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No. Publication Number Title Publication/Patent Number Publication/Patent Number Publication Date Publication Date
Application Number Application Number Filing Date Filing Date
Inventor Inventor Assignee Assignee IPC IPC
1
US10161446B2
Plain self-centering bearing
Publication/Patent Number: US10161446B2 Publication Date: 2018-12-25 Application Number: 15/528,143 Filing Date: 2015-11-17 Inventor: Morreale, Serge René   Assignee: Safran Aircraft Engines   IPC: F16C32/06 Abstract: A mechanical assembly includes two mechanical parts rotatable relative to each other. A first part is provided with a cylindrical cavity, a second part (34) has at least one cylindrical portion engaged in the cylindrical cavity of the first part, and a gap separates the cylindrical portion and the wall of the cylindrical cavity so as to allow relative movement in rotation between the first part and the second part (34). A lubricant distribution network (37, 38) is configured for feeding the gap with a fluid lubricant so as to form a fluid bearing. A first surface (34s) selected from the inside surface of the cylindrical cavity of the first part and the outside surface of the cylindrical portion of the second part is provided with at least two lubricant admission orifices.
2
US10073050B2
Assembly for capacitive measurement of the amount of gas in a fluid flow
Publication/Patent Number: US10073050B2 Publication Date: 2018-09-11 Application Number: 15/524,950 Filing Date: 2015-11-04 Inventor: Bruere, Alain   Nivet, Philippe   Fammery, Simon   Assignee: Safran Aircraft Engines   IPC: G01R27/26 Abstract: An assembly comprising an upstream pipe, a downstream pipe, and a system (1) for measuring variation in the gas content of a two-phase flow, the assembly including: an insulating sheath (6), an upstream ground (2), a measurement electrode (3), a guard electrode (7), and a downstream ground (4) arranged in succession in the insulating sheath (6) and each presenting an identical internal section defining an internal flow duct for a two-phase flow from the upstream ground (2) towards the downstream ground (4) in line with the upstream pipe and the downstream pipe, the guard electrode (7) being subjected to the same potential as the measurement electrode (3), the measurement electrode (3) measuring the capacitance of the two-phase flow relative to the upstream ground (2) and variation in that capacitance, the upstream ground (2) and the downstream ground (4) being electrically connected to the upstream pipe and to the downstream pipe, respectively.
3
US10101300B2
Device for inspecting a surface of an electrically conductive part
Publication/Patent Number: US10101300B2 Publication Date: 2018-10-16 Application Number: 14/903,155 Filing Date: 2014-06-26 Inventor: Chatenet, Luc Henri   Assignee: Safran Aircraft Engines   IPC: G01N27/90 Abstract: A device for inspecting a surface of an electrically conductive part, the device having a plurality of eddy current probes arranged on a convex surface of the device together with an applicator for applying the probes against the surface to be inspected into which the device is inserted, wherein the probes are fastened on flexible strips extending beside one another in a longitudinal direction of the device, the applicator including a deformable material, that, on being compressed along the longitudinal direction, gives rise to expansion transversely to the longitudinal direction, the expansion deforming the strips so as to apply the probes against the surface.
4
US10112330B2
Mould, particularly injection mould, and injection moulding method using such a mould
Publication/Patent Number: US10112330B2 Publication Date: 2018-10-30 Application Number: 15/113,992 Filing Date: 2015-01-27 Inventor: Jaussaud, Raoul   Techer, Marc-emmanuel   Nord, Richard   Assignee: Safran Aircraft Engines   IPC: B29C45/40 Abstract: A mold (10) comprising a plurality of blocks (11, 13) that, in an assembled position, define a mold cavity, the mold being characterized in that it includes at least one pusher (21), said pusher (21) being configured to be housed in a first block (11) of said plurality, in a side facing the mold cavity, and, when the pusher (21) is housed in said first block (11), to present a first surface (S1) flush with the mold cavity, and in that the mold (10) also includes actuator means (23, 25) enabling the pusher (21) to be moved relative to the first block (11), and sealing means (19, 27) configured to isolate the actuator means (23, 25) from the mold cavity. An associated molding method.
