公开(公告)号：US20240253804A1

公开(公告)日：2024-08-01

申请号：US18627959

申请日：2024-04-05

Applicant: Safran Nacelles

Inventor： Vincent DUTOT ,  Jean-Philippe Joret ,  Marc Versaevel ,  Vincent Lefeuvre

IPC: F02K1/34 ,  B64D29/00 ,  F02K1/82

CPC classification number: B64D33/06 ,  B64D29/00 ,  F02K1/827 ,  F05D2220/323 ,  F05D2260/963

Abstract: An air ejection nozzle for a nacelle includes an outer aerodynamic line and an inner aerodynamic line meeting at a trailing edge. The air ejection nozzle includes at discrete positions at least one area of larger thickness that is compensated by at least one fairing to connect the aerodynamic lines to form the trailing edge. The fairing includes an outer wall and an inner wall delimiting a cavity therebetween. The inner wall provides for the continuity of the inner aerodynamic line, and the outer wall is solid and the inner wall is pierced so that the at least one fairing forms an acoustic attenuation structure.

公开(公告)号：US12037941B2

公开(公告)日：2024-07-16

申请号：US18247052

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Damien Lemoine ,  Charles-Antoine Lampaert ,  Hazem Kioua

IPC: F02C7/04 ,  B64D33/02 ,  F02C7/047

CPC classification number: F02C7/047 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/026 ,  F05D2220/80

Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.

公开(公告)号：US20230417182A1

公开(公告)日：2023-12-28

申请号：US18247852

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Hazem Kioua ,  Pierre Charles Caruel ,  Jean-Philippe Joret ,  Charles-Antoine Lampaert

IPC: F02C7/047 ,  F02C7/042

CPC classification number: F02C7/047 ,  F02C7/042

Abstract: Disclosed is an air intake of a turbine engine nacelle extending along an axis in which a flow of air circulates from upstream to downstream, the air intake extending annularly about the axis, the air intake having a movable upstream portion and a stationary downstream portion, at least one controllable movement member for moving the movable upstream portion between a retracted position and an extended position in order to enable circulation of an air flow passing between the movable upstream portion and the stationary downstream portion, at least one de-icing circuit having at least one circulation channel fluidically connecting the movable upstream portion and a hot air source, the circulation channel having at least one non-telescopic upstream pipe and at least one telescopic downstream member.

公开(公告)号：US10753315B2

公开(公告)日：2020-08-25

申请号：US16246605

申请日：2019-01-14

Applicant: Safran Nacelles

Inventor： Jean-Philippe Joret ,  Jérôme Corfa ,  Serge Bunel ,  Xavier Bouteiller

IPC: F02K1/70 ,  F02K1/80 ,  B64D29/06 ,  F02C7/25 ,  F02C7/28

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.

公开(公告)号：US12000300B2

公开(公告)日：2024-06-04

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.

公开(公告)号：US20240018903A1

公开(公告)日：2024-01-18

申请号：US18247052

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Damien Lemoine ,  Charles-Antoine Lampaert ,  Hazem Kioua

IPC: F02C7/047 ,  B64D33/02

CPC classification number: F02C7/047 ,  B64D33/02 ,  B64D2033/0233 ,  B64D2033/026 ,  F05D2220/80

Abstract: Disclosed is a supersonic speed attenuator for an air inlet of an aircraft power plant, having a conical external wall with a tapered end upstream and an internal dividing wall that delimits, with the conical external wall, a cavity; the supersonic speed attenuator further having a de-icing device having: an internal wall mounted in the cavity opposite the conical external wall so that, together, the two walls delimit a calibrated de-icing volume; at least one member for supplying a de-icing air flow, opening into the de-icing volume; and at least one member for discharging the de-icing air flow from the de-icing space.

公开(公告)号：US20230184193A1

公开(公告)日：2023-06-15

申请号：US18065875

申请日：2022-12-14

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Jérémie Rabineau ,  Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: F02K1/62 ,  F02K1/58

CPC classification number: F02K1/62 ,  F02K1/58 ,  F05D2220/323

Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

公开(公告)号：US20170174353A1

公开(公告)日：2017-06-22

申请号：US15453308

申请日：2017-03-08

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Emmanuel LESTEVEN ,  Vincent PEYRON ,  Patrick BOILEAU

IPC: B64D29/06 ,  F02K1/76 ,  F02K1/62 ,  F04D29/52 ,  F02K1/58

CPC classification number: B64D29/06 ,  B64D27/16 ,  F02K1/763 ,  F05D2220/323 ,  F05D2230/72 ,  F05D2250/11 ,  F05D2260/57

Abstract: A propulsion unit for an aircraft is provided. The propulsion unit includes a stationary unit having at least one cowl pivotally mounted on an axis collinear with a longitudinal axis of the propulsion unit between an operating position or a maintenance position allowing access to the turbojet engine for regular maintenance operations and irregular maintenance operations. The maintenance position for irregular maintenance operations includes an opening angle of the cowl that is greater than the opening angle of the cowl to carry out regular maintenance operations. The propulsion unit further includes at least one cylinder and at least one safety connecting rod secured to the cowl and stationary unit.

公开(公告)号：US12258924B2

公开(公告)日：2025-03-25

申请号：US18065875

申请日：2022-12-14

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Jérémie Rabineau ,  Alexis Yves-Marie Loncle ,  Laurent Georges Valleroy

IPC: F02K1/62 ,  F02K1/58

Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

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.