Abstract: Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

Abstract: The tank for a turbine engine comprises a partition separating a first compartment from a second compartment of the tank , the partition having a first end and a second end, the second end being closer to the bottom of the tank than the first end, the partition being inclined from the first end to the second end in the first direction and in the direction of the first outlet to the second outlet , the partition comprising at least one first Through-hole near the first end and at least one second through-hole closer to the second end than the first hole.

Abstract: 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.

Abstract: Turbine engine (1), in particular for an aircraft, comprising at least one axial shaft (2) rotatably mounted in a casing (3) of the turbine engine (1), the turbine engine (1) comprising an annular reference part (10) comprising short (11) and long (12) longitudinal reference teeth, first means for detecting the passage of the short (11) and long (12) reference teeth so as to measure the speed of the shaft (2) of the turbine engine (1) about its axis (X), an annular measurement part (20) comprising longitudinal measurement teeth (21); and second means for detecting the passage of the long reference teeth (12) and the measurement teeth (21) so as to measure the torque of the shaft (2, 102) of the turbine engine (1).

Abstract: The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterized in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor.

Abstract: The tank for a turbine engine comprises a partition separating a first compartment from a second compartment of the tank , the partition having a first end and a second end, the second end being closer to the bottom of the tank than the first end, the partition being inclined from the first end to the second end in the first direction and in the direction of the first outlet to the second outlet , the partition comprising at least one first Through-hole near the first end and at least one second through-hole closer to the second end than the first hole.

Abstract: The invention relates to a method for controlling an electric motor actuating a mobile hood provided in a thrust reverser for a turboreactor, said method being characterised in that it comprises steps of: determining the operating state of the electric motor; interrupting the supply of the electric motor if said motor is not in operation during a defined period of time; reactivating the electric motor after an idle period and repeating the previous steps or definitively stopping the motor if the steps have already been repeated a pre-defined number of times. The invention also relates to a method for managing the electrical supply of a motor provided in a device arranged in the vicinity of a turboreactor.

Abstract: A turbojet thrust reverser includes two doors each displaceable between an open position and a closed position of the reverser by at least one respective control actuator. Two electric motors drive the control actuators for the doors; each motor being controlled by an electronic control unit connected to a full authority digital engine control. Two servo-control devices control the displacement of the doors as a function of determined position references. The servo-control devices enable the doors to be displaced synchronously as a function of any variation in the forces exerted on the reverser and as a function of any force difference between the two doors.

Abstract: A turbojet thrust reverser has two doors that are displaceable between a reverser open position and a reverser closed position, each door being controlled by a respective electronic control unit connected to a FADEC, and each door having a respective locking device for locking the position of the door associated therewith. Each locking device can be unlocked solely on receiving orders that come simultaneously from both electronic control units.

Abstract: Each manual control unit for a moving part of a thrust reverser is associated with a maintenance plate that is pivotable between at least two positions: a first or “normal operation” position in which said plate prevents the manual control unit with which it is associated from being driven manually, while allowing it to be driven electrically; and a second or “maintenance” position in which said plate allows the manual control unit with which it is associated to be driven manually while preventing it from being driven electrically.

Abstract: A turbojet thrust reverser includes two doors each controlled by a respective electronic control unit, at least one sensor per door measuring at least one item of position data concerning the door, at least one sensor of each door being connected to the electronic control unit controlling that door, the electronic control units being connected to each other in order to exchange the position data, a FADEC having two channels each connected to both electronic control units in order to receive from each of the electronic control units data concerning the positions of each of the doors and data concerning the operating state of each of the electronic control units, the channels being connected to each other in order to exchange the door position data and the electronic control unit state data so that the airplane pilot is continuously informed about the positions of the doors and the states of the electronic units, even in the event of a breakdown in one of the electronic units and in one of the FADEC channels.

Abstract: A turbojet thrust reverser comprising two doors each displaceable between an open position and a closed position of the reverser by means of at least one respective control actuator; two electric motors each driving said at least one control actuator for each door; each motor being controlled by an electronic control unit connected to a full authority digital engine control; and two servo-control means for controlling the displacement of corresponding ones of said doors as a function of determined position references, said servo-control means enabling said doors to be displaced synchronously as a function of any variation in the forces exerted on the reverser and as a function of any force difference between the two doors.

Abstract: A turbojet thrust reverser has two doors that are displaceable between a reverser open position and a reverser closed position, each door being controlled by a respective electronic control unit connected to a FADEC, and each door having a respective locking device for locking the position of the door associated therewith. Each locking device can be unlocked solely on receiving orders that come simultaneously from both electronic control units.

Abstract: Each manual control unit for a moving part of a thrust reverser is associated with a maintenance plate that is pivotable between at least two positions: a first or “normal operation” position in which said plate prevents the manual control unit with which it is associated from being driven manually, while allowing it to be driven electrically; and a second or “maintenance” position in which said plate allows the manual control unit with which it is associated to be driven manually while preventing it from being driven electrically.

Abstract: A turbojet thrust reverser comprises two doors each controlled by a respective electronic control unit, and at least one sensor per door measuring at least one item of position data concerning said door, said at least one sensor of each door being connected to said electronic control unit controlling that door, said electronic control units being connected to each other in order to exchange said position data, and a FADEC having two channels each connected to both electronic control units in order to receive from each of said electronic control units data concerning the positions of each of said doors and data concerning the operating state of each of said electronic control units, said channels being connected to each other in order to exchange said door position data and said electronic control unit state data so that the airplane pilot is continuously informed about the positions of said doors and the states of said electronic units, even in the event of a breakdown in one of said electronic units and in o