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1
US10112330B2
Publication/Patent Number: US10112330B2
Publication date: 2018-10-30
Application number: 15/113,992
Filing date: 2015-01-27
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. 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 ...more ...less
2
US10161446B2
Publication/Patent Number: US10161446B2
Publication date: 2018-12-25
Application number: 15/528,143
Filing date: 2015-11-17
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. 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 ...more ...less
3
US10126228B2
Publication/Patent Number: US10126228B2
Publication date: 2018-11-13
Application number: 15/524,499
Filing date: 2015-11-06
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. 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 ...more ...less
4
US10101300B2
Publication/Patent Number: US10101300B2
Publication date: 2018-10-16
Application number: 14/903,155
Filing date: 2014-06-26
Inventor: Chatenet, Luc Henri  
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. 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 ...more ...less
5
US10073050B2
Publication/Patent Number: US10073050B2
Publication date: 2018-09-11
Application number: 15/524,950
Filing date: 2015-11-04
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. 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 ...more ...less
6
US9995224B2
Publication/Patent Number: US9995224B2
Publication date: 2018-06-12
Application number: 15/327,719
Filing date: 2015-07-22
Inventor: Gallet, François  
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. 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 ...more ...less
7
US10072508B2
Publication/Patent Number: US10072508B2
Publication date: 2018-09-11
Application number: 14/979,641
Filing date: 2015-12-28
Abstract: The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated with the disk, wherein the bulb includes a slot that opens up radially inwards at its lower face, and in that the rotor includes a retaining part extending partly into the groove projecting radially outwards from the bottom face of the groove, of which a radially outer end of the retaining part fits into the slot of the bulb and bears radially inwards on the inner wall of the slot of the bulb. The invention relates to a turbomachine rotor including a disk and at least one blade wherein the root comprises a bulb accommodated into a groove associated with the disk, wherein the bulb includes a slot that opens up radially inwards at its lower face, and in that the rotor ...more ...less
8
US10077742B2
Publication/Patent Number: US10077742B2
Publication date: 2018-09-18
Application number: 15/034,662
Filing date: 2014-10-24
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. 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 ...more ...less
9
US10115245B2
Publication/Patent Number: US10115245B2
Publication date: 2018-10-30
Application number: 15/028,267
Filing date: 2014-10-01
Abstract: A method and a system for monitoring an aircraft engine (2), including: acquisition and processing part (11) configured to collect a time signal of the exhaust gas temperature residual margin of the aircraft engine (2), acquisition and processing part (11) configured to smooth the time signal thus forming a first curve representing the temperature residual margin, acquisition and processing part (11) configured to identify decreasing pieces in the first curve, acquisition and processing part (11) configured to construct a second curve by concatenation of the decreasing pieces, the second curve being continuous while being restricted to the decreasing pieces of the first curve, acquisition and processing part (11) configured to construct a prediction model from the second curve to determine at least one failure forecast indicator. A method and a system for monitoring an aircraft engine (2), including: acquisition and processing part (11) configured to collect a time signal of the exhaust gas temperature residual margin of the aircraft engine (2), acquisition and processing part (11) configured to smooth ...more ...less
10
US10094740B2
Publication/Patent Number: US10094740B2
Publication date: 2018-10-09
Application number: 14/506,901
Filing date: 2014-10-06
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. 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 ...more ...less
11
US10125630B2
Publication/Patent Number: US10125630B2
Publication date: 2018-11-13
Application number: 14/782,863
Filing date: 2014-03-28
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. 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 ...more ...less
12
US10113480B2
Publication/Patent Number: US10113480B2
Publication date: 2018-10-30
Application number: 14/897,607
Filing date: 2014-06-11
Abstract: The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterized in that it includes a drop-launching extension (32) arranged such as to extend opposite a flared portion (33) of the inner surface (34) of the seal mounting (26), such that when the trunnion (23) is rotated about the shaft of the low-pressure turbine (9), oil (H2), which tends to penetrate between the trunnion (23) and the seal mounting (26), is thrown by centrifugal effect from the drop-launching extension (32) toward the flared portion (33) of the inner surface (34) of the seal mounting (26). The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterized in that it includes a ...more ...less
13
US10151653B2
Publication/Patent Number: US10151653B2
Publication date: 2018-12-11
Application number: 14/843,161
Filing date: 2015-09-02
Abstract: A system for reproducing a dry friction torque applied to an actuator on a valve of a hydraulic line including a disc coupled to a power transmission shaft; a disc brake including a caliper mounted on a frame and plates adapted to be put into contact with the disc; and an electric actuator configured to control the force of application of the plates onto the disc so as to apply a controlled resistive torque to the power transmission shaft, is provided. A system for reproducing a dry friction torque applied to an actuator on a valve of a hydraulic line including a disc coupled to a power transmission shaft; a disc brake including a caliper mounted on a frame and plates adapted to be put into contact with the disc; and an ...more ...less
14
US10150156B2
Publication/Patent Number: US10150156B2
Publication date: 2018-12-11
Application number: 15/127,286
Filing date: 2015-03-09
