AIRCRAFT PROPULSION ASSEMBLY

摘要

The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channelling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.

主权项

1. An aircraft propulsion unit, including a bypass turbojet engine equipped with a nacelle, the turbojet engine including a structure defining a first portion of a secondary flow path intended to channel a secondary flow, the nacelle including a structure defining a second portion of the secondary flow path, wherein the structure of the nacelle defining the second portion of the secondary flow path is arranged in such a way that the first portion and the second portion of the secondary flow path are offset angularly at an angular offset value about a longitudinal axis of the engine when the bypass turbojet engine is stopped.