Abstract: The invention relates to a temperature measurement method using a thermometric resistance-type temperature probe (1) comprising at least two electroconductive sensitive elements (3, 4) on the same substrate (2), wherein different parameters representative of the strength of the electric current circulating in one of said sensitive elements (3, 4) are measured, and a correction, according to said strength of the electric current circulating in said sensitive element (3, 4), is applied to a signal representative of a temperature measurement generated from the other one of said sensitive elements (3, 4), in order to correct an error created as a result of the self-heating by the Joule effect of said sensitive element (3, 4) affecting the other one of said sensitive elements (3, 4).

Abstract: A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.

Abstract: A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement.

Abstract: The invention relates to a temperature measurement method using a thermometric resistance-type temperature probe (1) comprising at least two electroconductive sensitive elements (3, 4) on the same substrate (2), wherein different parameters representative of the strength of the electric current circulating in one of said sensitive elements (3, 4) are measured, and a correction, according to said strength of the electric current circulating in said sensitive element (3, 4), is applied to a signal representative of a temperature measurement generated from the other one of said sensitive elements (3, 4), in order to correct an error created as a result of the self-heating by the Joule effect of said sensitive element (3, 4) affecting the other one of said sensitive elements (3, 4).

Abstract: A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result.

Abstract: A device for measuring a compressor inlet temperature in a primary stream flow passage of a bypass turbojet. The device includes an airtight hollow structure forming a connection arm of an intermediate casing of the turbojet and configured to pass radially through a flow passage for the primary stream and a flow passage for a secondary stream of the turbojet, the connection arm including at least one inlet air orifice opening out into the primary stream flow passage at an inlet of a compressor and at least one air outlet orifice leading to a zone of the turbojet in which surrounding pressure is less than pressure in the primary stream flow passage at the inlet of the compressor; and a temperature probe having its sensitive element arranged inside the connection arm.

Abstract: A method to correct a current measurement of pressure of a gas stream delivered during a mission by a sensor in the engine. The method includes: estimating a drift error affecting the sensor on the basis of a difference existing between: (1) a calibration measurement of the pressure of the gas stream as delivered by the sensor in the engine, and (2) an atmospheric pressure measurement delivered by a sensor of the aircraft presenting accuracy greater than that of the sensor in the engine; these measurements being performed while the sensor in the engine and the sensor of the aircraft are subjected to same surrounding atmospheric pressure; and subtracting the estimated drift error from the current measurement.

Abstract: A process for monitoring a machine including moving pieces, a lubrication system and an electromagnetic sensor fitted with a magnet and two electrodes is disclosed. The sensor is capable of collecting particles present in the lubrication system between the electrodes. The monitoring process includes a step for obtaining measurements of resistance between the electrodes of the sensor, taken during an operating period of the machine; a step for determining from said measurements a first autoregressive mathematical model characterizing the resistance; a step for comparison between the first model and a predetermined reference model; and a step for working out an opinion on maintenance of the machine as a function of the comparison result.

Abstract: A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.

Abstract: A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and excitation, control or servo circuits for pieces of electrical equipment of the engine. The engine electrical power supply circuit includes a first bus distributing DC or AC voltage to excitation, control or servo circuits for first pieces of electrical equipment of the engine, a second bus distributing DC or AC voltage to excitation, control or servo circuits for other pieces of electrical equipment of the engine requiring higher electrical power compared with the first pieces of equipment, and a third bus connected to receive power from an electricity source such as an airplane on-board electricity distribution network or an electricity generator dedicated to the engine and driven thereby. The third bus supplies the first and second bus with electricity power.