Abstract: 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.

Abstract: A method and a device for determining, in real time, the flow rate of air collected from an aircraft engine by a system for collecting air from the engine, including an acquisition device for acquiring at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for the air collection system, a computing device for evaluating at each current time of the successive times a first current estimation of the flow rate of air collected from the aircraft engine on the basis of the physical quantity measurements, the acquisition device for acquiring at the current time a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables, the computing device for hybridising, at the current time, the first current air flow rate estimation and the minimum current air flow rate data item to form a second current air flow rate estimation.

Abstract: 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.

Abstract: A method for detecting degradation of a turbine engine by monitoring performance of the turbine engine, the turbine engine including plural functional modules, the method including: measuring plural physical parameters of the turbine engine to form a current performance index for the turbine engine; calculating plural degraded performance indices for the turbine engine, assuming that, for each degraded performance index, only one functional module of the turbine engine has degraded; calculating plural cost indices corresponding to the difference between the current performance index and a degraded performance index; determining an optimum cost index corresponding to the one with a lowest value for all the degraded performance indices; and detecting degradation of the module of the turbine engine, the degraded performance index of which is associated with optimum cost index.

Abstract: 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.

Abstract: A method and a device for determining, in real time, the flow rate of air collected from an aircraft engine by a system for collecting air from the engine, including an acquisition device for acquiring at successive times measurements of physical quantities in respect of temperature, pressure and pressure loss, specific for the air collection system, a computing device for evaluating at each current time of the successive times a first current estimation of the flow rate of air collected from the aircraft engine on the basis of said the physical quantity measurements, the acquisition device for acquiring at the current time a minimum current air flow rate data item defined on the basis of a predetermined flow rate tables, the computing device for hybridising, at the current time, the first current air flow rate estimation and said the minimum current air flow rate data item to form a second current air flow rate estimation.

Abstract: A method for detecting degradation of a turbine engine by monitoring performance of the turbine engine, the turbine engine including plural functional modules, the method including: measuring plural physical parameters of the turbine engine to form a current performance index for the turbine engine; calculating plural degraded performance indices for the turbine engine, assuming that, for each degraded performance index, only one functional module of the turbine engine has degraded; calculating plural cost indices corresponding to the difference between the current performance index and a degraded performance index; determining an optimum cost index corresponding to the one with a lowest value for all the degraded performance indices; and detecting degradation of the module of the turbine engine, the degraded performance index of which is associated with optimum cost index.

Abstract: 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.