公开(公告)号：US20200333008A1

公开(公告)日：2020-10-22

申请号：US16850114

申请日：2020-04-16

Applicant: Safran Aircraft Engines

Inventor： François Pierre Ribassin ,  Patrice André Commaret ,  Romain Nicolas Lunel ,  Christophe Pieussergues

IPC: F23R3/04

Abstract: The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.

公开(公告)号：US11441779B2

公开(公告)日：2022-09-13

申请号：US16850114

申请日：2020-04-16

Applicant: Safran Aircraft Engines

Inventor： François Pierre Ribassin ,  Patrice André Commaret ,  Romain Nicolas Lunel ,  Christophe Pieussergues

IPC: F23R3/04

Abstract: The provision of air passage holes through a wall of a gas turbomachine combustion chamber. Multi-perforations are virtually positioned and distributed, even in a first safety zone without air passage openings. Multi-perforations with a virtual inlet or outlet in this first security zone are virtually removed. According to certain criteria, at least some of said removed multi-perforations are then virtually reintegrated, and, from then on a perimeter passing through the virtual inlets and outlets of all the multi-perforations present is defined, in the direction of a primary or dilution hole to be installed, a modified safety zone is defined, then, respecting around said hole and with the freedom to reposition it within this limit, the shape of this hole is redefined.

公开(公告)号：US10883718B2

公开(公告)日：2021-01-05

申请号：US16095813

申请日：2017-04-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Romain Nicolas Lunel ,  Guillaume Aurelien Godel ,  Haris Musaefendic ,  Christophe Pieussergues ,  Francois Pierre Georges Maurice Ribassin

IPC: F23R3/14 ,  F23R3/26 ,  F23R3/28

Abstract: An air intake swirler for a turbomachine injection system includes an upstream wall and a downstream wall, both of revolution about an axis of the air intake swirler, and fins distributed about the axis and connecting the upstream wall to the downstream wall so as to delimit, between the upstream wall and the downstream wall, air inlet channels each having an inlet and an outlet. The swirler includes two aerodynamic deflectors that respectively extend the downstream walls radially outward and that have a concavity oriented upstream. The aerodynamic deflectors extend radially facing the respective inlets of the air inlet channels and thus make it possible to limit the loss of pressure of the air supplied to the air inlet channels.

公开(公告)号：US20240219028A1

公开(公告)日：2024-07-04

申请号：US18555913

申请日：2022-04-15

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clément Jean Henri Bechet ,  Emmanuel Jean André Greslin ,  Pierre André Gabriel Malbois ,  Christophe Pieussergues

IPC: F23R3/18

CPC classification number: F23R3/18

Abstract: A flame-holder device for a turbojet afterburner comprises an annular row of flame-holder arms, each having an inner branch having a free end and another end, and two outer branches which extend from the other end and diverge from one another in a direction extending from the free end to the other end, such that the inner branch transitions radially outward into the two outer branches which diverge radially outward from one another in two opposing circumferential directions, thereby forming mutually approaching areas between consecutive flame-holder arms for enabling the flame to spread from arm to arm.

公开(公告)号：US11725822B2

公开(公告)日：2023-08-15

申请号：US16423953

申请日：2019-05-28

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Romain Nicolas Lunel ,  Damien Bonnefoi ,  Christophe Pieussergues ,  Luc Namer ,  Dominique Raulin ,  Dan Ranjiv Joory ,  Benjamin Frantz Karl Villenave

IPC: F23R3/60 ,  F02C3/06 ,  F02C7/20 ,  F02C7/22 ,  F02C9/16 ,  F23R3/26 ,  F23R3/28

CPC classification number: F23R3/60 ,  F02C3/06 ,  F02C7/20 ,  F02C7/22 ,  F02C9/16 ,  F23R3/26 ,  F23R3/28 ,  F05D2220/323 ,  F05D2260/30

Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).

公开(公告)号：US11846420B2

公开(公告)日：2023-12-19

申请号：US17610288

申请日：2020-05-12

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Julien Marc Matthieu Leparoux ,  Christophe Pieussergues

IPC: F23R3/06 ,  F23R3/00 ,  F23R3/50 ,  F02C7/266 ,  F23R3/60

CPC classification number: F23R3/06 ,  F23R3/002 ,  F23R3/50 ,  F02C7/266 ,  F23R2900/03042

Abstract: A combustion chamber for a turbomachine including an annular casing delimiting an inner volume of the combustion chamber and provided with a chimney extending to the outside of the inner volume and delimiting a passage for a penetrating part, and a bushing mounted floating on the chimney, further includes: a main air collection chamber open to the upstream arranged facing the downstream portion of the chimney; and a through-opening of the annular casing, connecting the inner volume to the main air collection chamber. The air collected by the main air collection chamber is injected into the inner volume via the through-opening and can cool an annular casing zone downstream of the chimney.

公开(公告)号：US10233836B2

公开(公告)日：2019-03-19

申请号：US15026010

申请日：2014-10-02

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Francois Leglaye ,  Olivier Bidart ,  Pierre-Francois Pireyre ,  Christophe Pieussergues

IPC: F02C1/00 ,  F02C7/04 ,  F23R3/04 ,  F23R3/06 ,  F23R3/16 ,  F02C7/264 ,  F02C3/04 ,  F02C7/18 ,  F02P15/00

Abstract: A device for cooling of an annular wall of a turbomachine combustion chamber provided with micro-perforations, and in particular the cooling of a region of the wall facing a wake induced by an ignition plug, the device includes, a deflector designed to divert air immersing the ignition plug towards a median plane of the wake and towards the annular wall of the combustion chamber, so as to increase the air pressure within the wake in proximity to the annular wall.