Abstract: A field of lost pattern casting, and more particularly to a casting tree for lost pattern casting, and also to its method of assembly is provided. The casting tree includes at least one part support, at least one pattern, and at least one first male-female connection connecting the pattern to the part support. The first male-female connection includes an orifice, a peg at least partially inserted inside the orifice, and a film of meltable material interposed at least between an outside surface of the peg and an inside surface of the orifice. A field of lost pattern casting, and more particularly to a casting tree for lost pattern casting, and also to its method of assembly is provided. The casting tree includes at least one part support, at least one pattern, and at least one first male-female connection connecting ...more ...less
15
US10132177B2
Publication/Patent Number: US10132177B2
Publication date: 2018-11-20
Application number: 14/893,332
Filing date: 2014-05-28
Abstract: A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity, before allowing the main portion to close again, closing a nesting between a protrusion at the bottom of the cover and a widening at the bottom of the opening. The disadvantages linked to the use of welding, glue or even assembly parts are as such avoided. A hollow vane, includes a main portion, of which the cavity is closed by a cover, that is produced by expanding the main portion relative to the cover, for example by means of differential thermal expansion, then by placing the cover at the bottom of the opening of the cavity ...more ...less
16
US10139110B2
Publication/Patent Number: US10139110B2
Publication date: 2018-11-27
Application number: 15/259,803
Filing date: 2016-09-08
Abstract: A turbomachine combustion chamber, comprises a fuel injector nozzle and an injection system. The injection system comprises a sliding traverse, means for maintaining the sliding traverse and a supporting sole for the sliding traverse. The injection system comprises means for recalling the sliding traverse configured to stress the supporting sole against axial displacements of the sliding traverse relatively to the means for maintaining. The outer connection surface of the injector nozzle and/or at least one portion of the internal centring surface of the sliding traverse narrow in the downstream direction, in such a way as to retain the injector nozzle relatively to the sliding traverse axially in the downstream direction. A turbomachine combustion chamber, comprises a fuel injector nozzle and an injection system. The injection system comprises a sliding traverse, means for maintaining the sliding traverse and a supporting sole for the sliding traverse. The injection system comprises means for ...more ...less
17
US10138745B2
Publication/Patent Number: US10138745B2
Publication date: 2018-11-27
Application number: 15/034,728
Filing date: 2014-11-12
Inventor: Scholtes, Christophe  
Abstract: A sealing system in a cavity under the stator of a turbomachine flow path, the cavity being located between a root of a vane of the stator and a complementary rotor device, the root including two surfaces each provided with an abradable coating, the rotor device being provided with a first and a second sealing element, arranged facing the first and the second surface respectively, the first surface and the first sealing element forming a first sealing pair and delimiting a first leakage section between them, the second surface and the second sealing element forming a second sealing pair and delimiting a second leakage section between them, one of the two pairs tending towards a minimum leakage section when the other tends towards a maximum leakage section, and vice versa. A sealing system in a cavity under the stator of a turbomachine flow path, the cavity being located between a root of a vane of the stator and a complementary rotor device, the root including two surfaces each provided with an abradable coating, the rotor device being provided ...more ...less
18
US10138754B2
Publication/Patent Number: US10138754B2
Publication date: 2018-11-27
Application number: 15/348,824
Filing date: 2016-11-10
Abstract: The present invention relates to a device for measuring aerodynamic magnitudes (1) intended to be placed transversally in a flow passage (12, 13) of a turbine engine comprising: an upstream body (2) having a profile of general cylindrical shape defining a leading edge (5) a plurality of sensors (4), the instrumentation lines (45) of the sensors being placed in the body (2), the sensitive elements (41) of the sensors extending at the leading edge (5); a downstream fairing (3) mounted on the upstream body (2) and defining a trailing edge (6); the downstream fairing (3) comprising, in the longitudinal direction of the upstream body (2), several sections (35) fixed independently of each other to the body (2), two successive sections (35) being connected by a flexible junction (37). The present invention relates to a device for measuring aerodynamic magnitudes (1) intended to be placed transversally in a flow passage (12, 13) of a turbine engine comprising: an upstream body (2) having a profile of general cylindrical shape defining a ...more ...less
19
US10145305B2
Publication/Patent Number: US10145305B2
Publication date: 2018-12-04
Application number: 14/652,999
Filing date: 2013-12-09
Abstract: A fuel circuit of a turbomachine, this circuit including a fuel return valve connected to the main fuel circuit and to a tank, the valve being able to take a first and a second open position, separate from one another, and a closed position, two primary hydraulic lines connecting the valve to the main circuit and including, respectively, first and second filters through which the fuel passes when the valve is in its first open position, two secondary hydraulic lines which connect the valve to the main circuit and which are positioned in relation to the first and second filters in such a way that the circulation of fuel in these secondary lines contributes, respectively, to the cleaning of the first and second filters, the fuel circulating in the secondary lines when the valve is in its second open position. A fuel circuit of a turbomachine, this circuit including a fuel return valve connected to the main fuel circuit and to a tank, the valve being able to take a first and a second open position, separate from one another, and a closed position, two primary hydraulic lines ...more ...less
20
US10100859B2
Publication/Patent Number: US10100859B2
Publication date: 2018-10-16
Application number: 15/303,924
Filing date: 2015-04-08
Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together. An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of ...more ...less