The present description relates to a device (30) for positioning an inspection tool (130) with respect to a flange (10) of a casing (1). This device (30) comprises a first positioning piece (40) and a second positioning piece (70) which are assembled with one another. The first piece (40) comprises a fixing part (45...

Assistance device (100) for an aircraft free turbine turbomachine (TAG1) the device comprising means (K11 CVS1) for electrically powering a coil (SU) of a rotary starter machine (GD1) referred to as first coil in order to provide a first acceleration assistance to the gas generator of the turbomachine (TAG1). The de...

Assistance device (100) for a free turbine turbomachine (TAG1) of an aircraft comprising at least two free turbine turbomachines (TAG1 TAG2) the device comprising an electric starter machine (D1) for providing prolonged assistance to the gas generator of a first turbomachine (TAG1) using energy produced by an electr...

Method for notifying an authorization to completely shut down an aircraft gas turbine engine and aircraft gas turbine engine comprising a device for such notification the method comprising following the detection (E10) that the engine has switched to low idle: • (a) a step (E20) of evaluating from a value of a first...

The invention relates to a particle trapping device (2) for a turbomachine said particles being contained in an air stream flowing inside a turbomachine in particular the air stream flowing in the bypass region (17) of the combustion chamber (13) of said turbomachine. The device is characterised in that it comprises...

The invention relates to an assembly for a turbine engine (1). The assembly includes a mount (4) a nut (3) clamping around the male portion of the mount (4) a member (10) projecting from the mount (4) and a device for limiting loosening of the nut (8 9). The loosening limitation device (8 9) includes a member (8) fo...

The quick assist device applies to a free turbine turbomachine (11) of an aircraft comprising at least a first free turbine turbomachine (11) provided with a gas generator combined with an electric machine (12) that can operate as a starter and as a generator the first turbomachine (11) being capable of being brough...

The invention relates to the field of magnetohydrodynamic generators and more specifically to such a generator (10) including a flow duct (11) for a working fluid delimited by a first wall (12) and a second wall (13) a working fluid ionization device (14) a pair of arms (15) each connecting the first and second wall...

The invention relates to a helicopter comprising a structural frame (5) at least one main lift and propulsion rotor (10) secured to said structural frame (5) and a drive train for moving said main rotor (10) comprising a power transmission box (11) and at least one main motor (12a 12b) characterised in that it also ...

The invention relates to a hydraulic torquemeter comprising a rod (30) translatably mobile in a longitudinal direction under the effect of an axial thrust (31) representing the torque to be measured and a hydraulic circuit (40) in which a fluid (38) flows. The invention also comprises a manometric capsule (46) compr...

The invention relates to an ignition system of a combustion chamber (2) of a turbo engine comprising: a plurality of start up injectors (21a 21b 31a 31b) capable of injecting fuel into said chamber (2) during a combustion initiation phase; a fuel supply circuit (6) of said start up injectors comprising a first sub c...

The invention relates to a removable pack for reactivating a helicopter turboshaft engine (6) including a gas generator (7) provided with a drive shaft (12). Said turboshaft engine (6) is capable of operating in at least one standby mode during a stabilized flight of the helicopter. Said removable pack includes: a r...

The invention relates to an architecture for a propulsion system of a multi engine helicopter including turboshaft engines connected to a power gearbox. Said architecture is characterized in that it includes:  at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stabi...

The hybrid propulsion system for a multi engine aircraft comprises a plurality of free turbine turbomachines each one equipped with a gas generator these including at least one first turbomachine (1) or hybrid turbomachine able to operate in at least a standby state during a stabilized flight of the aircraft while o...

The invention relates to a propulsion unit (10) notably for an aircraft comprising  a turbomachine (12);  a propeller (14) that can be selectively coupled to said turbomachine (12);  a rotary electrical machine (16) able to drive at least the turbomachine (12) characterized in that it comprises means (20) of selecti...

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (8 9) and a receiver unit (10) each rotating about a same axis (7) of rotation said fuse comprising a body (13) extending in a longitudinal direction parallel to said axis (7) of rotation once the fuse is mounted between s...

