Abstract: A method for brazing parts having complex profiles, while enabling reproducible implementation conditions to be defined. The method adjusts a heat cycle during brazing by controlling and mapping heat, while taking emissivity coefficient of the material to be brazed into account. Further, a brazing station includes a power generator configured to supply a predetermined voltage to a transformer connected to a circuit forming a shape inductor, the circuit having an overall shape of the parts to be brazed. A pressure mechanism exerts a load on the parts to be brazed. A camera establishes a heat map. A laser-sighted infrared pyrometer measures the brazing temperature by radiation after parameterizing an emissivity coefficient, other parameters being fixed. A controller supplies a set power to the generator on the basis of the measured temperature.

Abstract: An overspeed protection device includes at least one torque measurement unit supported by an output shaft coupled mechanically to a free turbine of a turbine engine and a signal processing unit able to transmit to a turbine engine regulating system a command to reduce a flow of fuel injected if it is detected that the torque has dropped below a first datum value. The signal processing unit is shaped to command a reduction of the flow if it is detected that the torque has dropped below a first datum value, the torque measurement used to trigger the reduction being taken during a rotation corresponding to a fraction of a revolution of the output shaft.

Abstract: A method and architecture for recombining power of a turbomachine improving on problems of size, mass, or reliability. In the method energy is recovered in an exhaust nozzle and converted and recirculated using a mechanical and/or electrical power recombining mechanism. An example of an architecture of a turbomachine includes a main turbine engine and a heat exchanger positioned in the exhaust nozzle and coupled, via pipes, to an independent system that converts thermal energy into mechanical energy. This independent system is connected to a localized mechanical recombination mechanism via a power shaft to supply power to a power transmission shaft according to aircraft requirements.

Abstract: An architecture making it possible to provide sufficient absorption of shocks for a power shaft while maintaining rigidity at front bearings so as to not compromise meshing of power teeth of a drive pinion. A compressible dynamic shock absorption is provided in alignment with a downstream shock absorber of an additional meshing. An assembly for dynamically absorbing shocks for a power shaft includes upstream and downstream bearings including power rollers mounted on two casings and flanking a speed-reducing teeth meshing. The downstream bearing is coupled to at least one additional roller bearing associated with a compressible shock absorber to form a downstream shock absorber axially offset relative to the upstream bearing opposite the teeth meshing. Both downstream bearings are connectable by a flexible frame mounted on the common casing. The architecture can be used for power-transmission shafts, for example supercritical shafts in turbine engines.

Abstract: A turbine engine for a helicopter, the helicopter including a main gearbox, a rotor, and a speed-reducing device housed entirely within the main gearbox of the helicopter while also being connected to the rotor, the turbine engine including a casing, a gas generator with a gas generator shaft, and a free turbine for being driven in rotation by a gas stream generated by the gas generator, the free turbine including a free turbine shaft. When the turbine engine is fastened to the gearbox of the helicopter, the free turbine shaft extends axially into the main gearbox of the helicopter to be connected directly to the speed-reducing device.

Abstract: A heat-exchange architecture for exhaust of a turbine engine, including heat-exchange elements partially obstructing a hot exhaust gases stream. In an architecture built into an exhaust line for gas streams of a turbine engine, the turbine engine is a turboshaft engine including a gas generator and a free turbine supplying power to a shaft via a through-shaft and an upstream reduction gear. An annular plate-shaped exchanger is installed in the axisymmetric portion of the ejector. The exchanger includes inlet and outlet channels, connected to the inlet and outlet of a central channel wound into a helix shape or sine curve in the annular plate. The channels are connected at the other ends to mechanical or electromechanical mechanisms for recovering and recycling energy. The energy is recovered via a cold fluid heated in the central channel by transfer of heat from residual gases.

Abstract: To achieve accurate and rapid acquisition or distribution of fluid—at multipoints—with good spatial resolution and minimal bulk, a twisted arrangement of ducts is provided in the acquisition/distribution zone making it possible to perform several acquisitions/distributions over several heights with one and the same device. The device is a pressure probe in which a probe body exhibits a first part or section for acquiring pressure forming a cylinder less than 6 mm in diameter. The probe exhibits internal ducts forming parallel helicoidal traces on the section and channels formed in a metal alloy body between the ducts and inlet orifices. The number of internal ducts is advantageously equal to nine, including three orifices being disposed over three different heights of the probe body.

Abstract: A combustion chamber, for example for a turbine engine, presenting an inner annular wall, an outer annular wall, and a pierced annular chamber end wall extending around an axis, the chamber end wall including at least one opening receiving a fuel injector, the opening being substantially centered on a circular line defining a first chamber end wall portion extending radially between the circular line and the inner annular wall, and a second chamber end wall portion extending radially between the circular line and the outer annular wall. First and second channels are inclined relative to a normal vector normal to the chamber end wall while extending tangentially, the first channels arranged to provide a flow of air in a first rotary direction, the second channels arranged to provide a flow of air in a second rotary direction opposite to the first rotary direction.

Abstract: A method for maintaining efficiency and duty of a turbine engine compressor to reduce specific consumption, while guaranteeing a high enough pumping margin with partial load. The method adapts airflow to a variable demand for flow or mechanical or electric power in a centrifugal compressor of a turbine engine. The method includes diffusing the airflow through a first annular blade ring having variable pitch blades, radially bordered by a second annular blade ring having a same number of fixed pitch blades with an equivalent extension, guiding the radial extension diffusion by coupling the blades of the two blade rings. According to the method, each blade of the first blade ring is spun off-axis.