5
US10126228B2
Peeling test device
Publication/Patent Number: US10126228B2 Publication Date: 2018-11-13 Application Number: 15/524,499 Filing Date: 2015-11-06 Inventor: Brossier, Pascal Noël   Berranger, Thibault   Chichery, Emmanuel   Gani, Léa   Timon, Alain   Assignee: Safran Aircraft Engines   IPC: G01N19/04 Abstract: A device to test the peeling resistance of coupons, each formed of a support and an adhesive, includes: (i) a frame including rollers with parallel axes designed to maintain the coupon supported while guiding movement of the latter, (ii) a traction device including a vertical jack linked to an attachment element including a loop configured in order to cause detachment of the adhesive from the surface of the support, (iii) a device for measuring the force exerted by the jack in order to pull the loop during peeling, and (iv) a coupon, complex in shape, such as one derived from a reinforced vane. At least one roller is translationally adjustable in relation to other rollers and the coupon is specially prepared in order to facilitate carrying out the tests.
6
US9995224B2
System for supplying pressured air installed in an aircraft turbine engine including sealing means
Publication/Patent Number: US9995224B2 Publication Date: 2018-06-12 Application Number: 15/327,719 Filing Date: 2015-07-22 Inventor: Gallet, François   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D25/24 Abstract: A system for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurization air to a portion of the aircraft for using compressed air from pressurization air collected from a portion for collecting compressed air, characterized in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment.
7
US10047621B2
Sealing plate with fuse function
Publication/Patent Number: US10047621B2 Publication Date: 2018-08-14 Application Number: 15/313,521 Filing Date: 2015-05-26 Inventor: Gustave, Marie-guy Devradj   Barbier-neveu, Antoinette Clelia   Palazuelos, Raymond Miguel   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D25/24 Abstract: The invention proposes an assembly (1) comprising: an exhaust casing (20), rotating about an axis (X-X), comprising a flange (23) for attachment to a mounting (42); a sealing plate (30) for rotation about the axis, the plate being added to the attachment flange of the casing and having a radial section comprising: a radially inner end portion (32), a radially outer end portion (34), and a bend (31) extending between the two end portions, said portions forming therebetween an angle of 80 to 100 degrees, the outer end portion having a length in an axial direction (L34) equal to 15% to 35% of the height (H) of the plate measured in the radial direction around the rotation axis, the outer end portion extending parallel to said axis, and said bend being open in the downstream direction relative to the flow of air.
8
US10077742B2
Technical trial method
Publication/Patent Number: US10077742B2 Publication Date: 2018-09-18 Application Number: 15/034,662 Filing Date: 2014-10-24 Inventor: Le, Gonidec Serge   Reichstadt, Sebastien   Musta, Virgil   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F02C9/00 Abstract: A technical test method for evaluating at least one operating parameter of a device over a sequence of a plurality of operating stages, each stage corresponding to a stable value of at least one operating setpoint of the device. The method including at least sampling values of the at least one operating parameter over time, filtering the sampled values in order to obtain a filtered signal for each operating parameter, calculating the variance of the sampled values for each operating parameter in a sampling window during the operating stage, calculating the absolute value of the time derivative of the filtered signal for each operating parameter, and changing the value of the at least one operating setpoint when, for each operating parameter, the variance of the sampled values and the absolute value of the time derivative of the filtered signal are less than respective predetermined lower thresholds.
9
US10072578B2
Method and system for injecting fuel into an engine combustion chamber
Publication/Patent Number: US10072578B2 Publication Date: 2018-09-11 Application Number: 14/912,523 Filing Date: 2014-08-20 Inventor: Chalaud, Sebastien   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F02C7/22 Abstract: A system of injecting fuel into the combustion chamber of an engine, including at least two fuel circuits, one permanent flow circuit and one intermittent flow circuit, fuel proportioning and distribution devices for proportioning fuel and distributing fuel between the two circuits and a controller. When an order to fill circuits with fuel after the circuit with intermittent flow has been drained is received, the controller is adapted to control the proportioning and distribution devices to obtain a predetermined fuel flow higher than the flow corresponding to the filling order and to supply the resulting surplus of fuel to the intermittent flow circuit for a predetermined duration.
