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.

公开(公告)号：US10190430B2

公开(公告)日：2019-01-29

申请号：US14385867

申请日：2013-04-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Francois Leglaye ,  Emeric D'Herbigny

IPC: F01D11/00 ,  F01D9/02 ,  F23R3/00

Abstract: A turbine engine, a turbojet, or a turboprop engine, including an annular combustion chamber defined by an inner shell and an outer shell, a turbine distributor arranged downstream of the combustion chamber, with a downstream end of the outer shell and/or of the inner shell of the chamber including a radial rim arranged opposite a radial rim of an upstream end of the distributor, a sealing mechanism including at least one strip extending between the rims to provide a seal between the combustion chamber and the distributor. The sealing strip extends axially and circumferentially between the rims and bears sealingly against free ends of the rims.