Safran Aircraft Engines

Snecma

Christophe Javelot

Cedrik Djelassi

Bruno Robert Gaully

Amaury Olivier

Damien Bonneau

Cédrik Djelassi

Mohamed Boutaleb

Ismail Sylla

Victor Henry

Darragh McGrath

Darragh Mcgrath

A method for controlling thrust from a turbojet that is fuel flow rate regulated by a high limit value for providing protection against surging of a compressor of the turbojet is provided. The method includes: obtaining a first thrust value corresponding to a first operating point of the compressor on the high limit value, the high limit value taking account of an underestimate of the fuel flow rate; controlling the turbojet to reach the first thrust value; monitoring the turbojet to detect underspeed of the compressor; and where applicable: obtaining a second thrust value corresponding to a second operating point that guarantees a predetermined margin relative to the high limit value so as to obtain protection against underspeed of the turbojet; and controlling the turbojet to reach the second value.

Method and a device for controlling thrust from a turbojet

A method of adjusting a fuel flow rate in a turbine engine propelling an aircraft, including: obtaining a first estimate of a flow rate of fuel injected into a combustion chamber of the turbine engine propelling an aircraft and as delivered by a fuel metering device of the turbine engine; obtaining a second estimate of the fuel flow rate, which second estimate is more accurate than the first estimate for at least one range of fuel flow rate values and being delivered by an estimator device having a flow meter; and adjusting the fuel flow rate threshold value with help of a difference evaluated between the first estimate and the second estimate, the threshold value being for use in an open loop for regulating the turbine engine.

Method and device for adjusting a threshold value of a fuel flow rate

A method controlling a clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method including: controlling flow and/or temperature of air directed toward the housing according to an estimate of the clearance, the estimate of the clearance is determined upon start-up of the aircraft engine, according to a temperature measured by a temperature sensor including a sensitive element positioned in a free space of the aircraft engine.

Method for controlling the clearance at the tips of blades of a turbine rotor

A method of testing an engine fuel supply cutoff valve includes: detecting a fuel supply cutoff command; commanding to close the fuel supply cutoff valve; commanding to hold the fuel metering valve in the open position for a predetermined time; commanding to close the fuel metering valve after the predetermined time; measuring an engine operating parameter during performance of the previous steps; and comparing the measured parameter with a predetermined threshold, so as to determine whether or not the engine operating parameter corresponds to an engine fuel supply cutoff by normal operation of the fuel supply cutoff valve.

Monitoring the fuel supply cutoff valve for an engine

Growing community of inventors

Rungis, France

Christophe Javelot