Abstract: A fuel cell (10) has a compressed air inlet fed by a compressor (20) and a fuel inlet, and it produces direct current electricity. A turbine (30) receives a flow of gas under pressure from the fuel cell and is mechanically coupled to the first compressor in order to drive it. A second compressor (46) of a circuit for use in flight to feed pressurized air to the aircraft cabin (40) is mechanically coupled to a shaft of the turbine. An electric machine (50) may be coupled to the same turbine shaft as drives the compressor (46), the electric machine being capable of operating as a generator or as an electric motor.

Abstract: A turbine blade extends radially between a blade root and a blade tip having an open cavity referred to as a bathtub formed therein, which cavity is defined by a closed end wall and a side rim. The side rim of the cavity carries at least one rib extending between a leading edge and a trailing edge of the blade.

Abstract: In a helicopter gas turbine engine, lips (30, 32) defining a radial air intake (34) are connected along an opening (12a) of an engine compressor air supply passage (12). The air intake lips are at least partially formed by a sound attenuator (40, 42) calculated to attenuate sound frequencies produced by the compressor rotation.

Abstract: A centrifugal compressor for a turbine engine, including a cover with an upstream end and a downstream end; a casing presenting an upstream edge and a downstream edge; and a bladed impeller mounted to rotate in the casing. The cover covers the blades of the impeller to define an outside surface of a gas-flow passage extending between the upstream and downstream edges of the casing, while being fastened to the upstream edge of the casing via its upstream end while its downstream end remains free. The cover further includes an abutment limiting axial movement of its downstream end relative to the downstream edge of the casing while the compressor is in operation.

Abstract: A compressor impeller including at least one blade connected to an impeller hub via a junction of curved shape, the blade extending along a defined chord between a leading edge and a trailing edge of the blade. The junction presents the shape of an ellipse that varies along the chord.

Abstract: A torque measurement device including: a power shaft transmitting rotary torque about the axis of the power shaft; a first wheel carrying angle marks, the wheel being secured to the power shaft; a reference shaft including a second wheel carrying angle marks; and a sensor placed facing at least one of the wheels to determine the torque transmitted by the power shaft. The first wheel includes first and second series of angle marks and the second wheel includes third and fourth series of angle marks. The marks of the first and third series are mutually parallel, while the marks of the second and fourth series are mutually parallel and are inclined relative to a first axial plane containing the axis, the marks of the first series being inclined relative to the marks of the second series, whereby the signal supplied by the sensor is representative of temperature of the power shaft.

Abstract: A turbine engine, for example for a helicopter, the engine including a gas generator and a free turbine driven in rotation by a gas stream generated by the gas generator, the turbine engine further including a reversible electric machine for coupling to the gas generator, the reversible electric machine configured to set the gas generator into rotation during a stage of starting the turbine engine. To generate electricity, the reversible electric machine is also configured to be coupled to the free turbine after the turbine engine has started.

Abstract: A method of diagnosing or determining parameters for an installation for detecting open defects in the surfaces of parts by sweating, the method including passing at least one standard testpiece through the installation, the testpiece having a surface possessing at least one pattern representative of the type of defect that is to be detected, applying to the surface of the testpiece a penetrating composition including an indicator substance, washing, drying, applying to the surface of the testpiece a composition including a developer, and illuminating the surface of the testpiece to illuminate any remaining indicator substance so as to form a developed image of the or each pattern and deduce therefrom an indication about the quality of the operation of the installation.

Abstract: A sealing device for providing sealing between a casing and a shaft rotatably mounted in the casing. The device includes first and second annular lip gaskets for placing axially side by side between the casing and the shaft. A stream of pressurized gas is delivered into an annular casing defined by the first lip gasket, the second lip gasket, and an outside surface of the shaft, such that during rotation of the shaft, the gas stream is suitable for causing at least one of the two lip gaskets to lift off a little from the outside surface of the shaft in order to flow out from the cavity.

Abstract: A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening for admitting air into the enclosure, the first opening including a first essentially metallic grid, the enclosure further including a second opening for directing the air towards a compression stage of the gas turbine. The de-icer device further includes a wave generator for generating electromagnetic waves in the enclosure at a frequency suitable for causing ice to melt.

Abstract: A turbine engine, for example for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator. The turbine engine further includes a motor/generator coupled to a shaft of the gas generator, to provide a quantity of additional rotational kinetic energy to the shaft during a stage of turbine engine acceleration, or to draw a quantity of rotational kinetic energy from the shaft during a stage of turbine engine deceleration.

