Abstract: The invention relates to a method (1000) for monitoring a degree of coking at dynamic seals of a turbine engine comprising: a gas generator including a rotary shaft and an injection wheel mounted on the shaft; a fuel injection manifold designed to convey fuel to the injection wheel; and dynamic seals designed to provide a seal between the injection wheel and the fuel injection manifold. The method is characterised in that it comprises steps consisting in: measuring (1100) the rotation speed of the gas generator shaft during a turbine engine autorotation phase, and determining (1200) a degree of coking at the dynamic seals, based on changes in the measured rotation speed over time. The invention also relates to a turbine engine equipped with a monitoring system.

Abstract: Air conditioning system for the pressurized cabin of an aircraft, said system (1) being characterized in that it comprises an air withdrawal module (3) configured for withdrawing ambient air from outside the aircraft, an air compression module (5) configured for compressing the withdrawn air flow (F1) and an air cooling module (10) comprising means (15) for storing at least one coolant configured for cooling the compressed air flow (F2, F3).

Abstract: A laser welding head is configured to fasten under a focusing lens for focusing the laser and including at least one annular nozzle for injecting a protective gas, and a protective chamber for protecting the focusing lens with a transverse flow of air. The annular nozzle is arranged around an unobstructed optical axis passing through the laser welding head. The chamber for protecting the focusing lens with a transverse flow of air includes air admission and air exhaust in register with the air admission in a plane substantially perpendicular to said optical axis. The laser welding head is configured to be fastened against the focusing lens without any lateral opening between the focusing lens and the protective chamber. The head presents a distance of at least 100 mm between an outlet of the annular nozzle and the protective chamber.

Abstract: A method of starting a turbomachine, performed by an electronic unit, the turbomachine including a gas turbine engine including at least one rotor and a starter to drive the rotor in rotation, the method including: receiving an order to start the turbomachine, and executing in response to receiving the order to start: a primary acceleration during which the starter is operated to increase speed of rotation of the rotor; a thermal homogenization during which the starter is operated to keep the speed of rotation of the rotor constant or to decrease it until a predetermined condition is satisfied; after the predetermined condition is true, a secondary acceleration in which the starter is operated to increase the speed of rotation of the rotor; and an ignition in which ignition of the engine is ordered.

Abstract: A turboshaft engine including a low-pressure compressor, a high-pressure compressor, a low-pressure turbine, a high-pressure turbine, and a regulator for regulating a speed of rotation of the low-pressure turbine to a speed that is substantially constant. The low-pressure turbine is coupled by a first shaft to the high-pressure compressor, while the high-pressure turbine is coupled by a second shaft to the low-pressure compressor.

Abstract: The invention relates to a method (1000) for monitoring a degree of coking at the dynamic seals of a turbine engine comprising: a gas generator, comprising a rotary shaft and an injection wheel mounted on said shaft, an injection manifold, dynamic seals for ensuring a seal between the injection wheel and the injection manifold, and a starter, the method comprising the steps: measuring (1500), during a phase for initiating rotation of the shaft of the gas generator by the starter, a current flowing through the starter and a voltage on the terminals of the starter, determining (1600), from the measured current and voltage, a degree of coking at the dynamic seals. The invention also relates to a turbine engine comprising a system for monitoring a degree of coking.

Abstract: A turbomachine including: a combustion chamber, with a fuel injection device in the combustion chamber; a supply mechanism supplying fuel to the fuel injection device; a mechanism determining instantaneous variation of fuel flow rate of the supply mechanism; and a regulation mechanism regulating the fuel flow rate of the injection device according to the instantaneous variation of the fuel flow rate of the supply mechanism determined by the determination mechanism.

Abstract: A method for discharging exhaust gas from a gas turbine wherein a number of sectors, position, and angle at the center of at least one sector of a peripheral opening capable of forming an area for reingestion of a primary flow into an engine bay are determined by correlation of interactions between secondary cooling flows and the primary flow, from following behavior parameters: air gyration and speed at an inlet of a pipe, geometry of an exhaust stream, routing of the secondary cooling flow for cooling the engine bay, and a geometry and position of inlets of the secondary flows. The peripheral opening is then closed over the identified at least one angular sector. The method prevents backflow of hot primary air into the peripheral opening formed between a pipe and an ejector of the exhaust stream of a gas turbine.

Abstract: A start-up injector for a turbine engine combustion chamber, said injector including a fuel injection circuit; and a fuel ignition circuit including a fuel injector supplied by the fuel injection circuit and a spark plug for igniting the injected fuel. The start-up injector also includes a partitioned enclosure including a first compartment in which the fuel is ignited by the spark plug and a second compartment separated from the first compartment by a thermally conductive partition; and a main combustion start-up circuit which includes at least one fuel injector supplied by the fuel injection circuit and opens into the second compartment of the enclosure such as to inject the fuel against the wall.

Abstract: A support, for example for a turboshaft engine, or for at least one bearing for a hot section of a turboshaft engine. The support includes at least a central hub incorporating an outer bearing seat for directly receiving the bearing, an annular casing segment around the central hub, and a plurality of radial arms connecting the central hub to the casing segment. The radial arms are inclined in an axial direction and in a tangential direction and are integrated as a single piece with the central hub and with the annular casing segment.

