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公开(公告)号：US20240003315A1
公开(公告)日：2024-01-04
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
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.
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Patent Agency Ranking
公开(公告)号：US20250035069A1
公开(公告)日：2025-01-30
申请号：US18714363
申请日：2022-12-02
Applicant: SAFRAN NACELLES
Inventor： Tony MIOSSEC , Fabien BRAVIN , Vincent DEVANLAY , Marc VERSAEVEL , Valentin SIMEON
IPC: F02K1/82
Abstract: An assembly for an exhaust cone of an aircraft turbomachine, including a first annular wall, and first partitions and second partitions defining between them a plurality of acoustic boxes distributed around the first wall, an assembly formed by the first and the second partitions being fastened to the first wall with first fastening members arranged upstream and with second fastening members arranged downstream, the first fastening members being offset circumferentially with respect to the second fastening members.
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公开(公告)号：US20250019081A1
公开(公告)日：2025-01-16
申请号：US18714334
申请日：2022-12-02
Applicant: SAFRAN NACELLES
Inventor： Tony MIOSSEC , Fabien BRAVIN , Vincent DEVANLAY , Marc VERSAEVEL , Valentin SIMEON
IPC: B64D27/10
Abstract: An assembly for an ejection cone of an aircraft turbomachine, including a first annular wall and a plurality of first partitions and of second partitions extending substantially perpendicularly from the first wall, the first partitions additionally extending wholly in the axial direction and the second partitions extending wholly in a circumferential direction between the adjacent pairs of first partitions and being curved partitions including at least one arcuate portion in the axial direction upstream or downstream, the first wall, the first partitions and the second partitions additionally defining between them a plurality of acoustic boxes distributed around the first wall.
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公开(公告)号：US20230407813A1
公开(公告)日：2023-12-21
申请号：US18251860
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Fabien BRAVIN , Hélène MALOT
Abstract: An assembly for a turbomachine includes an exhaust cone and an exhaust casing having an annular inner shell. The exhaust cone and the exhaust casing can extend about a first axis, the exhaust cone can have an outer surface extending in the projection of the inner shell, the exhaust cone can be connected to the exhaust casing by means of a flange, the flange having an upstream portion fastened to the exhaust casing and lugs extending downstream from said upstream portion, and the exhaust cone can be fastened to the lugs. The flange can be sectorized and include of a plurality of angular sectors arranged so as to be circumferentially adjacent, with each flange sector having at least one lug extending rectilinearly along a second axis parallel to the first axis.
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公开(公告)号：US20230392518A1
公开(公告)日：2023-12-07
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.
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公开(公告)号：US20240011453A1
公开(公告)日：2024-01-11
申请号：US18035574
申请日：2021-11-03
Applicant: SAFRAN NACELLES
Inventor： Jean-Philippe JORET , Vincent DEVANLAY , Fabien BRAVIN , Boualem MERABET
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).
Figure to be published with the abstract: FIG. 2
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