公开(公告)号：US20170312868A1

公开(公告)日：2017-11-02

申请号：US15510866

申请日：2015-09-03

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Marina Wilma BILIONIERE ,  Thierry Michel BREUGNOT ,  Didier Noël DURAND

IPC: B23P6/00 ,  B23K9/04 ,  F01D25/24 ,  B23K9/167 ,  B23K101/00

Abstract: A method for repairing an upstream rail of a turbine engine turbine casing, the casing including a casing body extending along a longitudinal axis, the upstream rail including: a base including a radial surface, extending substantially radially from the casing body; a plate including an upper surface, extending substantially along the longitudinal axis; and a connection portion between the base and the plate, including a concave surface connecting the radial surface and the upper surface, the concave surface and the radial surface extending on either side of an edge, the method including: covering a surface with a solder, the surface including the upper surface and the concave surface, such that the solder extends substantially until the edge; and a step of machining the covered surface, in a single action, in the direction of the radial surface, and at least until the edge, so as to reshape the surface.

公开(公告)号：US20250035002A1

公开(公告)日：2025-01-30

申请号：US18715268

申请日：2022-12-02

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Antoine GIGUET ,  Nicolas Daniel DELAPORTE ,  Pierre Marie MULHEIM ,  Arnaud MARTINE

IPC: F01D5/30

Abstract: An assembly includes a disk of a moving gear of a turbomachine comprising an axis of rotation and teeth. The teeth each include a first lateral surface on one side and a second lateral surface on the other side. Slots are formed between the teeth and each include a bottom surface that connects the first lateral surface of one tooth to the second lateral surface of an adjacent tooth. A first radial surface and a second radial surface are formed on either side of the disk and delimit the slots and teeth. A shim is mounted in a slot and includes an outer surface that partly covers the first and second radial surfaces, a base in contact with the bottom surface, a first lateral arm and a second lateral arm which are connected to one another by the base.

公开(公告)号：US20240337192A1

公开(公告)日：2024-10-10

申请号：US18575954

申请日：2022-06-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Pierre Marie MULHEIM ,  Arnaud MARTINE ,  Antoine GIGUET ,  Vincent GOYON

IPC: F01D5/30 ,  F01D5/32

CPC classification number: F01D5/3007 ,  F01D5/326 ,  F05D2260/36

Abstract: A foil and a root of a blade of a turbomachine rotor and includes a base, two side limbs that are connected to each other by the base, at least the first limb includes at least one recess including at least two folds in two different directions, the recess being capable of engaging with a notch provided in the root of the blade to ensure the foil is longitudinally retained relative to the root of the blade at least in a longitudinal direction.

公开(公告)号：US20230194371A1

公开(公告)日：2023-06-22

申请号：US17996154

申请日：2021-04-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Adeline Isabelle Anne-Marie HOUSSAYE ,  Arnaud MARTINE

IPC: G01L5/24 ,  B64F5/60

CPC classification number: G01L5/246 ,  B64F5/60

Abstract: A method for checking the tightening tension of at least one fastening bolt for fastening at least two aeronautical parts, wherein it includes the steps consisting in mounting a centring device on a head of a screw of the bolt, the centring device including an aperture aligned with an axis of the screw; engaging one end of a sensor in the aperture of the device until this end is in contact with the head of the screw; checking at least one physical parameter of the bolt by the sensor, this parameter being representative of the tightening tension of the bolt; then removing the centring device.

公开(公告)号：US20210254481A1

公开(公告)日：2021-08-19

申请号：US16973663

申请日：2019-06-06

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Alain Dominique GENDRAUD ,  Emmanuel Bernard Marie CHARRIER

IPC: F01D5/30 ,  F01D25/28

Abstract: The present disclosure relates to a holding system for the dismantling of a blade wheel, the blade wheel comprising: a disc, a plurality of blades configured to be mounted circumferentially around the disc, the plurality of blades defining a plurality of inter-blade spaces, each of the inter-blade spaces being defined circumferentially between two adjacent blades of the plurality of blades, the holding system comprising a plurality of inserts, each of the inserts being configured to be inserted into each of the inter-blade spaces in a holding position so as to hold the relative position of the blades when the plurality of blades is dismantled from the disc.

