part of the air intake lip, an angle, measured longitudinally, of between −20° and +10° over the majority of the thermal transition region.
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公开(公告)号：US20210107666A1
公开(公告)日：2021-04-15
申请号：US16990260
申请日：2020-08-11
发明人： Alain PORTE , Jacques LALANE , Frédéric VINCHES , Franck DOBIGEON
摘要： An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.
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4.发明申请公开(公告)号：US20180105281A1
公开(公告)日：2018-04-19
申请号：US15730954
申请日：2017-10-12
发明人： Alain PORTE , Frédéric VINCHES
CPC分类号： B64D33/02 , B64C7/02 , B64D29/00 , B64D2033/0206 , B64D2033/0273 , B64D2033/0286 , F02C7/045 , F05D2220/323 , F05D2230/60 , F05D2230/70 , F05D2260/30 , F05D2260/31 , F05D2260/963 , Y02T50/672
摘要： An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.
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公开(公告)号：US20210371118A1
公开(公告)日：2021-12-02
申请号：US17330598
申请日：2021-05-26
发明人： Alain PORTE , Jacques LALANE , Florian RAVISE , Franck DOBIGEON
IPC分类号： B64D29/00 , B29C65/48 , B29C65/00 , G10K11/162 , G10K13/00
摘要： A method for producing an alveolar soundproofing structure in which a portion of a membrane of a diaphragm including an acoustic outlet is inserted into a hole of a perforated membrane which covers a cell of the alveolar structure, and the diaphragm is pressed into the cell with the perforated membrane becoming deformed and is fixed at that location. It also relates to the alveolar structure. Such a method enables different types of diaphragms to be inserted into different configurations of cells and enables the diaphragm to be fixed therein, in accordance with the sound frequencies to be processed.
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公开(公告)号：US20190300191A1
公开(公告)日：2019-10-03
申请号：US16364888
申请日：2019-03-26
发明人： Alain PORTE , François PONS , Gregory ALBET
摘要： An aircraft nacelle comprising an air inlet, with a single fan cowling made of a single piece which extends over all the circumference of the fan. The fan cowling is borne by the air inlet and is mounted to be rotationally mobile about the axis of the nacelle relative to the air inlet, via a link and guiding arrangement comprising a circular rail and a runner capable of sliding along the circular rail. The fan cowling comprises one or more openings closed by hatches allowing access to the interior of the nacelle. The fan cowling has little susceptibility to being deformed both in flight and on the ground during maintenance operations. Furthermore, no pylon portion is needed in the zone of the fan cowling since the latter is not attached to the pylon.
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公开(公告)号：US20220282669A1
公开(公告)日：2022-09-08
申请号：US17684667
申请日：2022-03-02
发明人： Arnaud BOURHIS , Gregory ALBET , Alain PORTE
摘要： An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.
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公开(公告)号：US20220161939A1
公开(公告)日：2022-05-26
申请号：US17532830
申请日：2021-11-22
发明人： Alain PORTE , Jacques LALANE , François PONS
IPC分类号： B64D33/02 , B64D29/00 , G10K11/162
摘要： A resistive skin shell for an acoustic panel or inner wall of an aircraft air intake, comprising an alternation, in a transverse direction, of perforated metal bands and of composite solid bands extending in a longitudinal direction. The perforated metal bands and the composite solid bands form a smooth outer face configured to be in contact with an aerodynamic stream, and a crenelated inner face. The composite solid bands have a thickness greater than the perforated metal bands. Since the perforations are provided in metal bands, which are intrinsically resistant to wear and erosion, the future proofing of the acoustic performance of the resistive skin is guaranteed. Since the composite solid bands, which are thicker, can ensure the mechanical strength of the skin, the thickness of the perforated metal bands can be reduced, allowing perforations with dimensions that are also reduced, having a lower impact on drag.
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公开(公告)号：US20220097863A1
公开(公告)日：2022-03-31
申请号：US17387529
申请日：2021-07-28
发明人： Alain PORTE , Jacques LALANE , Florian RAVISE , Franck DOBIGEON
IPC分类号： B64D29/00 , G10K11/162 , B29D99/00
摘要： An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.
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公开(公告)号：US20210107669A1
公开(公告)日：2021-04-15
申请号：US16990214
申请日：2020-08-11
发明人： Alain PORTE , Jacques LALANE , Frédéric VINCHES , Gregory ALBET
IPC分类号： B64D33/02
摘要： An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.
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