Snecma

Safran Aircraft Engines

Nicolas Potel

Nicolas Alain Bader

Sebastien Gameiro

Brice Andre

Philippe Vertenoeuil

Regis Michel Paul Deldalle

Laurent Gilbert Yves Hodinot

Lauranne Sophie Mottet

Nicolas Gomes

Sébastien Gameiro

Hichem Belghagi

Thierry Poix

Régis Michel Paul Deldalle

Guillaume Mathon Margueritte

Laurent Gilbert Hodinot

Regis Michel Deldalle

A turbomachine fuel circuit including: a low pressure pump; a high pressure pump; a low pressure conduit connecting the low pressure pump to the high pressure pump; a high pressure conduit supplied by the high pressure pump, in which a component is arranged; a mechanism for testing operation of the component; a check valve capable of closing off a segment of the conduit when the pressure in the low pressure conduit is less than a predetermined threshold value; and the testing mechanism is capable of detecting that the check valve at least partly closes off the segment.

Fuel circuit comprising means for controlling a pump

A method for regulating oil cooling within an oil cooling device of a turbomachine including a first heat exchanger mounted in series with a second heat exchanger, the first heat exchanger being an oil/air exchanger while the second heat exchanger is an oil/fuel exchanger, each heat exchanger having an oil inlet and an oil outlet, a bypass directly connecting the oil inlet of the first heat exchanger to the oil outlet of the first heat exchanger, and a flow regulator to regulate the flow rate of oil flowing through the bypass. Circulation of oil though the bypass is allowed by means of the flow regulator when the oil temperature is less than or equal to a predetermined temperature comprised between 70&#xb0; C. and 90&#xb0; C., preferably equal to about 80&#xb0; C.

Method and device for regulating the cooling of oil in a turbomachine

A device for controlling feed of fluid to equipment, such as a heat exchanger, the device including: a fluid slide valve mounted in a fluid circuit including a slide movable between two positions, a first position in which it allows the fluid to flow through the equipment, and a second position in which it prevents the fluid from flowing through the equipment; a laminar flow constriction arranged in the fluid circuit upstream from the slide valve; and a drive mechanism moving the slide of the slide valve between its two positions by head loss of the fluid in the laminar flow constriction.

Fluid circuit in a turbine engine

A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

A fuel feed circuit for an aeroengine, the circuit including a high-pressure pumping system for delivering fuel at high pressure to combustion chamber injectors, the high-pressure pumping system including first and second positive displacement gear pumps driven simultaneously by the engine. A hydraulic switch member is interposed between respective outlets of the pumps, which makes it possible, in one state, to combine outlet flows from the two pumps to deliver fuel at high pressure to the combustion chamber injectors, and in another state, to discharge some or all of outlet flow from the first pump to a low-pressure feed line, an electrical control member serving to cause the hydraulic switch member to pass from one state to the other.

Fuel feed circuit for an aeroengine having a high pressure pump system with two pumps

A method tracking positive displacement efficiency of a high pressure positive displacement pump in a hydraulic regulator system of a turbomachine delivering a flow rate based on an engine speed of the turbomachine, the flow rate delivered to an actuator actuating variable geometry vanes of the turbomachine and to a bypass valve feeding engines of the turbomachine, the method including: starting engines of the turbomachine at a low engine speed, the valve being closed; using a computer to order a movement of the actuator; progressively increasing the engine speed until the flow rate reaches a predetermined value sufficient for opening the valve; storing in the computer a position of the actuator and the engine speed corresponding to opening of the valve; repeating the preceding operations at successive instants during a lifetime of the engines; and replacing the high pressure positive displacement pump when the engine speed exceeds a predetermined value.

Method of determining whether to replace a high pressure pump in a hydraulic regulation system of a turbomachine

The method consists, based on an operating parameter of the turbojet engine, in:

Method for monitoring the clearance of a kinematic link between a control member and a receiving member

A detection method of a breakdown of a pressure relief valve of a fuel injection circuit for a turbomachine, the injection circuit including a low pressure stage and a high pressure stage, the low pressure stage having an inlet and an outlet, the high pressure stage having an inlet and an outlet, the low pressure stage being connected to the high pressure stage, the pressure relief valve being connected in parallel with respect to the high pressure stage, the injection circuit further including a recirculation loop including an inlet connected to the outlet of the high pressure stage and an outlet connected to the outlet of the low pressure stage, the method including measuring a differential pressure in the injection circuit.

Method for monitoring a pressure relief valve of a fuel injection circuit for a turbomachine

A device monitors an obstruction of two fluid filters of a fluid circulation system of a gas turbine engine of an aircraft. A first obstruction sensor sends a first detection signal of an obstruction of a first filter. A second obstruction sensor sends a second detection signal of an obstruction of a second filter. A processor includes a monitoring input to measure the first and second detection signals. The first obstruction sensor includes a Wheatstone bridge including a strain gauge resistor. The second obstruction sensor is connected in parallel with the strain gauge resistor. The first detection signal is sent over a first predetermined variation range. The second detection signal is sent over a second predetermined variation range, distinct from the first variation range. The processor identifies the obstruction of one of the fluid filters as a function of one of the variation ranges of the detection signals.

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Maisons Alfort, France

Nicolas Potel