Abstract: A thrust reverser of a nacelle of a turbojet engine of an aircraft extending about a longitudinal axis and including a fixed structure and at least one door which is rotatable between a closed position and an open position and including a downstream frame spaced axially from a downstream end edge of the door by an axial clearance parallel to the longitudinal axis. The thrust reverser includes a system for diverting fluids to the exterior including at least one projection fixed onto the door or the other fixed structure and extending into the axial clearance and towards one of the fixed structure or the door, while leaving an axial gap between a free end of said projection and one of the fixed structure or the door.

Abstract: A device for securing at least one thermal protection mat to an internal fixed structure of a nacelle includes at least one removable fastening element for securing the at least one thermal protection mat to the internal fixed structure designed to be arranged between the mat and the internal fixed structure. The device includes at least one gripping element connected to the removable fastening element to project relative to the mat on the opposite side to the internal fixed structure, the removable fastening element being intended to be detached from the internal fixed structure by a pulling force exerted on the gripping element.

Abstract: A device for securing at least one thermal protection mat to an internal fixed structure of a nacelle includes at least one removable fastening element for securing the at least one thermal protection mat to the internal fixed structure designed to be arranged between the mat and the internal fixed structure. The device includes at least one gripping element connected to the removable fastening element to project relative to the mat on the opposite side to the internal fixed structure, the removable fastening element being intended to be detached from the internal fixed structure by a pulling force exerted on the gripping element.

Abstract: 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 channeling 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.

Abstract: 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.