Abstract: A heat exchanger of the air/oil type, for an annular air stream of a turbomachine, comprising a heat exchange zone with oil passages and heat exchange surfaces with the air, said heat exchange zone forming an axial air passage and having a profile facing the air flow and included in a plane perpendicular to said air flow, said profile of the exchange zone thermal being in an arc of a circle so as to be able to be arranged in the annular air stream, remarkable in that said heat exchanger comprises on a radially internal or external face of the exchange zone thermal, an oil inlet and an oil outlet, the oil passages comprising several paths between said oil inlet and said oil outlet, distributed along the profile in circular arc of the heat exchange zone.

Abstract: An axial turbomachine, comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called a secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow, the tertiary flow being in a tertiary flow vein radially external to said primary flow, delimited by an internal wall and an external wall; and an air/oil type heat exchanger, disposed in the tertiary flow vein. The heat exchanger comprises several angular sectors, each angular sector comprising an oil inlet on the internal wall at an angular end of said sector, and an oil outlet on said internal wall at an opposite angular end of said sector.

Abstract: An axial turbomachine comprising a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a flow of radially external air, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary flow and a tertiary flow flow in a tertiary flow vein radially external to said primary flow; and a heat exchanger disposed in the tertiary flow vein. The heat exchanger extends radially and axially in an upstream section section of the tertiary flow vein, having a divergent longitudinal section, said tertiary flow vein comprises a downstream section presenting a converging longitudinal section, following the tertiary flow.

Abstract: An axial turbomachine including a first separation nozzle capable of separating an incoming air flow into a radially internal air flow and a radially external air flow, called secondary flow; a second separation nozzle capable of separating the radially internal air flow into a primary f flow and a tertiary flow, said tertiary flow being in a tertiary flow vein radially external to said flow primary; and an air/oil type heat exchanger disposed in the tertiary flow stream and including heat exchange surfaces with air and oil passages extending in said tertiary flow stream; and structural arms extending radially through the tertiary flow vein. Each structural arm has in the tertiary flow vein a cross section with a downstream portion having a width decreasing towards the downstream, the heat exchanger being adjacent to said downstream portions of the structural arms.

Abstract: A heat exchanger includes a plurality of fins arranged as a network and delimiting corridors, and an envelope having an internal wall and an external wall, the internal and external walls delimiting between them a channel for a flow of a first fluid in a main direction, the network of fins being arranged in the channel and connected to the internal and external walls, at least one passage for a flow of a second fluid being embedded in at least one of the internal and external walls, the channel being, in the main direction, divergent and then convergent.

Abstract: The invention relates to a method of manufacturing at least one tank with a shell, in particular a turbojet engine oil tank. The method comprises the following stages: (a) definition of different shell sections (58) for each tank, whereof a first shell section (58) has a recess (60) and a second shell section (58) a boss (62); (b) production of the shell sections (58) by additive manufacturing in which the boss (62) on the second shell section is produced in the recess (60) in the first shell section; then (c) welding of the sections (60) one to the other.

Abstract: The invention relates to a turbojet engine oil tank (30). The tank (30) comprises a main chamber and an envelope (34) delimiting the main chamber, and a fixing portion (44) for example with fixing flanges (46) and a branch (48). The envelope (34) features in particular an envelope part (34) relative to which the fixing portion (44) projects. The envelope part (34) and the fixing portion (44) are produced by layered additive fabrication so as to be in one piece. The invention also relates to a method of fabricating an oil tank (30).

Abstract: An oil tank of a turbine engine, particularly of an aircraft turbojet includes an external wall forming a generally curved main cavity. This cavity includes an arched sensor for electrically measuring the oil level, for example in a capacitive manner. Said arched sensor matches the curvature of the main cavity in order to be integrated therein. Sensor supporting arms distributed along the curvature of the arched sensor and/or an arched sleeve with an arched cavity receive the arched sensor. A turbine engine is provided with an oil tank, as well as a method for mounting a sensor in an oil tank.

Abstract: A heat exchanger includes a plurality of fins arranged as a network and delimiting corridors, and an envelope having an internal wall and an external wall, the internal and external walls delimiting between them a channel for a flow of a first fluid in a main direction, the network of fins being arranged in the channel and connected to the internal and external walls, at least one passage for a flow of a second fluid being embedded in at least one of the internal and external walls, the channel being, in the main direction, divergent and then convergent.

Abstract: An oil tank of a turbine engine, particularly of an aircraft turbojet includes an external wall forming a generally curved main cavity. This cavity includes an arched sensor for electrically measuring the oil level, for example in a capacitive manner. Said arched sensor matches the curvature of the main cavity in order to be integrated therein. Sensor supporting arms distributed along the curvature of the arched sensor and/or an arched sleeve with an arched cavity receive the arched sensor. A turbine engine is provided with an oil tank, as well as a method for mounting a sensor in an oil tank.

Abstract: The invention relates to a turbojet engine oil tank (30). The tank (30) comprises a main chamber and an envelope (34) delimiting the main chamber, and a fixing portion (44) for example with fixing flanges (46) and a branch (48). The envelope (34) features in particular an envelope part (34) relative to which the fixing portion (44) projects. The envelope part (34) and the fixing portion (44) are produced by layered additive fabrication so as to be in one piece. The invention also relates to a method of fabricating an oil tank (30).

Abstract: The invention relates to a method of manufacturing at least one tank with a shell, in particular a turbojet engine oil tank. The method comprises the following stages: (a) definition of different shell sections (58) for each tank, whereof a first shell section (58) has a recess (60) and a second shell section (58) a boss (62); (b) production of the shell sections (58) by additive manufacturing in which the boss (62) on the second shell section is produced in the recess (60) in the first shell section; then (c) welding of the sections (60) one to the other.