公开(公告)号：US10267154B2

公开(公告)日：2019-04-23

申请号：US15038732

申请日：2014-11-25

Applicant: SNECMA

Inventor： Maurice Guy Judet ,  Cecile Marie Emilienne Alirot ,  Alexandre Xavier Bossaert ,  Fabrice Marcel Noel Garin ,  Christian Michel Jacques Gosselin ,  Axel Sylvain Loic Thomas

IPC: F01D5/10 ,  F01D5/02 ,  F02C7/36 ,  F04D29/053 ,  F04D29/32 ,  F04D29/66

Abstract: The turbine (1) has a rotor (2) with blades (4) arranged on a periphery of disks (5) in radial planes (3), and a tie rod (6) extending along slots (7) in the disks. An annular spacer (15, 15′) fixes a position of the tie rod relative to a center line (M) of the disks, and is arranged in a channel (10, 11). The spacer has through-openings, which are arranged radially relative to the tie rod or to its center line, and extend coaxially. The channel carries a cooling medium and is limited by a separating pipe (13, 14) radially outwards. The through-openings serve for flow of the medium.

公开(公告)号：US20160123153A1

公开(公告)日：2016-05-05

申请号：US14931474

申请日：2015-11-03

Applicant: SNECMA

Inventor： Sébastien Serge Francis Congratel ,  Maurice Guy Judet

IPC: F01D5/10 ,  F01D5/30

CPC classification number: F01D5/10 ,  F01D5/22 ,  F01D5/3023 ,  F01D11/006 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/671

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.

Abstract translation: 一种用于涡轮发动机的涡轮机叶轮，包括每个具有平台的盘承载叶片，其承载由高跷连接到根部的叶轮。 每个叶片包括从叶片的平台向内延伸的上游径向壁和下游径向壁。 叶片的根部接合在盘的周边上的槽中，使得叶片的径向壁和叶片的平台被端对端地周向布置，并且在平台内部径向地限定叶片间空腔， 每个容纳叶片间密封和振动阻尼构件。 至少一个构件包括可弹性变形的构件，其构造成在构件安装位置中弹性预应力抵靠空腔的壁。

公开(公告)号：US20160186656A1

公开(公告)日：2016-06-30

申请号：US14897607

申请日：2014-06-11

Applicant: SNECMA

Inventor： Maurice Guy Judet ,  Laurent Coulombeau ,  Michel Jacques ,  Fabrice Garin

IPC: F02C3/06 ,  F02C7/20 ,  F02C7/06

CPC classification number: F02C3/064 ,  F01D25/16 ,  F01D25/18 ,  F01D25/183 ,  F02C7/06 ,  F02C7/20 ,  F02C7/28 ,  F05D2240/70 ,  F05D2260/602 ,  F05D2260/609

Abstract: The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterised in that it includes a drop-launching extension (32) arranged such as to extend opposite a flared portion (33) of the inner surface (34) of the seal mounting (26), such that when the trunnion (23) is rotated about the shaft of the low-pressure turbine (9), oil (H2), which tends to penetrate between the trunnion (23) and the seal mounting (26), is thrown by centrifugal effect from the drop-launching extension (32) toward the flared portion (33) of the inner surface (34) of the seal mounting (26).

Abstract translation: 本发明涉及一种用于高压涡轮机（11）的耳轴（23），其布置在低压涡轮机（9）的轴与密封件安装件（26）的内表面（34）之间 低压涡轮机（8），耳轴（23）的特征在于它包括一个下落发射延伸部（32），其布置成与密封件安装件的内表面（34）的扩口部分（33）相对延伸 （26），使得当所述耳轴（23）围绕所述低压涡轮机（9）的轴旋转时，容易穿过所述耳轴（23）和所述密封件安装件（26）之间的油（H2） 通过离心效应从下落推进件（32）向密封件安装件（26）的内表面（34）的扩口部分（33）抛出。

公开(公告)号：US10526906B2

公开(公告)日：2020-01-07

申请号：US15081079

申请日：2016-03-25

Applicant: SNECMA

Inventor： David Thien-Roger Nguyen ,  Franck Boisnault ,  Maurice Guy Judet ,  Laetitia Person

IPC: F01D11/02 ,  F01D5/18 ,  F01D11/04

Abstract: A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.

公开(公告)号：US10113480B2

公开(公告)日：2018-10-30

申请号：US14897607

申请日：2014-06-11

Applicant: SNECMA

Inventor： Maurice Guy Judet ,  Laurent Jacques Michel Coulombeau ,  Fabrice Garin

IPC: F01D25/18 ,  F02C3/06 ,  F02C7/28 ,  F02C7/06 ,  F02C7/20 ,  F01D25/16

Abstract: The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterized in that it includes a drop-launching extension (32) arranged such as to extend opposite a flared portion (33) of the inner surface (34) of the seal mounting (26), such that when the trunnion (23) is rotated about the shaft of the low-pressure turbine (9), oil (H2), which tends to penetrate between the trunnion (23) and the seal mounting (26), is thrown by centrifugal effect from the drop-launching extension (32) toward the flared portion (33) of the inner surface (34) of the seal mounting (26).

