Aircraft propulsion unit having thrust reverser flaps connected to an inter-compressor casing located between the engine compressors

An aircraft propulsion assembly comprising:

• a bypass turbojet having a space between passages separating a core stream flow passage and a bypass stream flow passage, and a stationary inter-compressor casing positioned upstream from said space between passages;
• a nacelle arranged around the turbojet and a downstream end of the nacelle includes an inner annular wall that defines an outside of the space between passages and an inside of the bypass stream flow passage, and an outer annular wall arranged around the inner annular wall and that defines an outside of the bypass stream flow passage, at least a portion of the inner annular wall being suitable for moving between a maintenance position wherein said portion of the inner annular wall uncovers the space between passages at least in part and a working position wherein said portion of the inner annular wall masks the space between passages;
• and
• a thrust-reverser comprising a downstream element of the outer annular wall that is movable in translation between a retracted position wherein said downstream element of the outer annular wall defines the outside of the bypass stream flow passage and a thrust-reversal position wherein bypass stream deflector elements are deployed in a racial direction, the deployment of said bypass stream deflector elements being controlled by guide rods, each of the guide rods having a first end fastened via a first hinged connection to a deflector element and a second end fastened via a second hinged connection to the stationary inter-compressor casing of the turbojet,
• wherein the stationary inter-compressor casing is axially located between an upstream stationary engine casing and said portion of the inner annular wall.