Abstract: The invention relates to a vane (10) of a diffuser (5) for a radial or mixed-flow compressor (2) of an engine (1), including a leading edge (11) arranged facing a flow of gas, a trailing edge (12) being opposite the leading edge (11), a side upper surface wall (13) and a side lower surface wall (14) which connect the leading edge (11) to the trailing edge (12), and a profile including a curved line (15) having at least two points of inflection (I1, I2) between the leading edge (11) and the trailing edge (12). The invention also relates to a corresponding radial diffuser (2).

Abstract: The invention relates to a method for starting an aircraft turboshaft engine, said turboshaft engine comprising a combustion chamber, a compressor shaft on which a compressor wheel is mounted to feed compressed air to said combustion chamber, at least one starter connected to said shaft so as to provide it with a specified starting torque for driving it in rotation. The method comprises accelerating the compressor shaft during a first start-up phase, then stabilizing the rotational speed of the compressor shaft during a second start-up phase. During acceleration of the compressor shaft, the rotational speed of the shaft is regulated such that the acceleration of the shaft remains substantially constant.

Abstract: A test rig combining high-frequency tribological stress and low-cycle fatigue. The test rig includes a first test piece which is fixed to a frame and defines at least one bearing surface, a second test piece which is connected to an actuator for loading the second test piece so that it bears against the at least one bearing surface of the first test piece, a heater configured for heating the test pieces and a vibration generator, such as a shaker, for loading the test pieces in a vibratory manner so as to carry out a fretting fatigue and low-cycle and high-cycle fatigue test. One of the test pieces includes a portion in the shape of a turbine engine rotor blade root and which is inserted in a groove having a shape that is substantially complementary to the other test piece so as to reproduce a turbine engine blade-disc attachment.

Abstract: A device and method for precise measurement of erosion of compressors, without removing an engine, and with easy positioning. A centrifugal compressor of a gas turbine with a radial air inlet includes an impeller including blades and a casing for an air stream to flow in the blades of the impeller. The casing, covered with an abradable coating, includes an annular elbow zone in a substantially median part. Marking depressions of predetermined depths, preferably in groups, are machined in the abradable coating of the zone. Examinations by endoscopy are successively performed to provide an image signal of the markers. Processing the endoscopic signal supplies a number of remaining markers and a criterion for decision on removing the engine is applied thereto. Erosion occurs in the elbow of the casing and evolution thereof may enable monitoring of erosion of other components of the compressor, in particular the blades of the impeller.

Abstract: A low-cycle fatigue test rig reproduces bearing of turbine engine parts. The test rig includes a support member that is fixed to a frame and defines at least one bearing surface. A test piece is connected to a traction element for loading the test piece so that the test piece bears against the at least one bearing surface of the support member. The at least one bearing surface is supported by a support element that is mounted to rotate about a first axis on the support member. The test piece is connected to the traction element for articulation around a second axis that is perpendicular to the first axis. The test rig is configured to enable adjusting and locking the support element and the test piece in positions around the above-mentioned axes.

Abstract: An accessory gearbox for a turboshaft engine of an aircraft, the gearbox including a casing, an aircraft wing flap control rod arranged so as to slide axially inside the gearbox and an actuator for driving the control rod which is mounted on the casing, the actuator including a hollow body, a piston which is arranged so as to move in translation inside the body and a piston rod which is connected to the piston and extends at least in part outside the body of the actuator the piston rod being connected to the control rod, wherein the actuator is arranged between the connection of the piston rod and the control rod, and the casing of the gearbox.

Abstract: A hybrid interrupter member for an electrical circuit, the interrupter member including a static interrupter component and an electromechanical interrupter component. The static component is mounted on a support carrying electrical contacts for the static component, the support being configured, on receiving a command to interrupt, to move in such a manner as to withdraw at least one of the electrical contacts from its respective pin, thereby forming the electromechanical interrupter component.

Abstract: A turbomachine injection manifold assembly including a main circuit for feeding fuel to sets of injectors, and an auxiliary circuit for feeding fuel to a set of injectors. The manifold assembly also includes a double coupling presenting a first endpiece receiving one end of a transfer tube of the main circuit, a second endpiece receiving one end of a transfer tube of the auxiliary circuit, and a mounting surface with a first orifice in fluid flow communication with the first endpiece and a second orifice in fluid flow communication with the second endpiece, the mounting surface of the double coupling being suitable for connecting the double coupling to an injector of said first set of injectors.

Abstract: An impeller of a centrifugal compressor, the impeller including a web and blades secured to the web on a front face of the web. A point of intersection between a trailing edge and a blade root is at least one half-thickness of the web further forward than the blade root at an intermediate diameter of the impeller, and a point of intersection between the trailing edge and the blade tip is also further forward than the blade tip at an intermediate diameter of the impeller.

Abstract: An air/fuel mixer system of a combustion chamber of a gas turbine includes at least one compressed air intake swirler, the swirler having a central axis of symmetry, and a fuel injector including an injection head having an axis of symmetry. Each injector is mounted in the corresponding swirler with aid of a guide mechanism, so that the axis of symmetry of the injection head is off-center with respect to the central axis of symmetry of the swirler. The system can reduce, or even eliminate, combustion instabilities, by injecting the fuel along a particular axis which is off-center relative to the axis of the air/fuel mixer system, inducing a flow of fuel which is no longer perfectly axially symmetrical.