The invention relates to a System (12) for recovering exhaust gas energy from at least one turboshaft engine, comprising a turbine (34) rotatably mounted about a recovery shaft (40), suitable for collecting at least one portion (14) of the exhaust gases, referred to as collected gases (14), and to expand said coll...

The invention relates to a system for the emergency starting of a turbomachine characterized in that it comprises a spinner for driving the turbomachine said spinner comprising a drum (2) secured to a rotation shaft (3) the axes of symmetry (LL) of the drum (2) and of the shaft being coincident the spinner furth...

The invention relates to a constant volume combustion system (3) for a turbine engine. Said system includes:  a plurality of combustion chambers (11 14) regularly distributed around a longitudinal axis (AX);  a toroidal manifold (7) including a radially oriented outlet for supplying compressed air from a compressor ...

The invention relates to an annular turbine engine combustion chamber having an axial direction (X) a radial direction and an azimuthal direction. Said chamber includes a first annular wall (12) and a second annular wall (14). Each wall defines at least part of the enclosure of the annular combustion chamber. The fi...

The invention relates to an emergency start device for a helicopter turbine engine (6). Said device is characterized in that it includes:  a hydraulic engine (7) mechanically connected to said turbine engine (6);  a hydropneumatic storage device (9) connected to said hydraulic engine (7) via a hydraulic system (10) ...

The invention relates to a method and a device for optimized global management of an energy network of an aircraft comprising a plurality of energy related equipment characterized in that it comprises a module 40 for selecting at least one optimization objective (19) from among a plurality of predetermined objective...

The invention relates to a turboshaft engine for a helicopter comprising a case (5) inside which a gas generator (6) and a turbine (7) are accommodated the turbine (7) being mounted on a power shaft (8) that extends along a longitudinal direction (X X) the turboshaft engine further comprising means for removably mou...

The invention relates to an architecture of a multi engine helicopter propulsion system comprising turbine engines (1 2) connected to a power transmission gearbox (3) and a low voltage on board DC network (7) intended to power helicopter equipment during flight characterized in that the architecture comprises: a hyb...

The invention relates to an architecture of a multiple engine helicopter propulsion system comprising turbine engines (1 2) which are connected to a power transmission gearbox (3) comprising: a hybrid turbine engine (1) able to operate in at least one standby state during steady stabilized flight of the helicopter; ...

The invention relates to a flow limiter which comprises a body (1) comprising a fluid intake (2) and a fluid outlet (3) in which body a pipe (5) for circulating the fluid is provided comprising a series of chambers having different cross sections connected to the fluid intake as well as to the fluid outlet the pipe ...

The invention relates to a turboshaft engine comprising a case (5) inside which a gas generator (6) and a free turbine (7) are accommodated the turbine (7) being mounted on a power shaft (8) designed to be mechanically coupled to/uncoupled from a reduction gearbox (10) characterized in that said turboshaft engine co...

The invention relates to a method for detecting a failure of a first turbine engine referred to as faulty engine (4) of a twin engine helicopter and for operating a second turbine engine referred to as sound engine (5) each engine (4 5) comprising protection end stops regulated by a regulating device which define a ...

The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator. The turboshaft engine is characterised in that it comprises a device (40) for the controlled mechanical coupling of the gas generator (5) and the free...

The invention mainly relates to a turbine engine combustion chamber module (4) comprising at least one constant volume combustion chamber (7). Said module is characterized in that it also comprises upstream of said at least one constant volume combustion chamber (7) a precombustion chamber (6) capable of producing h...

The invention relates to a ring shaped combustion chamber (10) comprising a first ring shaped wall (12) and a second ring shaped wall (13) which are coaxial about an axis (X) a chamber bottom (14) connecting the first and second walls (12 13) and a plurality of injectors (16) the first wall (12) comprising first air...

The invention relates to a blade of a turbomachine guide vanes assembly which blade is equipped with a cooling system comprising an insert (22) arranged inside an internal cavity (24) of the said blade connected to an inlet (26) for blade cooling air and designed to cool the surface of the internal cavity (24) of th...

The invention relates to an aircraft engine part (1) comprising at least one metal substrate (2) and an erosion protective coating (3) present on the substrate the coating comprising at least one phase (4) comprising at least chromium in an atomic content greater than or equal to 45% and carbon in an atomic content ...

