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 turbomachine including an exhaust housing, including a plurality of arms, the space separating the arms defining openings in which there circulates a primary air flow of the turbomachine, at least one conduit, a) configured to collect a compressed air flow at one of the ends of same, b) the other end of the conduit being connected to at least one opening of the exhaust housing, so as to insert the collected air flow into the primary air flow, the collected air flow having, when inserted into the opening, a Mach number less than or equal to 0.5.

Abstract: A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the circumferential ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged radially between the airflows.

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 turbomachine including an exhaust housing, including a plurality of arms, the space separating the arms defining openings in which there circulates a primary air flow of the turbomachine, at least one conduit, a) configured to collect a compressed air flow at one of the ends of same, b) the other end of the conduit being connected to at least one opening of the exhaust housing, so as to insert the collected air flow into the primary air flow, the collected air flow having, when inserted into the opening, a Mach number less than or equal to 0.5.

Abstract: An apparatus for activating a valve of an ejector in order to adapt the pressurization of a chamber in an aircraft turbojet engine comprising a device constructed and arranged to trigger the opening and/or closing of valve and/or the power of the valve as a function of the altitude at which the valve is located.

Abstract: A journal configured to be driven in rotation in a housing of a turbine engine, or for an aircraft, the journal including: a circumferential main body including plural ventilation openings configured to allow plural axial airflows to circulate from upstream to downstream in the turbine engine, two consecutive ventilation openings being connected by a connecting segment, and a circumferential ring for recovering a flow of lubrication oil, which ring is rigidly connected to the main body and is radially inside the ventilation openings, the recovery ring including plural radial discharge openings for allowing plural radial flows of oil to be discharged towards the outside, each discharge opening being radially aligned with a connecting segment of the main body to allow each flow of oil to be discharged between the airflows.

Abstract: An apparatus for activating a valve of an ejector in order to adapt the pressurisation of a chamber in an aircraft turbojet engine comprising a device constructed and arranged to trigger the opening and/or closing of valve and/or the power of the valve as a function of the altitude at which the valve is located.