公开(公告)号：US20180230949A1

公开(公告)日：2018-08-16

申请号：US15952331

申请日：2018-04-13

Applicant: Safran Nacelles

Inventor： Olivier KERBLER ,  Loïc GRALL ,  Guillaume GLEMAREC ,  Amadéo GALASSO ,  José FAUGERAS ,  Mélody SERISET

IPC: F02K99/00

CPC classification number: F02K99/00 ,  F02K1/1261 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/128 ,  Y02T50/671

Abstract: The present disclosure provides a variable section nozzle for an aircraft nacelle having a longitudinal axis. The variable section nozzle includes movable doors and at least one displacement device for displacing the movable doors between a reduced section position and a larger position. The movable doors include at least one first guide device and at least one second guide device, each operable to guide the displacement of the doors relative to a fixed structure of the nozzle. The second guide device is disposed downstream relative to the first guide device and each of the first and second guide devices provide a curvilinear path. In one form, the curvilinear paths are substantially circular and define a circular arc.

公开(公告)号：US20210003097A1

公开(公告)日：2021-01-07

申请号：US17025019

申请日：2020-09-18

Applicant: Safran Nacelles ,  Safran Aircraft Engines

Inventor： Quentin GARNAUD ,  Guillaume GLEMAREC ,  Patrick BOILEAU ,  Ludovic TOUPET

IPC: F02K1/72 ,  B64C7/02 ,  B64C1/14

Abstract: A turbofan propulsion assembly includes a thrust reverser with movable flaps. The propulsion assembly further includes an engine and a nacelle surrounding the engine, and the nacelle includes a thrust reverser with sliding cowls and thrust reverser flaps, and an inner structure. The portion of the inner structure positioned perpendicular to the thrust reverser flaps includes two halves that can open toward the exterior of the nacelle cowls.

公开(公告)号：US20220082064A1

公开(公告)日：2022-03-17

申请号：US17536480

申请日：2021-11-29

Applicant: Safran Nacelles ,  SAFRAN AIRCRAFT ENGINES

Inventor： Patrick BOILEAU ,  Pierre CARUEL ,  Gina FERRIER ,  Quentin GARNAUD ,  Guillaume GLEMAREC

IPC: F02K1/68 ,  F02K1/70

Abstract: An aircraft propulsion unit including a nacelle and a turbojet engine. The aircraft propulsion unit includes an external envelope, at least one fan casing, at least one actuator, and at least one support structure. The external envelope includes fan cowls. The fan casing cooperates with the fan cowls to define an interior space configured to house a thrust reverser configured to be displaced between a first position and a second position. The actuator configured to move the thrust reverser between the first position and the second position The support structure connects the fan cowls and the fan. The support structure includes at least one aperture configured to allow passage of part of the actuator.