公开(公告)号：US20210206505A1

公开(公告)日：2021-07-08

申请号：US17188809

申请日：2021-03-01

Applicant: Safran Nacelles

Inventor： Hakim MAALIOUNE ,  Julien CORBIN ,  Alain NOURRISSON ,  Julien CALMELS ,  Maxime POUYET

IPC: B64D41/00 ,  G05B15/02

Abstract: An electrical control system intended for an aircraft turbojet engine nacelle includes two control modules of a single power module controlling an electric machine and an approval module linking each of the control modules to the single power module. The approval module selectively authorizes the control of the single power module by one of the control modules.

公开(公告)号：US20220186665A1

公开(公告)日：2022-06-16

申请号：US17490766

申请日：2021-09-30

Applicant: Safran Nacelles

Inventor： Julien CORBIN ,  Jean-Nicolas BOUCHOUT ,  Caroline DANG

IPC: F02C7/14 ,  F02K1/56

Abstract: An engine nacelle, for a turbojet engine of the type having a lubricant, includes a cooling system. The cooling system includes a cold source heat-exchanger, configured to exchange heat between a heat-transfer fluid and air, a heat-transfer fluid inlet duct leading into the cold source heat-exchanger, and a heat-transfer fluid outlet duct leading out of the cold source heat-exchanger. The inlet and outlet ducts are configured to form a recirculation loop between the cold source heat-exchanger and a hot source heat-exchanger, configured to exchange heat between the heat-transfer fluid and the lubricant. The cold source heat-exchanger is arranged on a movable surface of the nacelle with respect to the hot source heat-exchanger and the heat-transfer fluid inlet and outlet ducts are extendable and/or flexible to permit the relative movement between the cold source heat-exchanger and the hot source heat-exchanger.

公开(公告)号：US20220025816A1

公开(公告)日：2022-01-27

申请号：US17492783

申请日：2021-10-04

Applicant: Safran Nacelles

Inventor： Julien CORBIN ,  David PEREIRA ,  Vincent PEYRON ,  Jean-Nicolas BOUCHOUT ,  Caroline DANG ,  Nicolas CHOUQUET

IPC: F02C7/18 ,  F02C9/00

Abstract: A cooling system for cooling an aircraft turbojet engine includes a first heat-exchanger for exchanging heat between a heat-transfer fluid and a lubricant of the turbojet engine, a second heat-exchanger for exchanging heat between the heat-transfer fluid and air, and a circulation duct for circulating heat-transfer fluid in a closed circuit. The cooling system further includes at least one regulating device for regulating the heat drawn from the lubricant, controlled by a control module of the regulating device that is configured to receive information according to the various flight phases.

公开(公告)号：US20210285400A1

公开(公告)日：2021-09-16

申请号：US17184464

申请日：2021-02-24

Applicant: Safran Nacelles

Inventor： Hakim MAALIOUNE ,  Alice PORTALIER ,  Julien CORBIN

IPC: F02K1/76

Abstract: An architecture for controlling and/or monitoring at least one actuator of a mobile cowl of a thrust reverser equipping a nacelle, the actuator being driven by at least one engine, includes at least one engine sensor to provide its control according to instructions, the architecture including an electronic control system to process at least one piece of information generated by the engine sensor and to calculate, using at least this same piece of information, the position of the mobile cowl of the thrust reverser.

公开(公告)号：US20190390633A1

公开(公告)日：2019-12-26

申请号：US16562814

申请日：2019-09-06

Applicant: Safran Nacelles ,  Safran Electronics & Defense

Inventor： Hakim MAALIOUNE ,  Julien CORBIN ,  Jean-Philippe JOIGNET ,  Julien HAUTECOEUR ,  Yvon JONCOUR ,  Jean-Michel FIGUET

IPC: F02K1/76 ,  B64C13/30

Abstract: An actuation device for a thrust reverser includes thrust-reversal movable elements carried by a nacelle and displaceable between a retracted and deployed position. The actuating device includes two actuators mounted on the nacelle and connected to a motor and to the movable elements. The actuation device drives the movable elements in a retraction or deployment direction over a course of the actuators between the retracted and deployed position. The actuation device further includes locks for locking the movable elements in the retracted position and antideployment members associated with the actuators which allow free operation of the actuators in the direction of retraction and retain the actuators in the direction of deployment. The antideployment bodies further provide free operation of the actuators in the direction of deployment over part of the actuators stroke that corresponds to a shift from an over-retraction position to the retraction position of the movable elements.