公开(公告)号：US12018629B2

公开(公告)日：2024-06-25

申请号：US17640111

申请日：2020-09-02

Applicant: SAFRAN NACELLES

Inventor： Pierre Charles Caruel ,  Fabien Charliac ,  Fabien Bravin ,  Loïc Chapelain

IPC: F02K1/76

CPC classification number: F02K1/763

Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including a mobile annular external structure, a single actuator for controlling the position of this mobile external structure and a device for guiding the mobile external structure when changing its position. The actuator and the guiding device are housed in a fairing of a pylon of the propulsion assembly to a wing or fuselage of the aircraft.

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.