The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

The invention relates to a planetary gear box in a gas turbine engine, characterized by at least one protective device in the interior of a casing of the planetary gear box, wherein the protective device is designed and configured to divert at least one particle which is moving in the casing, in particular in an event of damage, and/or to extract kinetic energy from the moving at least one particle, in particular by deformation of the protective device, wherein the protective device is coupled to the casing of the planetary gear box, to a planet gear and/or to a planet carrier. The invention also relates to a gas turbine engine.

Systems and methods for communicating a signal over a hydraulic line in a vehicle are provided. In one embodiment, a system can include a hydraulic line. The hydraulic line can include at least one communication medium for propagating a communication signal. The system can also include at least one signal communication device configured to receive the communication signal communicated over the hydraulic line. The system can also include at least one vehicle component in communication with the at least one signal communication device.

The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.

The present invention relates to a control method in case of engine failure of a hybrid helicopter having a power plant connected to at least one lift rotor and to at least one propeller, said lift rotor having a plurality of first blades and said at least one propeller having a plurality of second blades. The method comprises the following steps: (i) measuring a forward speed of the hybrid helicopter, (ii) on condition that said forward speed is greater than a first speed threshold and that each engine has failed, automatically implementing a first emergency piloting mode comprising a step for automatic reduction by an automatic piloting system of a pitch of said second blades toward an objective pitch making said at least one propeller produce a motive power which is transmitted to the lift rotor.

The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

Disclosed are systems and methods for testing aircraft engine that are not currently associated with a functional aircraft or systems. For testing, systems on the engine being tested are connected with the reciprocating systems (e.g., engine electronic controls, main and motive fuel) on a fully functional aircraft using conduits that have been extended to lengths enabling the connection.

A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.