Safran Aircraft Engines

Snecma

Sebastien Christophe Chalaud

Thierry Georges Paul Papin

Cedric Zaccardi

Mohamed-Lamine Boutaleb

Eric Pierre Georges Lemarechal

Michel Gilbert Roland Brault

Arnaud Nicolas Negri

Nathalie Nowakowski

Romain Guillaume Cuvillier

Guillaume Patrice Kubiak

Nils Edouard Romain Bordoni

Mohammed-Lamine Boutaleb

Loic Pora

Clement Bernard

Gwenole Yann Le Pache

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.

Method for controlling the supply of fuel to a combustion chamber of a turbine engine, fuel supply system and turbine engine

A feed system for feeding lubricating oil to members of a turbine engine including a reduction gearbox, the feed system including a nonpositive-displacement pump device for connecting upstream to an oil tank and driven in rotation at a speed that is not correlated with an operating speed of the turbine engine; a separator node connected to the outlet of the nonpositive-displacement pump device; a first delivery branch for lubricating the RGB connected to the nonpositive-displacement pump device via the separator node; a second delivery branch for lubricating other members connected to the nonpositive-displacement pump device via the separator node, the second delivery branch including a positive-displacement pump; and at least one fluid metering device having a metering slot fed by the nonpositive-displacement pump device via the separator node for the purpose of feeding the RGB.

System and method for supplying lubrication fluid to at least one member of an aircraft propulsion assembly

A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.

Turbofan comprising a simplified bearing lubrication assembly

A supply system for supplying a turbomachine with fluid. The supply system includes at least one centrifugal pump and a fluid recirculation branch. The fluid recirculation branch includes an inlet situated downstream of the centrifugal pump and an outlet situated upstream of the centrifugal pump or fluidically connected with a node situated upstream of the centrifugal pump, in such a way that at least one portion of the fluid circulates in the centrifugal pump. The fluid recirculation branch includes a valve situated between the inlet and the outlet, the valve including a shutter configured to open/close as a function of the temperature of the fluid.

Recirculation of fluid through a turbomachine centrifugal pump

The invention concerns a fuel system () for a turbomachine comprising: &#x2014;a control circuit (), &#x2014;a main circuit (), &#x2014;a flow rate regulator (), suitable for regulating the flow of fuel in the control circuit () and in the main circuit () depending on the speed of the turbomachine, and &#x2014;a drain tank () being designed to draw fuel from, store fuel in and drain fuel into the main circuit () on the basis of the pressure difference between the main circuit () and the tank () or the high-pressure pump () to which it is connected.

Multipoint fuel injection system for a turbomachine and associated regulation method

A multi-point fuel injection device for an aircraft engine, including an inlet line, at least two injection lines, and a purge line, a fuel distributor member connected to each line and including a moveable element which includes an injection passage, in which the moveable element additionally includes a purge passage, and is configured to adopt a first range of positions in which the injection passage interconnects the inlet line and the injection lines, and a second range of positions in which the injection passage interconnects the inlet line and at least a first injection line while the purge passage interconnects the purge line and at least a second injection line, the device additionally includes an actuator adapted to move the moveable element into a safety position when a failure of the distribution member is detected, the injection passage interconnecting, in this safety position of the moveable element, the inlet line and the first injection line while the purge passage does not interconnect the purge line to any of the injection lines.

Multi-point injection device for an aircraft engine

A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.

Output director vane for an aircraft turbine engine, with an improved lubricant cooling function using a heat conduction matrix housed in an inner duct of the vane

A guide vane for a dual flow aircraft turbine engine includes an aerodynamic part. The aerodynamic part includes an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. The aerodynamic part is embodied as a single piece, and includes heat transfer fins arranged in the duct expanding substantially parallel to a direction of the duct. The fins are spaced from each other depending on the direction of the duct and a transversal direction of the vane, so that at least some of the fins are arranged substantially staggered.

Outlet guide vane for aircraft turbine engine, presenting an improved lubricant cooling function

A system of injecting fuel into the combustion chamber of an engine, including at least two fuel circuits, one permanent flow circuit and one intermittent flow circuit, fuel proportioning and distribution devices for proportioning fuel and distributing fuel between the two circuits and a controller. When an order to fill circuits with fuel after the circuit with intermittent flow has been drained is received, the controller is adapted to control the proportioning and distribution devices to obtain a predetermined fuel flow higher than the flow corresponding to the filling order and to supply the resulting surplus of fuel to the intermittent flow circuit for a predetermined duration.

Method and system for injecting fuel into an engine combustion chamber

A system for supplying a turbomachine with fluid, the supply system including a low-pressure pumping unit intended to increase the pressure of the fluid flowing toward a downstream circuit. The downstream circuit divides at an inlet node, situated between the low-pressure pumping unit and the high-pressure volumetric pump, into a circuit supplying an injection system and a variable geometries supply circuit. The circuit supplying the injection system includes a high-pressure volumetric pump. The variable geometries supply circuit is configured to convey the fluid toward variable geometry from the inlet node to an outlet node connecting the variable geometries supply circuit to the upstream circuit between two pumps of the low-pressure pumping unit.

Variable geometries fluid supply circuit for a turbomachine without volumetric pump

The principal object of the invention is a method for managing the operation of a metering unit of a turbomachine fuel injection system, characterized in that a channel of the metering unit is selected according to the reliability of the injection system's flowmeter, determined by reliability conditions of the flowmeter providing information as to whether or not there is confidence in the flowmeter.

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Vincennes, France

Sebastien Christophe Chalaud