公开(公告)号：US12129761B2

公开(公告)日：2024-10-29

申请号：US17795511

申请日：2021-01-26

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Meredith Roberts ,  Chris Anderson ,  Nicolas François Paul Broussais-Colella ,  Ambroise Nicolas Marie Malfroy ,  Foster Alexander Maxwell ,  Paul Myslinski ,  Adrienne Retiveau-Leca

IPC: F01D11/12 ,  B05C5/02 ,  B05C9/06 ,  B05C11/02 ,  B05C11/10 ,  B05C17/10 ,  B05D1/40 ,  B05D3/12 ,  B05D7/22

CPC classification number: F01D11/122 ,  B05C5/0216 ,  B05C9/06 ,  B05C11/025 ,  B05C11/1036 ,  B05C17/10 ,  B05D1/40 ,  B05D3/12 ,  B05D7/22 ,  F05D2230/31

Abstract: A casing of an aircraft turbomachine includes an annular shell extending around an axis A and made of a composite material having fibers that which are woven and embedded in a resin. An annular layer made of abradable material extends inside the shell, around axis A and is obtained by spreading and polymerizing a paste. Support panels extend around axis A and are interposed between the shell and the abradable layer.

公开(公告)号：US11788434B2

公开(公告)日：2023-10-17

申请号：US17626322

申请日：2020-07-10

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Vincent Pascal Fiore ,  Gatien Frisoni ,  Foster Alexander Maxwell ,  Steven Meserve ,  Jeffrey Steven Sherman

IPC: F01D25/24 ,  B29C65/00 ,  B29L31/00

CPC classification number: F01D25/24 ,  B29C66/612 ,  B29C66/919 ,  B29C66/929 ,  B29L2031/7504 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2300/603

Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.

公开(公告)号：US20230075984A1

公开(公告)日：2023-03-09

申请号：US17795511

申请日：2021-01-26

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Meredith ROBERTS ,  Chris ANDERSON ,  Nicolas François Paul BROUSSAIS-COLELLA ,  Ambroise Nicolas Marie MALFROY ,  Foster Alexander MAXWELL ,  Paul MYSLINSKI ,  Adrienne RETIVEAU-LECA

IPC: F01D11/12 ,  B05C11/02 ,  B05C17/10 ,  B05C11/10 ,  B05C5/02 ,  B05C9/06

Abstract: A casing of an aircraft turbomachine includes an annular shell extending around an axis A and made of a composite material having fibers that which are woven and embedded in a resin. An annular layer made of abradable material extends inside the shell, around axis A and is obtained by spreading and polymerizing a paste. Support panels extend around axis A and are interposed between the shell and the abradable layer.

公开(公告)号：US20220281198A1

公开(公告)日：2022-09-08

申请号：US17634716

申请日：2020-08-07

Applicant: SAFRAN AERO COMPOSITE ,  SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Damien Vincent LE CLOAREC ,  Clement GIACOVELLI ,  Jeffrey Steven SHERMAN ,  Mickaelle Lucie Alicia THOMAS

IPC: B29D99/00 ,  G05D5/02

Abstract: A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.

公开(公告)号：US20220243617A1

公开(公告)日：2022-08-04

申请号：US17626322

申请日：2020-07-10

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Vincent Pascal FIORE ,  Gatien FRISONI ,  Foster Alexander MAXWELL ,  Steven MESERVE ,  Jeffrey Steven SHERMAN

IPC: F01D25/24 ,  B29C65/00

Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.

公开(公告)号：US12275202B2

公开(公告)日：2025-04-15

申请号：US17980931

申请日：2022-11-04

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Maxime Marie Désiré Blaise ,  Allison Glugla ,  Lauren Chin ,  Cali Lapenta

IPC: B29C70/44 ,  B29L31/08 ,  B64C21/10

Abstract: A method for producing an aerodynamic element for an aircraft, including a wall which is covered, at least partially, by a printed film including a plurality of ribs and/or grooves, the method including: providing a raw film made of a deformable material which is devoid of grooves and ribs; providing a pressure plate which includes a face provided with ribs and/or grooves complementary to the ribs and/or grooves of the printed film; placing said raw film on the wall of the element; positioning the pressure plate on the raw film, the printed side of the pressure plate facing the raw film; and a forming step during which the raw film is bonded with the wall of the component and during which the raw film is shaped by cooperation with the pressure plate to obtain the printed film including the ribs and/or the grooves.

公开(公告)号：US12005666B2

公开(公告)日：2024-06-11

申请号：US17634716

申请日：2020-08-07

Applicant: SAFRAN AERO COMPOSITE ,  SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Damien Vincent Le Cloarec ,  Clement Giacovelli ,  Jeffrey Steven Sherman ,  Mickaelle Lucie Alicia Thomas

IPC: B23P15/02 ,  B29D99/00 ,  G05D5/02 ,  F01D5/14

CPC classification number: B29D99/0025 ,  B23P15/02 ,  G05D5/02 ,  F01D5/141 ,  F05D2230/18 ,  Y10T29/49336 ,  Y10T29/49771

Abstract: A verification method for verifying whether the aerodynamic profile of a real blade for an aircraft turbine engine complies with a theoretical blade, the method including constructing a camber line of the theoretical blade and constructing a camber line of the real blade; constructing a relationship for the thickness of the theoretical blade and constructing a relationship for the thickness of the real blade, the thickness relationship of a blade corresponding to the curve plotting the thickness of the blade as a function of curvilinear length along the camber line from a leading edge of the blade to a trailing edge of the blade, where thickness is the dimension of the blade extending perpendicularly to the camber line at each point of the camber line; superposing the thickness relationship of the real blade on the thickness relationship of the theoretical blade; and extracting the leading-edge and trailing edge thicknesses.