US 11,913,378 B2
Assembly for a turbomachine
Nicolas Jérôme Jean Tantot, Moissy-Cramayel (FR); Xavier Carbonneau, Toulouse (FR); Philippe Gérard Chanez, Moissy-Cramayel (FR); Nicolas Garcia Rosa, Toulouse (FR); Alejandro Martin Pleguezuelo, Toledo (ES); and Nicolas Joseph Sirvin, Moissy-Cramayel (FR)
Assigned to INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE, Toulouse (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/768,933
Filed by INSTITUT SUPERIEUR DE L AERONAUTIQUE ET DE L ESPACE, Toulouse (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 15, 2020, PCT No. PCT/FR2020/051841
§ 371(c)(1), (2) Date Apr. 14, 2022,
PCT Pub. No. WO2021/074535, PCT Pub. Date Apr. 22, 2021.
Claims priority of application No. 1911490 (FR), filed on Oct. 15, 2019.
Prior Publication US 2023/0349323 A1, Nov. 2, 2023
Int. Cl. F02C 7/04 (2006.01); B64D 29/00 (2006.01); B64D 33/02 (2006.01); F02C 7/042 (2006.01)
CPC F02C 7/042 (2013.01) [B64D 29/00 (2013.01); B64D 33/02 (2013.01); B64D 2033/0233 (2013.01); B64D 2033/0286 (2013.01)] 13 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine comprising:
a nacelle extending along a longitudinal axis and comprising an intake lip defining an air intake; and a device comprising:
a first slat presenting a downstream surface; and
a second slat presenting an upstream surface;
wherein the first slat and the second slat are mobile in translation along the longitudinal axis relative to the nacelle between:
a first position wherein the first slat forms the intake lip and the second slat extends inside the nacelle; and a second position wherein the first slat extends at a distance from the intake lip and the second slat forms the intake lip so as to define an airflow channel extending between the downstream surface and the upstream surface.