Abstract: A noise-attenuating covering configured for example for a pipe for guiding gases along a gas path. The covering includes a wall defining the gas path and at least one resonance cavity, the wall being pierced with holes for fluid communication between the gas path and the resonance cavity to attenuate noise. The holes have substantially identical diameters and, since the pipe is arranged to guide the gases in the downstream direction, a number of the openings per wall surface unit decreases continuously along the gas path in the downstream direction, such as to confer on the wall substantially constant acoustic resistance along the gas path, for which the noise attenuation is optimized along the gas path.

Abstract: A device for ejecting gas from a gas turbine engine, which includes: an outer wall and an inner wall defining a gas flow path therebetween, the inner wall forming a central body defining an inner cavity, the outer wall being perforated and communicating with at least one outer resonance cavity for attenuating noise in a first range of sound frequencies; and a mechanism for placing the outer and inner cavities in fluid communication, extending through the gas flow path, the inner cavity thus forming a resonance cavity for attenuating the noise in a second range of sound frequencies. The device can, for example, be used to attenuate two ranges of sound frequencies.

Abstract: An assembly including a part for mounting at least one shaft bearing of a turbine engine and a support part that forms an abutment for the mounting part. The mounting part includes at least one channel through which engine gases pass, and connection parts that are capable of connecting the channel to an outer structure of the engine and to a housing holding the bearing. At least one of the connection parts is flexible so as to enable radial movement of the channel, an amplitude of the radial movement being limited by at least one of the elements of the mounting part coming onto an abutment supported by the support part. The support part extends longitudinally with regard to the direction of the rotational axis of the turbine engine so as to generate a turbine shroud that is configured to be positioned in alignment with a turbine wheel of the turbine engine.

Abstract: A turbomachine includes a compressor, a first shaft, a second shaft, a first turbine, and a second turbine. The first shaft carries at least one turbine wheel belonging to one of the elements selected from the first and second turbines. The second shaft carries at least one turbine wheel belonging to the other element selected from the first and second turbines. The first and second shafts are oriented substantially vertically in normal utilization situations of the turbomachine. The first shaft is held by a first single bearing while the second shaft is held by a second single bearing.

Abstract: A low-cost combustion chamber injector device that has sturdier construction and is safer for use. Parts are configured specifically to be nested, to dispense with welding between the cellular parts. The device for injecting a fuel-air mix includes, centered on a single axis, a swirl chamber including at least two annular air suction parts, a centering guide, and a retainer ring. The annular parts have cellular conduits connecting to axial inner and outer Venturi tubes. The parts are coaxially mounted, the inner part being configured to be self-centered in the outer part by engagement of the axial and radial walls and then, after assembly, the outer part is welded to the retainer ring and to the inner part in a single radial plane.

Abstract: The soundproofed exhaust duct for a turbine engine comprises a perforated inner shell defining a flow passage, and a solid outer shell, the inner and outer shells defining between them a space that is closed at the upstream and downstream ends of said space. A core extends between the inner and outer shells at a distance therefrom, and contains at least one sound energy dissipating layer made up of hollow beads that are held against one another. A frame with upstream and downstream portions connected together by longitudinal members supports the core and partitions it into a plurality of boxes that are filled with hollow beads that are held between perforated textures, the frame being secured to the outer shell and/or to the inner shell via at least one of its upstream and downstream portions.

Abstract: A method and system for cooling turbine engine turbines, the system includes: at least one pair of parts to be cooled, the pair including a stator upstream from the rotor valve, and a sealing ring mounting a downstream movable blade rotor that is adjacent to the stator; a turbine casing; and an outlet path. The system further includes: at least one opening in the casing facing at least one part to be cooled; and an air circuit producing a forced convection in connection with the parts and at least one downstream outlet in the path so as to draw in and transport an ambient air flow.

Abstract: A method for ground control of proper operation of an aeronautical turbine engine for a plane. A test includes carrying out, on the operating turbine engine and from a predetermined speed, a quick reduction in fuel flow according to a programmed decrease to evaluate flame-out resistance of the combustion chamber of the turbine engine during a quick inflight deceleration maneuver of the speed thereof.

Abstract: A method to prevent blockage of air passages in curvic couplings between drive parts and to prevent potential damage to the drive parts during weakening of protective elements. To this end, axial abutments are formed by ring gears of the curvic couplings. A coupling includes two rings, each ring being on the end of one drive part and engaged with the other so as to transmit to the drive part a rotation around a central axis while allowing air to pass between male and female portions of the teeth of the rings behind a bearing area. The rings are extended in an at least partially radial manner relative to each other to form an outer ring extension and an inner ring extension respectively facing elements surrounding the drive part that are mounted onto the other ring. The rotor lines can be used in turbine engines.

Abstract: A turbine wheel having an axis of rotation and including: a disk having a periphery and a side face; a plurality of blades assembled on the disk, each blade having a blade root and a first hook oriented radially and defining a first groove that opens radially towards the axis of rotation of the turbine wheel. The disk includes a series of second hooks oriented radially and defining a second groove that opens radially towards the axis of rotation of the turbine wheel. An axial retaining ring for placing in the first and second grooves includes a tab for placing between two adjacent blade roots to limit movements of the ring in azimuth.

Abstract: A device for filtering intake air of an internal combustion engine, including at least one filtering element including an inlet for air being treated, a first clean air outlet toward the engine, and a second air outlet toward the outside, and a ventilation mechanism driving the air from the second air outlet. The ventilation mechanism includes a fan wheel driven by a turbine set into motion by a gas flow taken from the engine.