公开(公告)号：US20240351298A1

公开(公告)日：2024-10-24

申请号：US18580668

申请日：2022-07-13

Applicant: SAFRAN NACELLES ,  SAFRAN NACELLES LIMITED

Inventor： Julien LORRILLARD ,  Bertrand Léon Marie DESJOYEAUX

IPC: B29C70/44 ,  B29C70/54 ,  B29L31/30

CPC classification number: B29C70/443 ,  B29C70/446 ,  B29C70/544 ,  B29C70/549 ,  B29L2031/3076

Abstract: The invention relates to an assembly structure (10) for manufacturing a composite part. The structure comprises:—a skin preform (Pp) and a generally omega-shaped stiffener preform (PT) each having first and second opposing surfaces, the stiffener preform extending along and opposite the first surface of the skin preform. longitudinally and transversely in the form of a stiffener preform cross-section,—a rigid skin tooling (Op) disposed opposite the entire second surface (Sp2) of the skin preform,—a local rigid stiffener tooling (Or1, Or2) extending transversely around the stiffener preform cross-section with a transverse dimension smaller than the transverse dimension of the first surface of the skin preform.

公开(公告)号：US20250067196A1

公开(公告)日：2025-02-27

申请号：US18719046

申请日：2022-12-15

Applicant: SAFRAN NACELLES

Inventor： Virginie Emmanuelle Anne-Marie DIGEOS ,  Caroline COAT-LENZOTTI ,  Thierry Jacques Albert LE DOCTE

IPC: F01D25/02 ,  F01D25/10 ,  F01D25/24

Abstract: An annular air intake lip for a nacelle of an aircraft propulsion assembly is provided. The annular lip can extend about an axis of revolution and include: an external annular wall, an internal annular wall, an upstream annular wall connecting the external and internal annular walls to define an annular cavity therebetween. At least part of the annular lip can include at least one heat transfer coating that is made from a carbon allotrope material.

公开(公告)号：US20250058898A1

公开(公告)日：2025-02-20

申请号：US18717834

申请日：2022-12-09

Applicant: SAFRAN NACELLES

Inventor： Patrick ARCOUËT ,  David PEREIRA ,  Hakim MAALIOUNE

IPC: B64F5/60 ,  G01R31/00 ,  G01R31/28

Abstract: An electronic device for diagnosing the condition of a system of actuators of an aircraft turbine engine, the device being configured to be coupled to an electrical wiring harness of a turbine engine connecting a computer of a turbine engine to a system of actuators of the turbine engine, the device including a power supply block to power the device, a connection block configured to enable the connection of the device to the electrical wiring harness of the turbine engine to be diagnosed, a communication block configured to send information to a user and to receive instructions from the user, and a control block including a test signal transmission module and modules for measuring the signals received by the device in response to the test signals over a work cycle of the system of actuators of the turbine engine.

公开(公告)号：US12214893B2

公开(公告)日：2025-02-04

申请号：US18258319

申请日：2021-12-21

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Thomas Marlay ,  Damien Lemoine ,  Ophélie Schmitter

IPC: F01D17/00 ,  B64D33/02

Abstract: An air inlet for an aircraft propulsion unit having a movable upstream portion, a stationary downstream portion and at least one member for longitudinally translating the movable upstream portion between a retracted position in which the movable upstream portion is adjacent to the stationary downstream portion, and an extended position in which the movable upstream portion is separated from the stationary downstream portion, the moving member having at least one guiding bar connected to the movable upstream portion and a drive bar having a plurality of teeth, the stationary downstream portion having, for each moving member, a gear wheel configured to co-operate with the teeth in order to form a rack-and-pinion connection and at least one guiding member of the guiding bar.

