Patent ID: 11913378
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Transport (Mechanical engineering)
Classification: CPC F  B | IPC B  F

Claim 0:
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.