公开(公告)号：US11851200B2

公开(公告)日：2023-12-26

申请号：US17253441

申请日：2019-06-25

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Hervé Simonotti

IPC: F02C7/25 ,  B64D27/26 ,  F02C7/20 ,  B64D27/18 ,  B64D45/00 ,  F02C7/28

CPC classification number: B64D27/26 ,  F02C7/20 ,  B64D27/18 ,  B64D2045/009 ,  F02C7/25 ,  F02C7/28 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2240/90

Abstract: A fire resistance device designed to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling with which the turbomachine is equipped, the connecting cowling being designed to connect an upstream ring, delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device can be produced as a single piece and includes two contact lips which extend along different lines, the first lip having a C-shaped cross-section.

公开(公告)号：US11585292B2

公开(公告)日：2023-02-21

申请号：US16969228

申请日：2019-02-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Thomas Claude Broage ,  Florent Robert André Godin ,  Joël François Roudil ,  Hervé Simonotti

IPC: F02K1/80 ,  B64D27/10 ,  F02C7/28 ,  F02K3/02

Abstract: An outer shroud of an intermediate casing for a dual flow turbine engine for an aircraft, the shroud including: an annular downstream portion provided with a shroud opening passing through an annular downstream edge of the shroud; a connecting member (50) attached to the annular downstream portion, and intended to attach an arm that passes through a secondary flow path; an air-sealing and fire-resistance device including: a portion including: a pad arranged in a hollow annular area of the annular downstream edge of the shroud; a blade protruding from the pad and clamped between a circumferential end and the radially outer end of the arm, a leaf spring (pressing the pad into the hollow annular area.

公开(公告)号：US11746706B2

公开(公告)日：2023-09-05

申请号：US17299963

申请日：2019-11-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Faouzi Aliouat ,  Hervé Simonotti

IPC: F02C7/28 ,  F16J15/06 ,  F01D11/00 ,  F01D25/26 ,  F16J15/02

CPC classification number: F02C7/28 ,  F01D11/003 ,  F01D11/005 ,  F01D25/265 ,  F16J15/027 ,  F16J15/061 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/291 ,  F05D2300/437 ,  F05D2300/614

Abstract: An air-sealing device intended to be inserted between an aircraft dual-flow turbine engine casing element and a nacelle element, the sealing device including an attachment tab at the end of which is located a sealing portion having an outer surface intended to be contacted by the casing element and the nacelle element, and an inner surface defining a cavity. The inner surface defines at least one protuberance extending inside the cavity.

公开(公告)号：US11920519B2

公开(公告)日：2024-03-05

申请号：US17311539

申请日：2019-11-29

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Hervé Simonotti

IPC: F02C7/25 ,  B64D29/02

CPC classification number: F02C7/25 ,  B64D29/02

Abstract: A fire resistance device intended to be placed between a mounting strut of a double-flow aircraft turbomachine and a connecting cowling equipping this turbomachine, the connecting cowling being intended to connect an upstream ring delimiting an inter-flow compartment, to an arm that extends radially across a secondary flow of the turbomachine. The device includes two contacting lips extending along different lines, of which a first lip with a C-shaped section is integrated within a contact structure, and a second lip including at its end a protruding blocking portion protecting the contact structure.

公开(公告)号：US11480107B2

公开(公告)日：2022-10-25

申请号：US16970035

申请日：2019-02-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Bruno Alexandre Didier Jacon ,  Baghdad Achbari ,  Thomas Claude Broage ,  Hervé Simonotti ,  Soufien Akachkachy ,  Charles Maurice Jean-Louis Cheret ,  Joseph Taglialavore

IPC: F02C7/25 ,  F02C7/28 ,  F01D9/06 ,  F01D25/16 ,  F02K1/80 ,  F02K3/06

Abstract: A fire resistance device is intended to be interposed between an upstream end of an aircraft turbine engine mounting structure and a cowling of the turbine engine delimiting an inter-flow compartment.