Safran Aircraft Engines

Jean-Loïc Hervé Lecordix

Daniel-Ciprian Mincu

Anthony Binder

Nicolas Joseph Sirvin

Eva Julie Lebeault

Philippe Gérard Chanez

Frédéric Dautreppe

Tangi Brusq

Yacine Cheraga

Irène Bujon

Patrice Fraisse

Tangi Rumon Brusq

An air intake for an aircraft propulsion assembly extending along a longitudinal axis and including a turbine engine that includes a primary flow path and a secondary flow path for respectively guiding a primary air flow and a secondary air flow during a thrust, and thrust reversal for changing the secondary airflow into a reverse airflow during a thrust reversal. The air intake including a peripheral external enclosure including, in each plane radial to the axis, a point of maximum curvature for detaching the reverse airflow, an osculating circle defining a radius of curvature that is defined at each of the points of maximum curvature. The average value of the radii of curvature being less than a product of 0.028 times an internal radius of the air intake at the fan.

Nacelle air intake for an aircraft propulsion assembly to promote a thrust reversal phase

A method for controlling a turbojet engine thrust reverser during an aborted aircraft takeoff, the thrust reverser including doors movable between a stowed position, an overstowed position and a deployed position; door actuators to move the doors between the stowed, overstowed and deployed positions; a device for locking the doors in the stowed position, moveable between a locking position and an unlocking position; and a lock actuator to move the locking device between the locking and unlocking positions. The method includes decreasing the engine speed of the turbojet engine by following a setpoint value below a first engine speed threshold value at which the aerodynamic forces being exerted on the doors are equal to the forces developed by the door actuators; controlling the door actuators to bring the doors into the overstowed position; controlling the lock actuator to bring the locking device into the unlocking position.

Method and system for controlling a thrust reverser of an aircraft

An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.

Turbojet engine comprising a nacelle with an air intake to promote a reversed thrust phase

A method for controlling the clearance between the blade tips of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, including the controlling of a valve delivering a stream of air to the turbine shroud, this method further including the following steps: the detection of a transient acceleration phase of the engine; the receiving of an item of data representative of the gas temperature at the outlet of the combustion chamber of the engine; a valve opening command, to deliver the air stream to the turbine shroud or to increase the flow rate of the delivered air stream, if the transient acceleration phase is detected and if the gas temperature at the outlet of the combustion chamber is greater than a first temperature threshold corresponding to a degraded clearance characteristic of an aged engine, this threshold being less than an operating limit temperature of the engine.

Method and control unit for controlling the play of a high-pressure turbine

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Moissy-Cramayel, France

Jean-Loïc Hervé Lecordix