公开(公告)号：US09726033B2

公开(公告)日：2017-08-08

申请号：US14357113

申请日：2012-11-12

Applicant: SNECMA

Inventor： Alain Dominique Gendraud ,  Fabrice Marcel Noel Garin ,  Romain Nicolas Lunel

IPC: F01D5/30 ,  F01D11/00 ,  F01D5/32

CPC classification number: F01D11/006 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/326 ,  F01D11/001 ,  F05D2240/55 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/30 ,  Y02T50/672

Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

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。

公开(公告)号：US20140308133A1

公开(公告)日：2014-10-16

申请号：US14357113

申请日：2012-11-12

Applicant: SNECMA

Inventor： Alain Dominique Gendraud ,  Fabrice Marcel Noel Garin ,  Romain Nicolas Lunel

IPC: F01D11/00

CPC classification number: F01D11/006 ,  F01D5/3007 ,  F01D5/3015 ,  F01D5/326 ,  F01D11/001 ,  F05D2240/55 ,  F05D2250/231 ,  F05D2250/232 ,  F05D2260/30 ,  Y02T50/672

Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

Abstract translation: 用于诸如飞机涡轮螺旋桨或涡轮喷气发动机的涡轮发动机的转子轮，转子轮包括转子盘，转子盘在其外周边包括齿，其限定用于轴向安装并径向保持叶片根部的槽。 环形唇缘包括从径向保持机构的轴向下游并径向向内延伸的环形边缘，该径向保持机构形成为从盘的上游面轴向突出，并且密封机构径向设置在环形唇缘的径向内部和平台的上游端 刀片。

公开(公告)号：US10054000B2

公开(公告)日：2018-08-21

申请号：US14449308

申请日：2014-08-01

Applicant: SNECMA

Inventor： Fabrice Marcel Noel Garin ,  Florence Valerie Bon ,  Jerome Etienne Robert Cameau ,  Jean-Marc Michel Lesaine ,  Alain Paul Madec

IPC: F01D25/24 ,  F01D11/24 ,  F01D11/18

CPC classification number: F01D11/24 ,  F01D11/18 ,  F01D25/246 ,  F05D2210/12 ,  F05D2220/323 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2300/174 ,  F05D2300/175 ,  F05D2300/5021

Abstract: The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterized in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.

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：US20130108434A1

公开(公告)日：2013-05-02

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 ,  B21D53/78

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

Abstract: The invention 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 invention 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 axial fastening means. 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: 本发明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，本发明使用发动机外壳的延伸部。 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。 定子叶片包括轮辋，其被组装在具有轴向紧固装置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。