FIELD: transport machine building.
SUBSTANCE: invention provides an aircraft power plant (2) comprising double-flow turbojet (4) having a fixed inter-compressor body (52), located in front of space (48) between channels. Apparatus also comprises nacelle (6) comprising, on downstream end, inner wall (28), which forms external part of space between channels and internal part of flow channel (32) of external circuit flow, and external wall (30), arranged around inner wall and forming external part of flow path of external circuit flow, wherein at least a portion of the inner wall is movable between a servicing position and an operating position. Apparatus also comprises thrust reverser (8) comprising a downstream member of the outer wall, which is configured to rectilinearly move between the retracted position and the thrust reversal position, in which it allows elements (46) of external flow stream deflector to unfold in radial direction, wherein deployment of flow deflector elements is controlled by guide rods (50), each of which has first end, attached by means of first hinge joint (56) to deflector element, and second end, attached by second hinge joint (54) to inter-compressor housing (52) of turbojet engine.
EFFECT: proposed is aircraft power plant.
5 cl, 5 dwg