公开(公告)号：US09890652B2

公开(公告)日：2018-02-13

申请号：US14869312

申请日：2015-09-29

Applicant: Snecma

Inventor： Maurice Guy Judet ,  Pierre Guillaume Auzillon ,  Matthieu Simon

IPC: F01D5/02 ,  F01D5/12 ,  F01D5/22 ,  F01D11/00 ,  F01D5/08 ,  F01D5/30

CPC classification number: F01D11/006 ,  F01D5/02 ,  F01D5/082 ,  F01D5/12 ,  F01D5/225 ,  F01D5/3015 ,  F05D2220/323 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/231 ,  Y02T50/676

Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.

公开(公告)号：US20160090855A1

公开(公告)日：2016-03-31

申请号：US14869312

申请日：2015-09-29

Applicant: Snecma

Inventor： Maurice Guy Judet ,  Pierre Guillaume Auzillon ,  Matthieu Simon

IPC: F01D11/00 ,  F01D5/12 ,  F01D5/30 ,  F01D5/02 ,  F01D5/22

CPC classification number: F01D11/006 ,  F01D5/02 ,  F01D5/082 ,  F01D5/12 ,  F01D5/225 ,  F01D5/3015 ,  F05D2220/323 ,  F05D2240/24 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/231 ,  Y02T50/676

Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.

Abstract translation: 一种用于涡轮发动机的旋转组件，包括具有外周边具有交替的槽和齿的盘，从盘的径向延伸的叶片和其根部轴向接合在槽中，在所述槽的根部之间设置称为槽腔的空间 叶片和槽，平台从叶片横向延伸并且周向地布置成端对端，以便形成称为叶片间空腔的空间，以及下游环形护罩，包括与平台的下游端相对的外部环形密封唇 。 下游护罩还包括与槽的齿的下游面相对的中间环形密封唇缘，在槽腔和刀片间空腔之间。

公开(公告)号：US09951625B2

公开(公告)日：2018-04-24

申请号：US14931474

申请日：2015-11-03

Applicant: SNECMA

Inventor： Sébastien Serge Francis Congratel ,  Maurice Guy Judet

IPC: F01D5/10 ,  F01D5/22 ,  F01D11/00 ,  F01D5/30

CPC classification number: F01D5/10 ,  F01D5/22 ,  F01D5/3023 ,  F01D11/006 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/671

Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.

公开(公告)号：US20160281525A1

公开(公告)日：2016-09-29

申请号：US15081079

申请日：2016-03-25

Applicant: SNECMA

Inventor： David Thien-Roger NGUYEN ,  Franck Boisnault ,  Maurice Guy Judet ,  Laetitia Person

IPC: F01D11/02 ,  F01D5/18

Abstract: A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.

Abstract translation: 一种用于飞机涡轮机的涡轮叶片，包括根部，翼型件和插入在翼型件和根部之间并限定气体循环流动路径的平台，该平台具有两个轴向端，每个端部形成天使翼，其中至少一个具有内部空腔 将从叶片的根部提供空气。 两个天使翼中至少有一个钻有至少一个排放孔，用于从内腔通过渗流，这将限制/防止在流路外的气体再循环。

公开(公告)号：US09366150B2

公开(公告)日：2016-06-14

申请号：US13659404

申请日：2012-10-24

Applicant: SNECMA

Inventor： Maurice Guy Judet ,  Jerome Etienne Robert Cameau ,  Fabrice Marcel Noel Garin ,  Alain Paul Madec

IPC: F01D9/04 ,  F01D25/24

CPC classification number: F01D9/042 ,  F01D25/246 ,  F05D2230/60 ,  F05D2250/70 ,  F05D2260/30 ,  F05D2270/114 ,  F05D2300/501 ,  Y02T50/672 ,  Y10T29/49316

Abstract: The present disclosure aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the turbomachine uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with an axial fastener. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Abstract translation: 本公开旨在实现涡轮机定子叶片的安装，同时避免发动机壳体的精细加工过程。 它还旨在简化安装以及降低成本，并减少引擎的项目参考数量。 为了实现这些目的，涡轮机使用发动机外壳的延伸部分。 涡轮机包括用于在内部发动机壳体上流动的空气或气流的至少一个定子叶片。 定子叶片包括轮缘，该轮辋组装在具有轴向紧固件的发动机壳体的径向延伸部上。 在涡轮机的优选实施例中，发动机壳体呈现环形壁，该环形壁设有从该壁轴向产生并且根据曲率延伸的指状物，使得它们呈现抵靠定子叶片边缘的径向延伸尖端。