Inner side of the annular bypass duct of a turbojet engine and method for assembling such an annular duct

The wall has a set of heat exchangers, and a separator nose (10) for separating a primary flow and a secondary flow. An intermediate casing supports a rotor (2), and a wall portion is placed between a leading edge of the nose and the intermediate casing. A surface air-oil heat exchanger forms an annular segment of the wall portion, and a support arm (8) is fixed on the intermediate casing. The support arm extends from the intermediate casing towards the leading edge. Independent claims are also included for the following: (1) a turbojet engine comprising a nacelle (2) a method for cooling oil of a lubrication and cooling circuit of a bypass axial turbo machine.