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：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.