Snecma

Hispano Suiza

Pascal Marly

Alain Tiepel

Gilles Le Gouellec

Laurent Gilbert Yves Hodinot

Denis Louis Bocquet

Caroline Frantz

José Roland Rodrigues

Pascal LeBlanc

Celine Marie Anne Issert

A propeller for an aircraft turbine engine, comprising means for adjusting the pitch of the blades comprising a hydraulic actuator borne by the rotor and including a cavity and a piston displaceable in said cavity and dividing said cavity into two chambers, as well as means for limiting the stroke of the piston in order to prevent displacement of said blades in a predetermined direction beyond a predetermined limiting pitch angle, and comprising hydraulic connection means with which both chambers may be put into communication with each other as soon as the pitch angle of the blades becomes equal to said predetermined limiting pitch angle during the displacement of said blades in said predetermined direction, these hydraulic connection means being borne by said rotor of the propeller.

Propeller and system of counter-rotating propellers comprising improved means for limiting pitch, and a turbine engine comprising them

Turbomachine blade incidence control system including a fluidic cylinder with a first and a second chamber and having a pressurized fluid network adapted to selectively supply pressurized fluid to the first and/or the second chamber, the fluid network having one fluid routing device having a first normal position and a second protection position. The fluidic cylinder includes a fluid inlet positioned to be in fluid communication with the first chamber when the fluidic cylinder is in the blocked position, the routing device being adapted to set up a fluid communication between the inlet and the second chamber when it is in the protection position and to inhibit the fluid supply to the inlet when it is in the normal position.

Turbomachine blade incidence control system and turbomachine

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

Method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

The actuator () comprises a slide () carrying at least two stages () and being capable of sliding in a cylinder and two control chambers () connected to respective use holes (U, U) of an electrically controlled servo-valve hydraulic distributor (). The control chambers () are each situated on one side of a respective stage and an intermediate chamber connected to high or low pressure is situated between the other sides of the stages. In the event of electrical control failure, the distributor () slide is taken to a safety position in which the control chambers () of the actuator () are at the same low or high pressure opposed to that applying in the intermediate chamber () so that each stage of the actuator slide is then subjected to high pressure on one side and to low pressure on the other side. Sealing between each actuator slide stage () and the actuator cylinder () is carried out by a dynamic seal () producing a frictional force between stage and cylinder, depending on the difference between the pressures exerted on the two sides of the stage so that, in the event of electrical control failure, the actuator slide valve is immobilized in its position at the moment of the failure ('fail freeze'). The actuator () can be an aeronautical engine fuel metering unit.

Actuator position control device using a fail freeze servo-valve

A system for injecting fuel into a turbomachine comprising N fuel injectors placed in a combustion chamber of the turbomachine and fed from a fuel tank, the injection system further comprising, interposed between the N injectors and the tank, a single pumping means for taking fuel from the tank and delivering N metered flow rates of fuel to the injectors.

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Melun, France

Pascal Marly