Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

Abstract: A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient ? of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient ? on the basis of the measurement of the temperature of the gas stream.

Abstract: A method of testing and/or controlling the operation of an axial turbomachine through which passes a gas stream, includes the following actions: measurement of operating parameters of the turbomachine, said parameters including pressure in the gas stream at different axial positions, and calculation of operating conditions of the turbomachine from the measured parameters and the Laplace coefficient ? of the gas passing through the turbomachine, wherein the measurement of parameters includes a measurement of the temperature of the gas stream, and the calculation of operating conditions includes a determination of the Laplace coefficient ? on the basis of the measurement of the temperature of the gas stream.

Abstract: The disclosed technology concerns an aircraft turbomachine part comprising a part body drilled with at least one cavity open to the outside and at least one conduit joining the cavity on the one hand and leading to the outside on the other hand. Each cavity receives a pressure sensor, and the conduit corresponds to the cavity guides the cables connected to the sensor to the outside of the part body. The part is an aircraft turbomachine vane.

Abstract: A measuring system for a turbine engine includes a piezoresistive sensor and an analysis module, the sensor and the module being such that the module can determine, from measuring two electrical voltages, a pressure value (p) and a temperature value (T) in the vicinity of the sensor. The sensor can include a Wheatstone bridge arranged on a flexible membrane.

Abstract: A turbine engine casing, and in particular an axial turbine engine compressor casing, includes an annular wall and a fastening flange associated with the wall. The fastening flange includes a fastening surface applied against a corresponding mounting surface of the turbine engine, for example, a surface on an intermediate fan casing or a mounting surface of a flow separator. The fastening flange includes at least one electrical connector with one end lying flush with the fastening surface of said fastening flange.

Abstract: An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.

Abstract: A turbine engine casing, and in particular an axial turbine engine compressor casing, includes an annular wall and a fastening flange associated with the wall. The fastening flange includes a fastening surface applied against a corresponding mounting surface of the turbine engine, for example, a surface on an intermediate fan casing or a mounting surface of a flow separator. The fastening flange includes at least one electrical connector with one end lying flush with the fastening surface of said fastening flange.

Abstract: A variable-geometry turbine engine compressor, in particular a low-pressure turboreactor compressor, which is also called a booster, includes: an annular row of variable stator vanes, each of the vanes including a control gearing, and an synchronizing ring with an additional gearing which cooperates with the control gearing of the vanes, so as to control the effect with respect to the flow of the turbine engine. Each gearing of the vane or of the ring is a herringbone gearing, the teeth of a herringbone of which form between them an angle ? of between 60° and 150° inclusive, or possibly equal to 120°.

Abstract: An oil tank fitted to a turbomachine, for example an aeroplane turbo-jet engine. The tank includes an inner chamber containing the oil of the turbomachine, a wall with an inner surface surrounding the inner chamber, and a capacitive device for measuring the oil level. The device includes at least one electrode and potentially two parallel electrodes forming the inner surface. These electrodes are immersed in the oil to measure the oil level by measuring capacitance. A method for manufacturing a tank in which the electrodes are printed on the wall.

Abstract: An aeroplane turbojet low-pressure compressor vane includes a leading edge, a trailing edge, a surface, and an extrados surface which extend from the leading edge to the trailing edge. To combat the presence and the formation of ice, the vane is provided with an electric de-icing device with a thermistor. The thermistor forms a heating electrical track suitable for de-icing the vane. The present application also proposes a method for producing a turbine engine vane.

Abstract: Stator vane for a turbine engine and including at least one portion made from material suitable for superelasticity. The portion made from material suitable for superelasticity is arranged so as to start to resonate at a predetermined speed of the turbine engine, in particular during a speed of the turbine engine typical of the cruising phase of the aircraft.

Abstract: A passive leakage device for an axial turbomachine, more particularly for a low-pressure compressor of an axial turbomachine, is adapted to reduce and/or eliminate the surging phenomenon within the machine. The passive leakage device includes an insert having a general cylindrical shape with a flange at one end and a bottom or membrane at the other end. The membrane comprises two cross-shaped notches, the notches being adapted to enable a deformation of the membrane under a pressure exceeding a predetermined threshold, so as to allow a leakage to go through the membrane. Several inserts are arranged through the wall of a compressor casing, distributed over one or several circumferences of the casing, facing one or several rows of rotor blades. In the case of a double-flow turbomachine, such as a jet engine, the beak for separating the primary and secondary flows is used to form a chamber for communication between the inserts and for compensation with the pressure present in the secondary flow.

Abstract: A passive leakage device for an axial turbomachine, more particularly for a low-pressure compressor of an axial turbomachine, is adapted to reduce and/or eliminate the surging phenomenon within the machine. The passive leakage device includes an insert having a general cylindrical shape with a flange at one end and a bottom or membrane at the other end. The membrane comprises two cross-shaped notches, the notches being adapted to enable a deformation of the membrane under a pressure exceeding a predetermined threshold, so as to allow a leakage to go through the membrane. Several inserts are arranged through the wall of a compressor casing, distributed over one or several circumferences of the casing, facing one or several rows of rotor blades. In the case of a double-flow turbomachine, such as a jet engine, the beak for separating the primary and secondary flows is used to form a chamber for communication between the inserts and for compensation with the pressure present in the secondary flow.