Abstract: A starting injector usable in all flight modes without additional cost or weight. The starting injector includes a dual fuel circuit and an air circuit. An injector for a combustion chamber of a gas turbine includes a dual fuel injection circuit including a starting fuel circuit for ignition and then for all the flight modes, and a main fuel circuit for all the flight modes after starting. The circuits include parallel pipes in a common tube having an axis. The pipe of the starting circuit is substantially in communication with a center of a spherical injector body. At the end, the pipe accommodates an injection manifold coupled to a central channel passing through a central wall of a swirler. The pipe of the main circuit is in communication with an annular channel opposite jet channels. An air circuit is guided between two portions shaped as concentric spheres.

Abstract: A monitoring device for monitoring rotors of turbines, including: an acoustic sensor; and a sound waveguide for connecting the acoustic sensor to a sensing point close to the rotor of the turbine. The acoustic sensor is configured to detect, as soundwaves, pressure fluctuations due to pressure differences between suction and pressure sides of blades of the rotor as they move past in proximity of a sensing point. A method of monitoring a rotor of a turbine transmits pressure fluctuations due to pressure differences between suction sides and pressure sides of blades of the rotor going past the proximity of a sensing point by a sound waveguide to an acoustic sensor to be picked up as soundwaves.

Abstract: A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation.

Abstract: A device and method for providing mechanical protection, and in particular to a mechanical protection device including a transmission shaft with a resonant frequency in bending that corresponds to a predetermined rotary overspeed of the transmission shaft, the transmission shaft being insufficiently damped to avoid breakage of the transmission shaft as a result of the resonance in bending. In the mechanical protection method, the transmission shaft breaks as a result of this resonance in bending.

Abstract: A turbine wheel with optimal-mass dampers to dampen a predetermined resonance in context of vibration of a turbine, particularly a low-speed turbine, while assisting in flexibility of adapting to bearing surfaces of recesses of the dampers, by separating mass and flexibility functions by a flexible portion for clamping against the platform, and a mass portion for controlling frictional forces. A damper includes a plate and a counterweight. The plate is stamped from a metal sheet that is substantially thinner than that of the counterweight. The plate includes a wall configured to flexibly contact a platform of the blade of the wheel, while at least partially surrounding a surface of the counterweight. The damper can be used in particular for a wheel of a turbine of a turbine engine, of a fan, or of a BP compressor having mounted blades.

Abstract: The present invention relates to a coupling system comprising a coupling for fastening to one end of a pipe via a fastening connection, said coupling system further including safety fastener means in the form of a sleeve surrounding the fastening connection and having a first end for welding to the pipe, and a hook-forming second end for co-operating with the coupling in such a manner that the hook is suitable for providing fastening between the coupling and the pipe in the event of the fastening connection being damaged.

Abstract: A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acceleration/deceleration power of the gas generator by adjusting voltage of an electric network onboard the aircraft. After a phase of starting the gas turbine, voltage of the onboard network is adjusted by a voltage set value controlled by determining unballasting/ballasting status of a main electricity generation source of the onboard network. The status-determining is executed according to demand for taking power to be supplied for propulsion of the aircraft. The status-determining is followed by selecting a voltage set value from plural levels according to the determining the unballasting/ballasting status, and applying the selected set value to a control loop of the voltage supplied to the onboard network.

Abstract: A method and architecture to reduce specific fuel consumption of a twin-engine helicopter without compromising safety conditions regarding minimum amount of power to be supplied, to provide reliable in-flight restarts. The architecture includes two turbine engines each including a gas generator and with a free turbine. Each gas generator includes an active drive mechanism keeping the gas generator rotating with a combustion chamber inactive, and an emergency assistance device including a near-instantaneous firing mechanism and mechanical mechanism for accelerating the gas generator. A control system controls the drive mechanism and emergency assistance devices for the gas generators according to the conditions and phases of flight of the helicopter following a mission profile logged beforehand in a memory of the system.

Abstract: A system for real time simulation of the environment of an aeroengine includes a digital computer having its inputs switched by a selection module included in the computer either to a respective sensor or else to a substitution digital bus configured to convey substitution digital data generated by a real time simulator.

Abstract: A lubrication device including a bypass valve with an inlet connected to a feed circuit, a first outlet to be connected to elements to be lubricated, and a second outlet connected to a bypass circuit. The valve includes a valve member slidable between first and second positions, and separating a cavity into first and second chambers. The first chamber is connected to the inlet. In the first position, a fluid flow passage from the first chamber to the second chamber is open, and from the first chamber to the first outlet is closed. In the second position, a fluid flow passage from the first chamber to the first outlet is open, and from the first chamber to the second outlet is closed. At least in the second position, the valve member separates the chambers in substantially leaktight manner, while the second chamber remains in fluid flow communication with the second outlet.

Abstract: An attachment arrangement at a middle of a cover having an elastically deformable portion. The cover includes a concave shell including an inner surface spaced apart from the compressor including an impeller including blades by an attachment. The attachment includes one connection end at the middle of the shell, another end attached to a casing of the turbine engine, and an axisymmetric diaphragm having a generally frusto-conical configuration having an arm profile coupled to the end for attachment to the casing by a double-elbow joint having right and obtuse angles when in a rest position. The distance between the inner surface of the shell and upper edges of the blades can be held constant during operation with minimum clearance adjustment. The cover can be moved such that clearance between the cover and blades of the compressor impeller remains substantially constant and as low as possible.

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 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 method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.

Abstract: A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraft including, in an environment near the cabin, at least one main power-generating engine, sized to serve as a single pneumatic energy-generating source for the cabin and as an at most partial propulsive, hydraulic, and/or electric energy-generating source for the rest of the aircraft. The method minimizes power differential between a nominal point of the power sources when the sources are operating, and a sizing point of non-propulsive energy contributions of the sources when the main engine has failed, by equally dividing power contributions of the main engines and the main power generator under nominal operating conditions and in an event of failure of a main engine.

Abstract: A coupling system including a coupling for fastening to one end of a pipe via a fastening connection; and a sleeve surrounding the fastening connection is disclosed. The sleeve includes a first end for welding to the pipe, and a hook-forming second end for co-operating with the coupling in such a manner that the hook is suitable for providing fastening between the coupling and the pipe in the event of the fastening connection being damaged.

Abstract: A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.

Abstract: A method for optimizing operability of an aircraft propulsive unit, and a self-contained power unit implementing the method. The method removes mechanical bleed constraints in engines during transient flight phases of an aircraft to optimize operability of the engine assembly during the phases. To this end, a supply of power is provided, particularly during the phases, by an additional indirectly propulsive engine power source. The method for optimizing operability of the propulsive unit of an aircraft including main engines as main drive sources includes, using a main engine power unit GPP as a power source, providing all the non-propulsive power and, during the transient engine phases, at most partially providing additional power to the body of the main engines.

Abstract: A coupling system including a coupling for fastening to one end of a pipe via a fastening connection; and a sleeve surrounding the fastening connection is disclosed. The sleeve includes a first end for welding to the pipe, and a hook-forming second end for co-operating with the coupling in such a manner that the hook is suitable for providing fastening between the coupling and the pipe in the event of the fastening connection being damaged.

Abstract: A control device for controlling pivotable vanes of a turbo-machine, including: a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; and a control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links; wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with other links being connected to the ring portion via respective sliding pivot connections.