Abstract: A heat exchange system for a turbine engine is provided. The heat exchange system includes a cavity having an air intake, a heat exchanger arranged in the cavity and having a first circuit in which a first fluid can circulate, a movable flap mounted at the air intake and moving between two positions permitting or preventing, respectively, the circulation of air flow in the cavity, and a control device having a movable member configured to drive the movement of the movable flap. The control device can be arranged in the heat exchanger supply circuit and configured so as to permit or prevent the circulation of the first fluid to the heat exchanger and simultaneously move the movable flap between at least one of the two positions.

Abstract: An aircraft turbine engine assembly, including a lubricating oil circuit and a fuel supply device, the assembly also including a passive bypass valve enabling the oil to bypass an exchanger, the valve including a valve body and a piston arranged to move in a sliding space defining a first actuating chamber supplied with oil from the oil circuit, as well as a second actuating chamber supplied with fuel from the device, the valve being configured so that when the differential pressure between the oil pressure in the first actuating chamber and the fuel pressure in the second actuating chamber drops below a predetermined value of differential pressure, the piston moves from a normal operating position to an exchanger bypass position.

Abstract: An aircraft propulsion assembly includes a turbine engine surrounded by a nacelle with an annular air-intake lip extending around the turbine engine by two annular walls, inner and outer, respectively, intended for being swept across by air flows at least when the aircraft is in flight. The inner and outer walls each includes or supports at least one network of pipes forming heat exchangers. The inner wall pipe network having liquid outlet connected with a liquid intake of the outer wall pipe network. The propulsion assembly further includes means for circulating the liquid, connected to at least one liquid intake of the network of pipes of the inner wall.

Abstract: An assembly for an aircraft turbine engine includes a fan drive reduction gear and a lubrication system including: a reduction gear housing; a lubricant tank; a lubricant supply circuit including a feed pump; and a lubricant recovery circuit including a pump for recovering lubricant from the reduction gear housing. The recovery circuit includes a lubricant distributor, including: a lubricant inlet communicating with a lubricant outlet of the housing; an air inlet; and a distributor outlet, the distributor being able to adopt a lubricant recovery configuration and a configuration for retaining the lubricant in the housing.

Abstract: An assembly for a fluid circuit of a turbine engineincludes a main branch, a fluid control valve, and a bypass branch which is arranged in parallel to the main branch. The fluid control valve includes a main outlet which is fluidly connected to the main branch and a bypass outlet which is fluidly connected to the bypass branch. The fluid control valve including a shutter, a spring for biasing the shutter, and control members for electrically controlling the shutter to a main open position or a bypass position. The spring for biasing the shutter is configured to bias the displacement of the shutter to the bypass position when a fluid pressure value is lower than a first threshold value.

Abstract: A method for controlling the fuel injection of a turbine engine using a fuel supply circuit. The supply circuit includes a pilot injection line and a main injection line. During a transition of the supply distribution between the pilot injection line and the main supply line, the method includes the following steps: a) determining at least a minimum value to be maintained for a pressure value; b) determining at least one hydraulic quantity of the supply circuit; c) based on the determined hydraulic quantity of the supply circuit, calculating a calculated fuel supply distribution value corresponding to the minimum value to be maintained; and switching the fuel supply distribution to the calculated fuel distribution value.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: A method for controlling the fuel injection of a turbine engine using a fuel supply circuit. The supply circuit includes a pilot injection line and a main injection line. During a transition of the supply distribution between the pilot injection line and the main supply line, the method includes the following steps: a) determining at least a minimum value to be maintained for a pressure value; b) determining at least one hydraulic quantity of the supply circuit; c) based on the determined hydraulic quantity of the supply circuit, calculating a calculated fuel supply distribution value corresponding to the minimum value to be maintained; and switching the fuel supply distribution to the calculated fuel distribution value.

Abstract: A guide vane for an aircraft turbomachine, the aerodynamic part of the vane being defined by an extrados body and an intrados body, the part comprising an internal lubricant cooling passage equipped with flow disturbing studs, including a first series of studs made in a single piece with the extrados body, and a second series of studs made in a single piece with the intrados body, the studs of the second series defining a second inter-stud space between them through which studs of the first series pass while the studs of the second series pass through the first inter-stud space. Furthermore, the end of the studs is located at a distance from the intrados body, and the end of the studs is located at a distance from the extrados body.

Abstract: A guide vane for an aircraft turbomachine, the aerodynamic part of the vane being defined by an extrados body and an intrados body, the part comprising an internal lubricant cooling passage equipped with flow disturbing studs, including a first series of studs made in a single piece with the extrados body, and a second series of studs made in a single piece with the intrados body, the studs of the second series defining a second inter-stud space between them through which studs of the first series pass while the studs of the second series pass through the first inter-stud space. Furthermore, the end of the studs is located at a distance from the intrados body, and the end of the studs is located at a distance from the extrados body.