Abstract: Gas under pressure is admitted through an orifice formed in the bottom portion of a tank of substance in powder form, and is guided along an internal tube connected to the admission orifice, the tube passes through the powder stored in the tank and entrains powder through openings formed in the wall of the tube, the powder being extracted in the form of a gas-and-powder flow through an outlet at the top portion of the tank. The gas-and-powder mixture traveling along the internal tube is guided to the top portion of the tank where it is directed substantially towards a side wall of the tank so as to set up a gas-and-powder flow traveling through the volume situated in the tank above the powder stored in the tank, prior to the gas-and-powder flow being extracted through the outlet. The gas-and-powder flow can be taken to one or more powdering nozzles, e.g. in a system for powdering a developer in an installation for detecting surface defects by sweating.

Abstract: The invention relates to a signaling magnetic plug for a liquid circuit, the plug including a first magnetic electrode and a second magnetic electrode for coming into contact with the liquid flowing in the liquid circuit when the magnetic plug is mounted so as to detect the presence of metal particles that might be contained in the liquid. According to the invention, the plug also includes a preferably non-magnetic intermediate electrode disposed between the first and second magnetic electrodes while also being designed to be in contact with the liquid flowing in the liquid circuit when the magnetic plug is mounted, whereby said plug enables the presence of such metal particles to be detected early.

Abstract: The invention relates to a turbine engine (10), particularly for a helicopter, comprising a gas generator (12) and a free turbine (14) rotated by a gas flow (F) generated by the gas generator. The invention is characterized in that the turbine engine also comprises heating means (26) placed between the gas generator and the free turbine (14), the said heating means (26) being capable of increasing the temperature of the gas flow (f) generated by the gas generator (12) and driving the free turbine.

Abstract: At least one of the main injectors of the engine, forming a starter main injector, is fed directly by the pressurized feed pipe, while a head loss is imposed between the pressurized feed pipe and the other main injectors. Ignition is caused to take place at the starter main injector, and after ignition, said head loss imposed between the feed pipe and the other main injectors is eliminated so that all of the main injectors are fed with fuel at substantially the same pressure, without any imposed head loss.

Abstract: In a helicopter gas turbine engine, lips (30, 32) defining a radial air intake (34) are connected along an opening (12a) of an engine compressor air supply passage (12). The air intake lips are at least partially formed by a sound attenuator (40, 42) calculated to attenuate sound frequencies produced by the compressor rotation.

Abstract: The invention relates to a helicopter gas turbine engine having a combustion chamber, at least one turbine (20) arranged downstream from the combustion chamber to receive combustion gases emitted by the latter and a nozzle. The nozzle has one part forming a diffuser (26), connected downstream from the turbine and an ejector (30) which has an upstream part surrounding the downstream end of the diffuser and defining therewith an outlet passage (32) for an engine compartment cooling air secondary flow, the ejector running in the downstream direction beyond the downstream end of the diffuser. The ejector (30) has a wall formed at least partially by a sound attenuator (34) calculated to attenuate sound frequencies generated by the rotation of the or each turbine and/or by the combustion chamber.

Abstract: The present invention relates to a device for injecting a liquid fuel into a pressurized air flow (7), in particular for a combustion chamber, comprising a hollow cylindrical body (10) of longitudinal axis (YY?) delimiting a substantially cylindrical central volume (11), fluid veins (12) substantially radial in relation to the longitudinal axis of body (10) and arranged on the periphery of said body to allow passage of said flow, and axial fuel injection pipes (5) arranged inside said fluid veins and connected to at least one fuel inlet (3) by at least one supply point (16). According to the invention, pipes (5) are pierced with openings (9) that open onto central volume (11) of said body (10) and which are oriented substantially in the direction of the flow in fluid veins (12).

Abstract: Gas under pressure is admitted through an orifice formed in the bottom portion of a tank of substance in powder form, and is guided along an internal tube connected to the admission orifice, the tube passes through the powder stored in the tank and entrains powder through openings formed in the wall of the tube, the powder being extracted in the form of a gas-and-powder flow through an outlet at the top portion of the tank. The gas-and-powder mixture traveling along the internal tube is guided to the top portion of the tank where it is directed substantially towards a side wall of the tank so as to set up a gas-and-powder flow traveling through the volume situated in the tank above the powder stored in the tank, prior to the gas-and-powder flow being extracted through the outlet. The gas-and-powder flow can be taken to one or more powdering nozzles, e.g. in a system for powdering a developer in an installation for detecting surface defects by sweating.

Abstract: A method of diagnosing or determining parameters for an installation for detecting open defects in the surfaces of parts by sweating, the method comprising passing at least one standard testpiece through the installation, the testpiece having a surface possessing at least one pattern representative of the type of defect that is to be detected, applying to the surface of the testpiece a penetrating composition including an indicator substance, washing, drying, applying to the surface of the testpiece a composition including a developer, and illuminating the surface of the testpiece to illuminate any remaining indicator substance so as to form a developed image of the or each pattern and deduce therefrom an indication about the quality of the operation of the installation.