公开(公告)号：US12208915B2

公开(公告)日：2025-01-28

申请号：US18058483

申请日：2022-11-23

Applicant: SAFRAN NACELLES

Inventor： Jihane Bellahbib ,  Hakim Maalioune

IPC: B64D37/30 ,  B64D41/00 ,  F02K1/54 ,  F02K1/76

Abstract: Aircraft having at least one propulsion unit supplied with hydrogen by at least one hydrogen tank, and having at least one thrust reversal system including at least one actuator. The aircraft can include at least one means for storing or transporting the residual hydrogen of the propulsion unit, a fuel cell disposed in the hydrogen power source and supplied with hydrogen by the at least one means for storing the residual hydrogen, and a hydrogen thrust reverser actuation system. The thrust reverser actuation system can include a hydrogen thrust reverser actuation controller and a hydrogen primary power unit with a fuel cell supplied with hydrogen and powering the at least one thrust reverser actuator.

公开(公告)号：US20250001508A1

公开(公告)日：2025-01-02

申请号：US18757348

申请日：2024-06-27

Applicant: SAFRAN NACELLES

Inventor： Pierre-Yves GINI ,  Marc VERSAEVEL ,  Denis RAMAGE

IPC: B23B47/28 ,  B23B35/00 ,  B23B39/04 ,  B23B39/10 ,  B23Q11/10

Abstract: A machining device for producing at least one orifice in a workpiece made of composite material, the machining device including a tool holder and at least one drill bit mounted on the tool holder, the drill bit being configured to be driven in rotation about an axis of rotation. The machining device includes a cylindrical guide body coaxial with the axis of rotation, mounted on the tool holder, and surrounding the drill bit, the guide body being configured to bear on the workpiece during the production of the orifice and the drill bit projecting from the guide body.

公开(公告)号：US20240425191A1

公开(公告)日：2024-12-26

申请号：US18734449

申请日：2024-06-05

Applicant: Safran Nacelles

Inventor： Pierre Charles Caruel

IPC: B64D33/02 ,  F02C7/047

Abstract: An air intake module for an aircraft turbomachine extending along a longitudinal axis oriented from upstream to downstream and including an inner wall and an outer wall defining together a vein for circulating an air flow, a plurality of guide vanes of the air flow extending radially in the vein and each comprising an upstream leading edge, at least one stator member fixedly mounted on the inner wall and on the outer wall and extending radially in the vein upstream of the guide vanes, the stator member comprising an infrared wave emitting device configured to emit an infrared beam on the leading edge of at least one of the guide vanes for de-icing it.

公开(公告)号：US12170077B2

公开(公告)日：2024-12-17

申请号：US17716089

申请日：2022-04-08

Applicant: Safran Nacelles

Inventor： Marc Versaevel ,  Bertrand Desjoyeaux ,  Mathieu Preau

IPC: G10K11/172 ,  B64D33/02

Abstract: An acoustic attenuation panel includes a perforated acoustic wall, a first honeycomb structure coupled to the perforated acoustic wall and including a plurality of acoustic cells defined by peripheral partitions, a second honeycomb structure including a plurality of acoustic cells defined by peripheral partitions, and a septum which includes a plurality of macro-perforations and is positioned between the first honeycomb structure and the second honeycomb structure. Each acoustic cell of the first honeycomb structure and each acoustic cell of the at least second honeycomb structure are arranged opposite a single perforation of the septum.

公开(公告)号：US12168964B2

公开(公告)日：2024-12-17

申请号：US18560510

申请日：2022-05-13

Applicant: SAFRAN NACELLES

Inventor： Patrick Boileau ,  Julien Chandelier ,  Fabien Jourdan ,  Philippe Wiertel

IPC: F02K1/72 ,  F02K1/82

Abstract: A thrust reverser for an aircraft propulsion unit, including a fixed structure, at least one cowl and a plurality of cascades of deflection vanes, the cowl and the cascades of vanes forming a system capable of translational movement relative to the fixed structure along a longitudinal central axis, the mobile system further including at least one rear cascade-support structure to which a rear end of the cascades of vanes is fixed, the rear structure extending in a circumferential direction of the reverser. The rear structure incorporates an acoustic-absorption device including an array of cells and a skin covering the cells, the skin having a first surface arranged facing the cells, and a second surface bounding part of a secondary flow path.

公开(公告)号：US12152552B2

公开(公告)日：2024-11-26

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.