公开(公告)号：US10012097B2

公开(公告)日：2018-07-03

申请号：US14767183

申请日：2014-02-19

Applicant: Snecma

Inventor： Sébastien Jean Laurent Prestel ,  Denis Aydin ,  Rémi Blanc ,  Hélène Condat ,  Patrice Jean-Marc Rosset

IPC: F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D9/04 ,  F01D9/042 ,  F01D11/005 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/323 ,  F05D2230/18 ,  F05D2230/238 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2240/125

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

公开(公告)号：US10107116B2

公开(公告)日：2018-10-23

申请号：US14765816

申请日：2014-01-30

Applicant: SNECMA

Inventor： Sebastien Congratel ,  Marion Chambre ,  Thomas Marchyllie ,  Bruno Richard ,  Romain Roullet ,  Denis Aydin

IPC: F01D9/04 ,  F01D11/00 ,  F01D21/04 ,  F01D25/24

Abstract: The invention concerns a fixed flow distribution blading (10) in a turbomachine, comprising two coaxial annular platforms that are internal (12) and external respectively, linked to each other by a plurality of radial blades (11), in which the internal annular platform (12) comprises an annular radial partition (120) and a blade support ring (121) extending to each side of an outer radial end of said partition (120), the blading (10) further comprising an annular sealing plate (20) mounted on the internal annular platform (12), on the upstream side of the radial partition relative to an airflow in the blading, the blading (10) being characterized in that the sealing plate (20) is mounted on the blade support ring (121), and in that it comprises a circumferential groove. The invention also concerns a method for producing such a blading and a turbomachine comprising such a blading.

公开(公告)号：US20150125289A1

公开(公告)日：2015-05-07

申请号：US14401334

申请日：2013-05-06

Applicant: SNECMA

Inventor： Sabine Maltaverne ,  Denis Aydin ,  Bruno Richard

IPC: F01D25/24 ,  F01D9/04 ,  F01D25/28

CPC classification number: F01D25/246 ,  F01D5/147 ,  F01D9/041 ,  F01D25/28 ,  F05D2220/3213 ,  F05D2230/00 ,  F05D2230/60 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2250/22 ,  F05D2250/292 ,  F05D2260/30 ,  Y10T29/49323

Abstract: A part of a turbomachine distributor, including an outer platform, an inner platform, at least one blade interspaced circumferentially about a longitudinal axis of the part, radial ends of the at least one blade being respectively fixed to the inner platform and to the outer platform, and a fastening element extending from the outer platform, for fastening the part to a casing of the turbomachine. The fastening element includes, on ends thereof arranged on either side of the longitudinal axis, two separate fastening tabs for fastening the part to the casing, the cumulated sum of lengths of the two fastening tabs in relation to length of the fastening element according to a transverse axis of the part being between 25% and 35%.

Abstract translation: 涡轮机分配器的一部分，包括外平台，内平台，至少一个叶片围绕部件的纵向轴线周向间隔开，所述至少一个叶片的径向端分别固定到内平台和外平台 以及从所述外平台延伸的紧固元件，用于将所述部件紧固到所述涡轮机的壳体。 紧固元件在其布置在纵向轴线的任一侧的端部上包括用于将部件紧固到壳体的两个单独的紧固突片，两个紧固突片的相对于紧固元件的长度的累积总和相对于根据 该部分的横轴为25％至35％。

公开(公告)号：US20150377047A1

公开(公告)日：2015-12-31

申请号：US14767183

申请日：2014-02-19

Applicant: SNECMA

Inventor： Sébastien Jean Laurent Prestel ,  Denis Aydin ,  Rémi Blanc ,  Hélène Condat ,  Patrice Jean-Marc Rosset

IPC: F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D9/04 ,  F01D9/042 ,  F01D11/005 ,  F01D25/243 ,  F01D25/246 ,  F05D2220/323 ,  F05D2230/18 ,  F05D2230/238 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2240/125

Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).

Abstract translation: 飞机涡轮机的喷嘴部分包括具有朝向扇形体外部径向延伸的突起（70,70a，70b）的钩构件（64），凹部（72）通过至少一部分 突起（70,70a，70b）的远端，凹部（72）构造成容纳形成相邻扇区（26）的表面的止挡件的肩部构件（74）。

公开(公告)号：US20150354381A1

公开(公告)日：2015-12-10

申请号：US14765816

申请日：2014-01-30

Applicant: SNECMA

Inventor： Sebastien Congratel ,  Marion Chambre ,  Thomas Marchyllie ,  Bruno Richard ,  Romain Roullet ,  Denis Aydin

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D11/001 ,  F01D21/045 ,  F01D25/246 ,  F05D2220/30 ,  F05D2230/10 ,  F05D2230/31 ,  F05D2230/64 ,  F05D2240/11 ,  F05D2240/57 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49325

Abstract: The invention concerns a fixed flow distribution blading (10) in a turbomachine, comprising two coaxial annular platforms that are internal (12) and external respectively, linked to each other by a plurality of radial blades (11), in which the internal annular platform (12) comprises an annular radial partition (120) and a blade support ring (121) extending to each side of an outer radial end of said partition (120), the blading (10) further comprising an annular sealing plate (20) mounted on the internal annular platform (12), on the upstream side of the radial partition relative to an airflow in the blading, the blading (10) being characterised in that the sealing plate (20) is mounted on the blade support ring (121), and in that it comprises a circumferential groove. The invention also concerns a method for producing such a blading and a turbomachine comprising such a blading.

Abstract translation: 本发明涉及一种涡轮机中的固定流量分布叶片（10），包括分别由内部（12）和外部分别由多个径向叶片（11）彼此连接的两个同轴环形平台，其中内部环形平台 （12）包括环形径向隔板（120）和延伸到所述隔板（120）的外径向端的每一侧的叶片支撑环（121），所述叶片（10）还包括环形密封板（20），所述环形密封板 在所述内部环形平台（12）上，相对于所述叶片中的气流在所述径向隔板的上游侧，所述叶片（10）的特征在于所述密封板（20）安装在所述叶片支撑环（121）上， 并且其包括圆周凹槽。 本发明还涉及一种用于生产这种叶片的方法和包括这种叶片的涡轮机。