Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to the shaft. An air guide is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide passes between the first seal and the shaft, the air guide being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

Abstract: A power transmission system for a turbine engine is provided. The power transmission system includes a transmission shaft that is connected to a drive shaft by bevel gears, and that drives equipment or accessories. The transmission shaft is designed to operate under supercritical conditions and includes a damper system for damping vibration at its resonant speed.

Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to said shaft. An air guide means is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide means passes between the first seal and the shaft, said guide means being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.

Abstract: A method for automated detection of ingestion of at least one foreign body by a gas turbine engine, according to which: instantaneous speed of the rotor is measured; a speed signal of the rotor is filtered to separate a static component from a dynamic component thereof; the filtered dynamic component is compared to a standard resonance wave of the rotor to obtain an ingestion indicator, the standard resonance wave corresponding to the vibrational impulse response of a rotor; the obtained ingestion indicator is compared with a detection threshold; and a foreign body ingestion detection signal is emitted when the ingestion indicator is higher than the detection threshold.

Abstract: The invention relates to a power transmission system, in particular for a turbine engine such as an airplane turboprop or turbojet, the system comprising a transmission shaft (40) connected to a drive shaft (31) by connection means (30), such as bevel gears, and that drive equipment or accessories. The transmission shaft (40) is designed to operate under supercritical conditions and includes damper means for damping vibration at its resonant speed.

Abstract: A method for automated detection of ingestion of at least one foreign body by a gas turbine engine, according to which: instantaneous speed of the rotor is measured; a speed signal of the rotor is filtered to separate a static component from a dynamic component thereof; the filtered dynamic component is compared to a standard resonance wave of the rotor to obtain an ingestion indicator, the standard resonance wave corresponding to the vibrational impulse response of a rotor; the obtained ingestion indicator is compared with a detection threshold; and a foreign body ingestion detection signal is emitted when the ingestion indicator is higher than the detection threshold.

Abstract: A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the shaft, one of the bearings being capable of giving way when an unbalance occurs in the rotary assembly, at least one segment of the shaft being covered in a covering which comprises at least one piece of fabric impregnated with resin and which is for coming into contact with a surrounding portion of the turbomachine when the unbalance occurs in order to protect the first shaft and ensure that there is no risk of the first shaft rupturing. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.

Abstract: A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting said shaft, one of said bearings being capable of giving way when an unbalance occurs in the rotary assembly, at least one segment of said shaft being covered in a covering which comprises at least one piece of fabric impregnated with resin and which is for coming into contact with a surrounding portion of the turbomachine when said unbalance occurs in order to protect the first shaft and ensure that there is no risk of said first shaft rupturing. The turbomachine is intended to be used mainly in the field of aviation, and more particularly as an airplane turbojet.