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：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.