公开(公告)号：US20170129616A1

公开(公告)日：2017-05-11

申请号：US15412607

申请日：2017-01-23

Applicant: SAFRAN NACELLES

Inventor： Caroline COAT-LENZOTTI ,  Olivier KERBLER ,  Hakim MAALIOUNE ,  Jean-Paul RAMI

IPC: B64D15/12 ,  B05D1/28 ,  B05D1/02 ,  B64F5/10

CPC classification number: B64D15/12 ,  B05D1/02 ,  B05D1/28 ,  B64F5/10

Abstract: A method for installing a de-icing system on the skin of an aircraft element is provided, which involves applying to the skin several independent layers of solid and/or fluid materials which are hardened in succession, and which comprise at least one layer of controlled electrical resistivity material, which takes electrodes that conduct an electric current originating from an external source, which is flanked on each side by layers of an electrically insulating material.

公开(公告)号：US20210285382A1

公开(公告)日：2021-09-16

申请号：US17126257

申请日：2020-12-18

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Jean-Paul RAMI

IPC: F02C9/16 ,  H04B10/116 ,  B64D31/02 ,  B64D47/02

Abstract: The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

公开(公告)号：US20180216529A1

公开(公告)日：2018-08-02

申请号：US15940375

申请日：2018-03-29

Applicant: Safran Nacelles

Inventor： Hakim MAALIOUNE ,  Patrick GONIDEC ,  Jean-Paul RAMI

IPC: F02C7/047 ,  B64D15/04 ,  B64D33/02 ,  B64D15/06

CPC classification number: F02C7/047 ,  B64D15/02 ,  B64D15/04 ,  B64D15/06 ,  B64D33/02 ,  B64D2033/0233 ,  F01D25/02 ,  F02C6/18 ,  F02C7/14 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/62 ,  F05D2260/208 ,  Y02T50/672 ,  Y02T50/675

Abstract: The present disclosure provides a device for de-icing an air intake lip of an aircraft turbojet engine nacelle. The de-icing device includes a de-icing circuit in which a heat transfer fluid, working in a two-phase form, circulates. The de-icing circuit includes at least one device for circulating the heat transfer fluid in the de-icing circuit, a system for heating the heat transfer fluid and configured to change the phase of the fluid to a vapor phase, and an inlet conduit that opens into the lip through a rear wall and injects the vapor phase fluid into the lip. The fluid changes phase when it condenses on the front wall of the lip to de-ice the lip.

公开(公告)号：US20210078711A1

公开(公告)日：2021-03-18

申请号：US17025051

申请日：2020-09-18

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Jean-Paul RAMI ,  Hakim MAALIOUNE ,  Rémi BILLARD ,  Vincent RIGOLET ,  Jean-Denis SAUZADE

IPC: B64D15/16 ,  B64D15/22

Abstract: A method for de-icing or anti-icing an aircraft portion having at least one piezoelectric element fastened on the inner face of the aircraft portion includes, during a design phase of the aircraft portion, placing the piezoelectric element on an area of the aircraft portion to determine frequencies of resonance and increased dynamic coupling, and during the de-icing or anti-icing of the aircraft portion, the same piezoelectric element is excited according to the natural frequencies of the area.

公开(公告)号：US20200347800A1

公开(公告)日：2020-11-05

申请号：US16930524

申请日：2020-07-16

Applicant: Safran Nacelles

Inventor： Patrick GONIDEC ,  Olivier KERBLER ,  Alexandre PHI ,  Jean-Paul RAMI ,  STEPHANE TIREL ,  Jean-Baptiste GOULARD ,  Matthieu VANDERLINDEN ,  Arnaud CARLES-ESPITEAU

IPC: F02K1/62 ,  B64D29/06 ,  F02K1/76

Abstract: An improved thrust reverser for an aircraft propulsion assembly includes redirection of the air flow for performing the thrust reversal by one or more closure membranes, i.e. by thin and flexible structures deployed across the propulsion assembly. The improved thrust reverser includes at least one closure membrane arranged to deflect at least one portion of the air flow in the direction of the evacuation structure when the thrust reverser is in the reverse jet position and an intermediate structure movable in rotation relative to the fixed structure.

公开(公告)号：US20170292453A1

公开(公告)日：2017-10-12

申请号：US15630223

申请日：2017-06-22

Applicant: SAFRAN NACELLES

Inventor： Jean-Paul RAMI ,  Jérôme CORFA ,  Marc VERSAEVEL ,  François BREFORT ,  Remko MOEYS

IPC: F02C7/24 ,  F02K1/82 ,  F02C7/045

CPC classification number: F02C7/24 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0206 ,  F02C7/045 ,  F02K1/827 ,  F04D29/665 ,  F05D2220/323 ,  F05D2250/191 ,  F05D2250/25 ,  F05D2250/283 ,  G10K11/172 ,  Y02T50/672

Abstract: An acoustic attenuation panel for a turbojet engine nacelle is provided by the present disclosure. The panel includes at least one alveolar core disposed between at least one internal skin and at least one external skin. In one form, the alveolar core includes a plurality of alveoli having a helical-shaped cavity along an axis in a direction normal to at least one internal skin and at least one external skin.