公开(公告)号：US20190085713A1

公开(公告)日：2019-03-21

申请号：US16138062

申请日：2018-09-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Anthony Pierre BEGUIN ,  Didier Noël DURAND

IPC: F01D11/12

Abstract: The invention relates to a sealing assembly for a turbine engine, comprising a wheel mounted inside a sectorised ring carrying an abradable material, having at an axial end an annular groove (14) in which a circumferential rail of the casing is engaged, sealing members being partly engaged in a recess (19) of a circumferential edge of a ring sector and another part thereof being engaged in a recess of a circumferential edge circumferentially opposite a circumferentially adjacent ring sector, characterised in that each sealing member comprises an axial end portion (180a) arranged radially between the circumferential rail and two adjacent ring sectors.

公开(公告)号：US20250027431A1

公开(公告)日：2025-01-23

申请号：US18714243

申请日：2022-12-02

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Anthony Pierre BEGUIN ,  Olivier Jean-Daniel BAUMAS ,  Nicolas Daniel DELAPORTE

IPC: F01D9/04 ,  F01D25/24

Abstract: An assembly for a turbomachine of longitudinal axis includes a nozzle carried by an annular part which is fixed to an outer casing. The nozzle has an outer annular platform from which extends, radially outwards, a radial annular wall which carries an annular attachment tab extending longitudinally upstream from the radial annular wall. The assembly has a cooling circuit with an inner annular chamber delimited radially by the outer annular platform and the annular part and delimited downstream by the radial annular wall. An intermediate annular chamber is formed radially externally to the annular attachment tab and in fluid communication with the outer casing. Means of fluid communication between the inner annular chamber and the intermediate annular chamber is formed in the annular attachment tab of the nozzle.

公开(公告)号：US20240360769A1

公开(公告)日：2024-10-31

申请号：US18688009

申请日：2022-08-16

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Pierre Marie MULHEIM ,  Arnaud MARTINE ,  Antoine GIGUET ,  Vincent GOYON

IPC: F01D5/30

CPC classification number: F01D5/3007 ,  F01D5/3023 ,  F05D2220/323 ,  F05D2240/20 ,  F05D2240/30

Abstract: A foil for a turbomachine rotor blade, configured to be mounted on a root of the rotor blade and including an embossment located in a lower surface of the foil and forming, in the lower surface of the foil, a convex protrusion capable of being inserted into a housing formed in a lower face of the blade root.

公开(公告)号：US20240200460A1

公开(公告)日：2024-06-20

申请号：US18552017

申请日：2022-03-22

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Vincent GOYON ,  Pierre Marie MULHEIM ,  Arnaud MARTINE ,  Antoine GIGUET ,  Nicolas Daniel DELAPORTE

IPC: F01D5/30

CPC classification number: F01D5/3015 ,  F05D2250/75 ,  F05D2260/38

Abstract: A foil for a rotating blade of a turbomachine, configured to be mounted to a blade root of the rotating blade and including an overall U-shaped cross-section formed by two lateral legs connected through a lower surface, the lower surface covering a lower face of the blade root, the lateral legs each covering at least part of two lateral flanks of the blade root; and a blocking system for prohibiting at least some of relative movements between the blade root and the foil, the blocking system including at least one oblique tab, partially cut out of a lower surface of the foil and forming, with respect to the lower surface of the foil, a tilted plane protrusion able to be inserted into a housing formed in a lower face of the blade root.

公开(公告)号：US20230392519A1

公开(公告)日：2023-12-07

申请号：US18249230

申请日：2021-10-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Nicolas Daniel DELAPORTE ,  Antoine GIGUET ,  Mostafa BENBOUDA

IPC: F01D25/24

CPC classification number: F01D25/243 ,  F05D2260/31

Abstract: An aircraft turbomachine module having two tubular casings equipped with first and second annular flanges assembled by studs received in the first flange and receiving nuts on the back of the second flange, each stud having an intermediate stretch of hexagonal shape cooperating with a locking plate. The locking plate can have a first orifice received on the intermediate stretch by at least two opposite walls, and a transverse body which is immobilized to prevent the rotation of the plate and that of the stud. Each plate can be fitted on two immediately adjacent studs and the body can have, for this purpose, a second orifice opposite the first orifice and which is received on an intermediate stretch of an immediately adjacent stud and cooperates with the intermediate stretch of hexagonal shape of the stud.