10
US10082444B2
Method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit
Publication/Patent Number: US10082444B2 Publication Date: 2018-09-25 Application Number: 15/033,007 Filing Date: 2014-10-27 Inventor: Veyrat-masson, Antoine   Gomes, Nicolas   Mottet, Lauranne   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F02C7/22 Abstract: A method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit including a fuel tank, an engine fuel system connected to the fuel tank capable of delivering a flow of fuel to the engine depending on a speed of the engine, a fuel return pipe connected between the engine fuel system and the fuel tank, a fuel return valve arranged to switch between an open and closed position, the valve being capable of blocking the fuel return pipe in the closed position, and of bringing the fuel return pipe into communication with the fuel tank in the open position, the method including measuring a pressure of the flow of fuel from the fuel tank, and if the measured pressure is lower than a predefined threshold, measuring the engine speed.
11
US10082445B2
Method for monitoring the change in state of a valve by measuring pressure
Publication/Patent Number: US10082445B2 Publication Date: 2018-09-25 Application Number: 14/003,689 Filing Date: 2012-03-06 Inventor: Djebali, Karim   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D17/08 Abstract: A method for monitoring the change in state of a valve in a start up circuit of a turbo-engine following a command to change the state of the valve includes measuring the air pressure under a fan cowl of the turbo-engine before the change state command, measuring the air pressure under the fan cowl after the change state command, comparing the measured values of the air pressure, and determining whether or not the valve has actually changed state. An aircraft turbo-engine includes a unit that monitors the change in the valve using such a method.
12
US10094740B2
Non-regression method of a tool for designing a monitoring system of an aircraft engine
Publication/Patent Number: US10094740B2 Publication Date: 2018-10-09 Application Number: 14/506,901 Filing Date: 2014-10-06 Inventor: Gouby, Aurelie   Lacaille, Jerome Henri Noel   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: A61B3/00 Abstract: A system of non-regression tests of a designing tool including modules used to build a monitoring device of an aircraft engine is provided. The system includes a processor configured to automatically create an experience base by instrumenting behavior tests upon executing the modules, the experience base including reference input signals, sets of reference parameters, reference output signals, and collections of results of reference executions relating to the modules; start again the behavior tests on the modules depending on the corresponding reference input signals and the corresponding sets of reference parameters thus generating test output signals and collections of results of test executions; and compare the test output signals with the corresponding reference output signals and the collections of results of test execution with the corresponding collections of results of reference executions in order to test the non-regression of the designing tool.
13
US10125630B2
Fan disk for a jet engine and jet engine
Publication/Patent Number: US10125630B2 Publication Date: 2018-11-13 Application Number: 14/782,863 Filing Date: 2014-03-28 Inventor: Bois, Stephane   Accary, Arnaud   Dejaune, Claude   Kiener-calvet, Benjamin   Foll, Julien   Tan-kim, Alexandre   Petard, Benjamin   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D5/14 Abstract: A fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.
14
US10100842B2
Cover of a turbomachine centrifugal compressor capable of being rigidly connected via the downstream side near to the upstream edge of same, and turbomachine comprising this cover
Publication/Patent Number: US10100842B2 Publication Date: 2018-10-16 Application Number: 14/904,880 Filing Date: 2014-07-17 Inventor: Bromann, Alain Marc Lucien   Benderradji, Kamel   Reichert, Pamela Dominique Daniele   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F04D29/42 Abstract: A cover of a centrifugal compressor intended to be rigidly connected to a turbomachine housing, which includes a plurality of ports, is provided. The cover further includes a fastening device for fastening the cover to the housing. A portion of the fastening device is located upstream relative to the ports and can be accessed by a fastening tool through at least one of the ports of the cover. A turbomachine uses this cover to form a sealed space, in particular with a view to collecting air.
15
US10077677B2
Holding device of a cooling tube for a turbojet casing
Publication/Patent Number: US10077677B2 Publication Date: 2018-09-18 Application Number: 14/721,555 Filing Date: 2015-05-26 Inventor: Prestel, Sébastien Jean Laurent   Jouy, Baptiste Marie Aubin Pierre   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D25/12 Abstract: A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.