The invention relates to a device for rapidly reactivating a helicopter turbine engine (6). Said device is characterized in that it includes an air turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure the reactivation thereof;  a pneumatic storage device (9) connecte...

The present invention relates to an assembly for a turbomachine combustion chamber (20) comprising: a boss (32) for turbomachine combustion chamber (20) comprising a tubular body (33) configured to be inserted in a receiving orifice (29) formed in an annular wall (25) of a flame tube (24) and to accommodate a shank ...

Actuating system for an aircraft comprising: - an electromechanical actuator (25) comprising a non-volatile memory (60) wherein stored data (61) including configuration data (62) specific to the electromechanical actuator is stored; - a control unit (22) using the configuration data to implement a servo-control lo...

The invention relates to a device intended for implementation of an anodization treatment of a part the device comprising:  a treatment chamber comprising a part to be treated and a counter electrode situated opposite the part to be treated the part to be treated constituting a first wall of the treatment chamber  a...

The invention concerns a device (100) for attaching at least one sensor in particular a thermocouple device to a part comprising a first attachment portion (10) provided with means (14) for attachment to the part and a second attachment portion provided with an opening for receiving the sensor (90). According to the...

A transmission assembly for an aircraft and a helicopter comprising such an assembly for independently adjusting the speed of rotation of an engine and a torque receiver. According to the invention the assembly comprises a first input shaft (10a) configured to receive mechanical torque from a first engine (10) an ou...

The invention concerns a drive chain intended to drive the rotor or rotors (21 22) of a helicopter comprising a main transmission housing (24) capable of driving the rotor or rotors (21 22) when it is moving a main engine (23) intended to provide power for flight and at least one assistance drive module (31) the mai...

The invention concerns an architecture of a propulsion system of a multi engine helicopter comprising turboshaft engines (5 6) characterised in that it comprises: at least one hybrid turboshaft engine (5) capable of operating in at least one standby mode during a stabilised flight of the helicopter the other turbosh...

The invention relates to a turboshaft engine comprising a gas generator (5) designed to be rotated and a free turbine (6) rotated by the gases from the gas generator (5). The turboshaft engine is characterised in that it comprises a device (20) for the spontaneous mechanical coupling of the gas generator (5) and the...

The invention relates to a device for testing the integrity of a rapid restart system for a helicopter turbine engine (5) comprising a pneumatic turbine connected mechanically to said turbine engine (5) and supplied with gas on demand by a pneumatic supply circuit (8) so as to be able to spin said turbine engine (5)...

The invention relates to a torque meter comprising a casing (12) in which a translationally movable part (14) may move in a longitudinal direction under the effect of an axial pressure representative of the torque to be measured. The torque meter is characterised in that it comprises: a bearing surface (22) connecte...

The invention relates to distributor blading (10) having a blade (12) including a pressure side wall (16) and a suction side wall (14) and an insert (20) placed in the blade (12) and including: a closed wall (22) having an outer skin (24) extending opposite the pressure side walls (16) and suction side walls (14) th...

The invention relates to a twisting torque sensor comprising a transmission shaft (12) subjected to the torque to be measured a reference shaft (14) and a device for measuring an angular deformation representing the torque to be measured between the two shafts. The torque sensor is characterised in that the transmis...

In order to reduce the weight of a hybrid propulsion system (30) for a multi-rotor rotary-wing aircraft the system comprises at least one inverter (36) configured to supply power in parallel to multiple electric motors (46A 46B) intended to drive the corresponding propellers of the system.

The electrical machine according to the invention is a dual machine and comprises a first machine (32 33 34) which can be reversed and a second machine (30 35) functioning through induction between two windings. The second machine can be used for de-icing a propeller the induction-receiving winding (30) being mounte...

The invention relates to an auxiliary system for mechanically driving a relay shaft (8) of a helicopter propulsion system comprising: a hydraulic motor (7) mechanically connected to said relay shaft (8); a hydraulic circuit (10) for supplying a pressurised liquid to said hydraulic motor (7); a controlled fast-openin...

The invention relates to a system for deoiling an air-oil pressurising mixture (11 12) for pressurised enclosures (13) of a turbine engine said system comprising: at least one centrifugal degasser (20); at least one mechanical casing (30) of the turbine engine comprising a plurality of mechanical parts (21 22) at le...

