Abstract: A turbomachine comprises an inter-flow compartment extending radially between first and second intermediate walls, gas bypass ducts passing through the second intermediate wall and communicating with evacuation outlets opening up into a secondary gas flow; an oil reservoir arranged in the inter-flow compartment, and a surface air-oil heat exchanger communicating with the oil reservoir for fluid circulation. Circumferentially in relation to the inter-flow compartment, the surface air-oil heat exchanger extends at least partially between the evacuation outlets which pass through the first intermediate wall.

Abstract: An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.

Abstract: An aircraft propulsion assembly having a thrust reverser with moving guards, including an engine covered by a front cover and a rear cover that are both mobile; moving guards supported by the rear cover, the guards being covered by the front cover in normal operation, and extending into a space separating the front cover from the rear cover when the rear cover is moved to the rear; two arcuate frames, which are spaced apart and surround the engine in order to support actuators for moving the rear cover; the space located between the two arcuate frames being uncovered when the front and rear covers are moved to the front and rear; and wherein the two arcuate frames jointly support a series of elements forming steps which constitute a ladder for quick access to the top of the propulsion assembly.

Abstract: Turbine engine, comprising two structural annular casings (16, 22) which are interconnected by connecting rods (54), characterized in that the turbine engine further has at least one accessory gearbox (40) which is fixed to a first of the casings (16) and which is connected by the connecting rods to the other of the casings (22).

Abstract: An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.

Abstract: A turbomachine comprises an inter-flow compartment extending radially between first and second intermediate walls, gas bypass ducts passing through the second intermediate wall and communicating with evacuation outlets opening up into a secondary gas flow; an oil reservoir arranged in the inter-flow compartment, and a surface air-oil heat exchanger communicating with the oil reservoir for fluid circulation. Circumferentially in relation to the inter-flow compartment, the surface air-oil heat exchanger extends at least partially between the evacuation outlets which pass through the first intermediate wall.

Abstract: An aircraft propulsion assembly having a thrust reverser with moving guards, including an engine covered by a front cover and a rear cover that are both mobile; moving guards supported by the rear cover, the guards being covered by the front cover in normal operation, and extending into a space separating the front cover from the rear cover when the rear cover is moved to the rear; two arcuate frames, which are spaced apart and surround the engine in order to support actuators for moving the rear cover; the space located between the two arcuate frames being uncovered when the front and rear covers are moved to the front and rear; and wherein the two arcuate frames jointly support a series of elements forming steps which constitute a ladder for quick access to the top of the propulsion assembly.

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterized in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.

Abstract: Turbine engine, comprising two structural annular casings (16, 22) which are interconnected by means (40, 54) for absorbing thrust forces from the engine which have connecting rods (54), characterised in that said means for absorbing thrust further have at least one accessory gearbox (40) which is fixed to a first of said casings (16) and which is connected by said connecting rods to the other of said casings (22).

Abstract: Turbine engine, comprising means for absorbing the thrust forces from its engine, which comprise longitudinal connecting rods, the ends of which are connected to structural annular casings of the turbine engine, characterised in that it comprises means for supporting at least one item of equipment on said thrust-absorbing connecting rods and/or for suspending at least one item of equipment from said thrust-absorbing connecting rods.