16
US10107138B2
Device for de-icing a leading edge of a turbine engine by slanting notches
Publication/Patent Number: US10107138B2 Publication Date: 2018-10-23 Application Number: 14/103,360 Filing Date: 2013-12-11 Inventor: Mazet, Hélène   Balland, Morgan   Picart, Jean-yves   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F01D25/02 Abstract: A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction.
17
US10112275B2
Mounting for locking a vane by means of the blade thereof during machining of the root of said vane
Publication/Patent Number: US10112275B2 Publication Date: 2018-10-30 Application Number: 13/582,205 Filing Date: 2011-02-28 Inventor: Dupouy, Olivier   Chacon, Jose   Desmars, Philippe   Heyer, Gerard   Menguy, Jean-paul   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: B25B1/02 Abstract: A mounting for locking a turbine engine vane that includes a blade and at least one portion outside the blade is provided. The mounting can machine the outside portion on a machine tool and includes a stationary jaw for receiving the vane, the jaw including at least six points that form abutments and define a positioning reference system for the vane. The mounting also includes a movable jaw to ensure, during machining the outside portion, holding the vane against the stationary jaw by a clamping mechanism onto the vane blade. The movable jaw includes a first clamping mechanism exerting pressure on one of the surfaces of the blade, the pressure being substantially perpendicular to the surface. The stationary jaw includes a second clamping mechanism exerting pressure on the leading or trailing edge of the blade, the pressure being substantially oriented in the direction of the trailing or leading edge of the blade.
18
US10138170B2
Method of surface marking a mechanical part with a predefined graphical representation visible to the naked eye
Publication/Patent Number: US10138170B2 Publication Date: 2018-11-27 Application Number: 14/434,221 Filing Date: 2013-10-07 Inventor: Bilhe, Pascal   Begue-duthu, Geoffrey   Guipont, Vincent   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: B23K26/36 Abstract: The invention relates to a method of surface marking a mechanical part with a predefined graphical representation, the method comprising using a laser source to apply a single laser pulse to an outside surface of a part for marking, with a mask being interposed between the laser source and the outside surface of the part, the mask having a predefined graphical representation, and the laser pulse having power flux density of at least 20 MW/cm2 and a duration less than or equal to 100 ns.
19
US10138897B2
Blade and blade dihedral angle
Publication/Patent Number: US10138897B2 Publication Date: 2018-11-27 Application Number: 14/778,317 Filing Date: 2014-03-18 Inventor: Cellier, Damien   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F04D29/38 Abstract: The invention relates to a compressor blade, defined at each one of the points of its surface by a sweep angle and a dihedral angle, comprising: a root, a tip, the distance between the root and the tip, measured along an axis referred to as the radial axis, perpendicular to an axis of rotation of the compressor, being referred to as radial height (h), a zone, between the root and the tip, of which a first portion has a strictly positive leading edge dihedral angle, and a second portion has a strictly negative leading edge dihedral angle, the zone of maximum dihedral angle being, along the radial axis, between r=0.25 h and r=0.7 h.
20
US10131453B2
Hall effect thruster and a space vehicle including such a thruster
Publication/Patent Number: US10131453B2 Publication Date: 2018-11-20 Application Number: 15/547,360 Filing Date: 2016-01-28 Inventor: Marchandise, Frederic Raphael Jean   Vial, Vanessa   Zurbach, Stephan   Assignee: SAFRAN AIRCRAFT ENGINES   IPC: F03H1/00 Abstract: A Hall effect thruster arranged inside a wall and including a magnetic circuit and an electric circuit including an anode, a first cathode, and a voltage source. The magnetic circuit and the electric circuit are arranged in such a manner as to generate magnetic and electric fields around the wall. In every meridian section, the magnetic circuit presents an upstream magnetic pole and a downstream magnetic pole arranged at the surface of the wall and spaced apart from each other; and the anode and the first cathode are situated on either side of the upstream magnetic pole.
Total 5 pages