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公开(公告)号：US20230184195A1
公开(公告)日：2023-06-15
申请号：US17999106
申请日：2021-05-17
Applicant: SAFRAN NACELLES
Inventor： Xavier CAZUC , Jean-Philippe JORET , Vincent Jean-François PEYRON , Sébastien Laurent Marie PASCAL
Abstract: A thrust reverser for an aircraft bypass turbojet engine nacelle has a generally annular shape around an axis and includes an annular frame for securing deflection grids. The frame has a first frusto-conical wall widening in the downstream direction and including an upstream peripheral edge configured to be attached to a casing of the turbojet engine. A downstream peripheral edge of the wall extends in the continuation of the wall and secures the upstream ends of the grids. A second annular wall extends radially outwards from an outer frusto-conical face of the first wall. The first and second walls are integrally formed and the second wall has axial openings through which actuators pass.
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2.发明公开公开(公告)号：US20230192308A1
公开(公告)日：2023-06-22
申请号：US18069282
申请日：2022-12-21
Applicant: SAFRAN NACELLES
Inventor： Romain GARDEL , Pierre-Alain REBOUL , Jérôme CORFA , Jean-Philippe JORET , Thomas MARLAY , Matthieu MENIELLE
Abstract: A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.
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公开(公告)号：US20230182913A1
公开(公告)日：2023-06-15
申请号：US17999180
申请日：2021-05-18
Applicant: SAFRAN NACELLES
Abstract: A nacelle for a propulsion assembly, the nacelle including a front internal structure having a framework formed of longitudinal beams and including removable, dismountable or retractable panels which are provided to facilitate the access for maintenance to the parts of the motor shrouded by these panels.
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公开(公告)号：US20230088298A1
公开(公告)日：2023-03-23
申请号：US17904572
申请日：2021-02-16
Applicant: SAFRAN NACELLES
Inventor： Xavier CAZUC , Vincent Jean-Francois PEYRON , Jean-Philippe JORET , Sebastien Laurent Marie PASCAL
IPC: F02K1/72
Abstract: The invention relates to an assembly (601) which comprises a front frame (602) of a thrust reverser structure of an aircraft nacelle and at least one cascade (603). The assembly is characterized in that, when the cascade is fixed to the frame, the axial distance (L) that separates the first blading (605) upstream of the cascade from a covering area (606) between the extension of the cascade and the front frame is greater than or equal to once the mean height (h) of the cascade.
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公开(公告)号：US20240317415A1
公开(公告)日：2024-09-26
申请号：US18574120
申请日：2022-06-27
Applicant: SAFRAN NACELLES
Inventor： Patrick André BOILEAU , Gérard CLERE , Jean-Philippe JORET
Abstract: A propulsion unit includes a fairing delimiting a flow conduit for a secondary flow. This fairing comprises includes panels, at least one of which is articulated on a mast via connecting members such as clevises.
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Patent Agency Ranking
公开(公告)号：US20240003315A1
公开(公告)日：2024-01-04
申请号：US18251798
申请日：2021-11-03
Applicant: SAFRAN NACELLES , SAFRAN CERAMICS
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Fabien BRAVIN , Thomas VANDELLOS
Abstract: An assembly for a turbomachine nozzle having a longitudinal axis (X) includes an exhaust cone with an annular outer wall for guiding a primary air flow and an annular chamber placed radially inside said annular outer wall. The annular chamber includes an annular inner wall placed radially inside the annular outer wall of the exhaust cone. An exhaust case is placed upstream of the ejection cone. A connecting member is interposed longitudinally between the exhaust case and the exhaust cone and fastened to the exhaust case and to the annular inner wall. The assembly further includes elastic means configured to deform radially and prestressed radially between the annular outer wall and the connecting member.
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公开(公告)号：US20240300661A1
公开(公告)日：2024-09-12
申请号：US18574845
申请日：2022-06-27
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DUTOT , Stéphane RIQUIER , François BELLET , Charles-Antoine LAMPAERT
CPC classification number: B64D29/06 , E05C5/02 , E05C2005/005
Abstract: A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.
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公开(公告)号：US20230407813A1
公开(公告)日：2023-12-21
申请号：US18251860
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Fabien BRAVIN , Hélène MALOT
Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.
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公开(公告)号：US20230392518A1
公开(公告)日：2023-12-07
申请号：US18034659
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Marine OLLIVIER , Guillaume LEVIEUX
IPC: F01D25/24
CPC classification number: F01D25/24 , F05D2260/30
Abstract: The invention relates to an assembly for a turbomachine, comprising an exhaust cone (18) and an exhaust case having an annular inner shell, the exhaust cone (18) and the exhaust case extending about an axis (X), the exhaust cone (18) having a radially outer skin (31) extending in the projection of said inner shell and a radially inner skin (30) defining a chamber (32) with the outer skin (31), the upstream end (33) of the cone (18) being fastened to the inner shell (19) via connecting lugs (39), the assembly comprising an annular fairing (29) located radially outside said lugs (39) and extending axially between the inner shell (19) of the exhaust case (17) and the outer skin (31) of the exhaust cone (18), said fairing (29) extending in the projection of said inner shell (19) and of the outer skin (31), the assembly being characterized in that the fairing (29) is segmented and consists of multiple angular segments (42) arranged circumferentially end to end.
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公开(公告)号：US20200025135A1
公开(公告)日：2020-01-23
申请号：US16246605
申请日：2019-01-14
Applicant: Safran Nacelles
Inventor： Jean-Philippe JORET , Jérôme CORFA , Serge BUNEL , Xavier BOUTEILLER
Abstract: The present disclosure relates to a rear assembly of a turbojet engine nacelle that includes a thrust reverser fixed structure having at least one half-cowl mounted on a beam pivotally hinged by at least one hinge, a suspension mast on which the fixed structure is movably mounted, a hatch for access to the hinge of the half-cowl, and a fireproof sealing device which includes a sealing gasket adapted to provide sealing between a median section of the nacelle and the beam area. The sealing gasket includes a tubular gasket type lower portion which extends at least partially over a seal bearing edge of the half-cowl that is adapted to cooperate with a seal bearing wall of the mast and an upper portion including an elastically deformable sealing sheet extending from the seal bearing wall of the mast to the rear face of the hatch for access to the hinge.
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