公开(公告)号：US12044168B2

公开(公告)日：2024-07-23

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：US12037940B2

公开(公告)日：2024-07-16

申请号：US18247037

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Hazem Kioua ,  Emmanuel Lesteven

IPC: F02C7/04 ,  F02C7/047

CPC classification number: F02C7/047 ,  F05D2220/80

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: •⋅ pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •⋅ a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •⋅ at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •⋅ at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

公开(公告)号：US11891185B2

公开(公告)日：2024-02-06

申请号：US17999180

申请日：2021-05-18

Applicant: SAFRAN NACELLES

Inventor： Patrick André Boileau ,  Jean-Philippe Joret ,  Vincent Jean-François Peyron ,  Gina Ferrier

IPC: B64D29/08 ,  F02K1/72 ,  B64D29/06

CPC classification number: B64D29/08 ,  B64D29/06 ,  F02K1/72

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.

公开(公告)号：US20240018902A1

公开(公告)日：2024-01-18

申请号：US18247037

申请日：2021-10-01

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Hazem Kioua ,  Emmanuel Lesteven

IPC: F02C7/047

CPC classification number: F02C7/047 ,  F05D2220/80

Abstract: A supersonic air intake of an aircraft propulsion assembly comprises: a pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, a speed reducer fixedly mounted inside the pipe along the longitudinal axis, at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.

公开(公告)号：US12116954B2

公开(公告)日：2024-10-15

申请号：US18035574

申请日：2021-11-03

Applicant: SAFRAN NACELLES

Inventor： Jean-Philippe Joret ,  Vincent Devanlay ,  Fabien Bravin ,  Boualem Merabet

IPC: F02K1/04 ,  F02K1/80

CPC classification number: F02K1/04 ,  F02K1/80

Abstract: The invention relates to an assembly for a turbine of a turbomachine with a longitudinal axis (X) comprising:



an exhaust cone (100) comprising an outer annular wall (102) for the flow of a primary airflow and an annular box arranged radially inside said outer annular wall (102), the annular box comprising an inner annular wall (104) arranged radially inside the outer annular wall of the exhaust cone,
an exhaust case arranged upstream of the exhaust cone, and
a connecting member (106) flexible in a radial direction, interposed longitudinally between the exhaust case and the exhaust cone (100), the connecting member being fastened to the exhaust case and to the inner annular wall (104), and
wherein the inner annular wall (104) is connected to the outer annular wall (102) by fastening means (112) configured to enable movements of the inner annular wall (104) in a circumferential direction and a longitudinal direction with respect to the outer annular wall (102).

公开(公告)号：US11959437B2

公开(公告)日：2024-04-16

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

IPC: F02K1/04 ,  F02K1/80

CPC classification number: F02K1/04 ,  F02K1/80

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.

公开(公告)号：US12158122B2

公开(公告)日：2024-12-03

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

IPC: F02K1/76 ,  F02K1/60 ,  F02K1/70

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.

公开(公告)号：US12049853B2

公开(公告)日：2024-07-30

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

IPC: F02K1/72 ,  F02K3/06

CPC classification number: F02K1/72 ,  F02K3/06

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.