The invention relates to a turbine engine fuel injection architecture including: two fuel injection manifolds (30A 30B) each manifold being suitable for dispensing a fuel flow to at least one associated injector; a main fuel proportioning device (32) suitable for proportioning a total fuel flow (Q) to be supplied to...

The aircraft turbine engine rapid reactivation system includes an electrical machine (60) supplied with DC power by an onboard electrical power supply network (10). The system also includes:  a switch (50) positioned between the onboard network (10) and the electrical machine (60);  an additional assembly (30) inclu...

The invention relates to a turbine engine combustion assembly (20) which includes: an annular flame tube (21) including a front wall (23) a rear wall (24) and a bottom (22) arranged facing an engine shaft (30); an injection wheel (41) rotated by said engine shaft (30) partially projecting into the bottom (22) of the...

The invention relates to a device for controlling a propeller having variable pitch blades of a turboprop engine including a first hydromechanical device (10) for controlling the pitch of the blades of the propeller and a second hydromechanical device (20) for controlling the speed of rotation of the propeller chara...

Gas turbine combustion chamber injector (1) comprising - a fluid supply system (5) - an injector body (4) extending along a longitudinal axis (Z-Z) - an injection head (6) arranged on the injector body (4) and configured in such a way as to spray the said fluid in a direction (X-X) that is inclined with respect to t...

The invention concerns an assembly comprising: a fuel supply circuit (15, 15a, 15b) configured to supply fuel to a turbine heat engine, an electronic module (14, 14a, 14b), a power source (13, 13a, 13b) for supplying power to the electronic module (14, 14a, 14b), and a heat exchanger (16, 16a, 16b) positioned to all...

Adjustable-length connecting rod (40) for an aircraft turbomachine (10), this connecting rod having a generally elongate shape and comprising two longitudinal opposite ends (42, 50) for attachment to elements to be connected, characterised in that: • - a first (42) of these longitudinal ends is connected to a first ...

The invention relates to an electric actuator for air intake flaps of a gas turbine engine comprising a fixed part (104) attached to a stationary part of the engine and a moving part (102) mechanically connected to the air intake flaps, this electric actuator (100) comprising, uniformly distributed at the periphery ...

The invention relates to a fuel supply system (20) for a turbomachine. The supply system (20) comprises a starter circuit (120) at least one first hydraulic resistance (124 136) and a purge circuit (130). The purge circuit (130) comprises a duct (131) comprising an opening (133) at the exterior of the supply system ...

The invention relates to a turbomachine blade (1) comprising: an external enclosure (10) comprising a pressure-side wall (11) and a suction-side wall (12) delimiting an interior volume therebetween; an insert (30) arranged in the interior volume so as to form an air passage (40) between the insert (30) and the exter...

The invention relates to a hybrid turboprop engine (100) for an aircraft, comprising: a gas generator (12) which is supported by a generator shaft (14); a free turbine (11) which is supported by a turbine shaft (13) and rotated by a gas flow generated by the gas generator (12), the turbine shaft (13) meshing with a ...

A disengageable coupling assembly (2) for an aircraft propulsion assembly (1) comprises a first shaft (4) and a second shaft (6); a coupling sleeve (8) movable between positions of coupling and of uncoupling the shafts; fluid chambers defined between the coupling sleeve and the shafts; a tube (10) extending into a b...

The invention relates to a propulsion assembly (100) comprising a first and second engine (1, 2) each having a gas generator (12, 22) and a free turbine (11, 21), a main rotor (62) coupled to the free turbine (11, 21), the engines (1, 2) each comprising a first electric machine (30, 40) coupled to the gas generator ...

Disclosed is a hybrid turbomachine (10), in particular for a rotary-wing aircraft, comprising a gas generator (13) having a first shaft (16), at least one electric machine (11) having a second shaft (17), and a rotating equipment (15) coupled to a third mechanical shaft (18). The hybrid turbomachine (10) further com...

A system (2) for the transmission of propulsion power of a propulsion assembly (1) for an aircraft comprises means (12) for coupling a first rotating element (4) with a second rotating element (8), and an actuator (10) for moving the second rotating element (8) axially between a coupling position in which the coupli...