Nacelle for a bypass turbomachine comprising a thrust reverser, bypass turbomachine comprising such a nacelle, and aircraft comprising at least one such turbomachine

Nacelle for an aircraft bypass turbomachine) wherein an intake air stream flows in the upstream to downstream direction, separating into a primary flow channel and a secondary flow channel, the nacelle comprising:

• a fixed annular envelope extending about a longitudinal axis (104) of the nacelle,
• a thrust reverser comprising:
• an annular movable cowl extending about the longitudinal axis and located downstream of the annular envelope, the movable cowl being able to slide relative to the annular envelope along the longitudinal axis between a closed position, wherein the movable cowl and the annular envelope jointly define an annular and continuous outer surface of the nacelle, and an open position wherein the movable cowl and the annular envelope define therebetween an opening oriented radially relative to the longitudinal axis, said opening extending circumferentially about the longitudinal axis,
• at least one first movable thrust-reversing cascade, capable of occupying a retracted position wherein, with the movable cowl in the closed position, the first cascade is housed inside the annular envelope, and an extended position wherein, with the movable cowl in the open position, the first cascade extends across the opening, such that at least a part of the secondary stream is capable of passing through the first cascade in the extended position in order to emerge outside the nacelle with a velocity that is oriented so as to generate a negative thrust along the longitudinal axis,
• the movable cowl and the or each first cascade being connected to an actuating mechanism capable of moving them together,
• wherein said actuating mechanism is designed to allow for a partial or total thrust-cancelling configuration of the thrust reverser wherein the movable cowl is moved into the open position thereof while holding the or each first cascade in the retracted position thereof, and in that in said thrust-cancelling configuration, the opening is occupied by at least one second thrust-reducing cascade of the thrust reverser, in such a way that the secondary stream passing through the opening emerges outside the nacelle with a velocity that is oriented so as to generate a substantially zero or positive thrust along the longitudinal axis.