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Snecma Propulsion Solide
Snecma Moteurs
Snecma Services
Snecma Propulision Solide
Snecma Mexico S a De C v
Snecma A Corporation
Snecma Propulsion Solide_20100107
Snecma Propulsion Solide_20100121
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Snecma patents

Recent patent applications related to Snecma. Snecma is listed as an Agent/Assignee. Note: Snecma may have other listings under different names/spellings. We're not affiliated with Snecma, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "S" | Snecma-related inventors

Capacitive system for correcting the pogo effect with semi-centered discharge tube capable of being positioned in a bend

A pogo effect corrector system for a feed system for feeding a rocket engine with liquid propellant, the corrector system comprising: a feed pipe part for feeding liquid propellant that is configured to be connected both upstream and downstream to a liquid propellant feed pipe of the feed system; and... Snecma

Method of determining probabilistic operability requirements for a system and its component subsystems

A method of operation of a complex system includes obtaining a population of operating points in a multidimensional space having axes, each representative of a parameter of a subsystem of the system that is represented for characterization purposes; followed by constructing a plurality of limit domains in that space, each... Snecma

Compacting and injection mold for a fiber preform for fabricating a turbine engine guide vane made of composite material

A compacting and injection mold for a fiber preform is for use in fabricating a turbine engine guide vane out of composite material. The mold includes a shell forming a trough that is to receive the fiber preform and that is closed in leaktight manner by bottom and top covers,... Snecma

Lever arm device for controlling the pitch of fan blades of a turbine engine having an unducted fan

A device for controlling the pitch of fan blades in a turbine engine having an unducted fan including at least one set of adjustable pitch fan blades, each fan blade being coupled, for pitch adjustment purposes, to a radial control shaft constrained to rotate with the set of fan blades... Snecma

Ignition liquid propellant engine

A method of starting combustion of a space vehicle engine, the method comprising igniting a propellant tank heater (25); once the heater (25) has reached stable conditions, pressurizing a first tank (23) containing the first propellant and a second tank (24) containing a second propellant, and in parallel filling respectively... Snecma

Heat exchanger and turbine engine comprising such an exchanger

The invention relates to a heat exchanger (10) for heat-exchange between a first fluid and a second fluid, comprising a membrane separating the two fluids and a heat-conductive element (17) in thermal contact with the membrane and with the first fluid, characterised in that said heat-conductive element (17) moves between... Snecma

Stator of an aircraft turbine engine

A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the... Snecma

Turbomachine guide vanes with improved vane profile

A set of turbomachine guide vanes including plural vanes arranged around an annulus, each vane having a leading edge extending between root and tip ends, the leading edge offset between these two ends being greater than 10% of the blade height. A tangential stacking of the guide vanes towards the... Snecma

Fiber structure woven as a single piece by 3d weaving, and an application thereof to fabricating a composite material part

In a fiber structure woven as a single piece by three-dimensional weaving, first warp yarns interlink layers of weft yarns in a first portion of the fiber structure adjacent to a non-interlinked zone and also weft yarns of a second portion of the fiber structure beyond the non-interlinked zone, and... Snecma

Guide device for variable pitch stator vanes of a turbine engine, and a assembling such a device

A device for guiding variable pitch stator vanes of a turbine engine is provided. The device includes a plurality of inner ring angular sectors arranged end-to-end in order to form an inner ring, each inner ring sector having chimneys passing radially through the inner ring sector, a plurality of cylindrical... Snecma

Method for suppressing the pogo effect

A field of vehicles propelled by reaction, and more specifically to a method of suppressing the pogo effect in such a vehicle. A feed system for feeding a reaction engine of the vehicle includes a hydraulic accumulator enabling a selection to be made from among a plurality of predetermined operating... Snecma

Propeller blade pivot

The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal... Snecma

Air circulation device for turbomachine

A device for circulation of air for a turbomachine, the device including an inlet provided to receive incident airflow, air circulation ducts connected to the inlet, a central part including side walls, peripheral walls arranged at a distance from the central part, so as to form the air circulation ducts,... Snecma

Method and device for monitoring a parameter of a rocket engine

An obtaining step for obtaining a measurement of the monitored parameter as measured by a sensor and corresponding to an operating point of the engine, the operating point being defined by at least one regulation parameter of the engine; an estimation step for estimating a value of the monitored parameter... Snecma

Fan for a turbomachine

The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream (26) at the radially inner ends of the leading edges of... Snecma

Flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle

said system being characterized in that the computer also includes a plurality of empirical calibration curves that have been determined empirically for defining the flow rate of propellant fluid as a function of the magnitude of heating and as a function of environmental parameters, such that said computer also performs... Snecma

Device for searching for defects on parts by endoscopy

A device for searching for defects on parts that are masked, such as turbine engine blades, the device including a tubular sheath, a light-guide guiding light, an image-transmission mechanism transmitting images housed inside the sheath, an examination head at a distal end of the sheath including an illumination mechanism and... Snecma

Blade for a turbomachine impeller and modelling the same

A method of modeling the blade.... Snecma

Device for mounting a spark plug in a combustion engine of a gas turbine engine

A device for mounting a spark plug in a combustion chamber of a gas turbine engine includes a chimney including a collar extending radially inwards, a washer fastened on an axial end of the chimney so as to project towards the inside of the chimney, and a bushing forming a... Snecma

Propulsion assembly for an aircraft having a turbojet with a non-ducted fan and an attachment pylon

A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined... Snecma

Multilayer woven fibrous structure including a hollow tubular part, production method thereof and composite part comprising same

A fiber structure made as a single piece by multilayer weaving using a method including weaving warp yarns of at least a first set of layers of warp yarns with weft yarns including at least some that are woven with extra length so as to have warp yarn end portions... Snecma

Feed system and a suppressing the pogo effect

A feed system for feeding a rocket engine with a liquid propellant includes a feed circuit, and a device to vary a volume of gas in the feed circuit. The device is configured to cause a volume of gas in the feed circuit to vary while the rocket engine is... Snecma

Blade provided with platforms possessing attachment portions

A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse... Snecma

Variable geometries fluid supply circuit for a turbomachine without volumetric pump

A system for supplying a turbomachine with fluid, the supply system including a low-pressure pumping unit intended to increase the pressure of the fluid flowing toward a downstream circuit. The downstream circuit divides at an inlet node, situated between the low-pressure pumping unit and the high-pressure volumetric pump, into a... Snecma

Aircraft turbine engine with improved mechanical power takeoff

An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel... Snecma

Method for deploying a satellite constellation

controlling (40) the satellites in such a manner as to be moved sequentially in order to reach the same final altitude, said sequential movement being performed in such a manner that the satellites describe final orbits that are angularly offset relative to one another.... Snecma

Gear pump intended, in particular, as a high pressure fuel pump

A geared fuel pump (4′) operates to supply a determined flow but at low or zero pressure rise. It is planned to add gland packing (46) between support bearings (19) of the pinions (11), or between some of them, to provide hydrodynamic lift for these bearings, by delimiting a closed... Snecma

Assembly for aircraft turbine engine and mounting same

An assembly for an aircraft turbine engine, including a rolling bearing bracket defining an inner space on either side thereof; a rotary assembly including a first gear; a housing for drawing mechanical power including a second gear mating with the first gear; a shaft for drawing mechanical power, inserted into... Snecma

Fuel meter protected from icing

A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage... Snecma

Turbomachine turbine blade comprising a cooling circuit with improved homogeneity

The internal cooling of moving blades of turbines in aircraft turbomachines is limited in effectiveness because of inhomogeneities of this cooling on each of the pressure-side and suction-side walls. To address this problem, there is proposed a blade including a circuit for cooling the airfoil part thereof, in which circuit... Snecma

Turbine engine rotor lock

A turbine engine rotor lock, in particular for a turbojet fan, adapted to retain a blade axially relative to a disk of the rotor, the lock including a composite body including a woven fiber structure embedded in a matrix; and a damper pad made of elastomer and fastened to the... Snecma

Riveted assembly and associated production method

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... Snecma

A shaft machining anti-vibration device

An anti-vibration device for the machining of a shaft includes a first fixed ring intended to be kept inside a shaft by a shoulder, the anti-vibration device including: at least one first external groove and at least one first external seal for forming at least one contact with the internal... Snecma

Turbomachine casing comprising a cavity-free shroud and yokes reinforced by stiffeners

The invention relates to a turbomachine casing (1) comprising: a hub (2), an outer shroud (3), and yokes (11) projecting from the outer shroud (3), for attaching the housing (1), characterised in that it comprises at least one stiffener (10) extending between pairs of yokes (11) facing each other, and... Snecma

Method and device for remote endoscopy of an aircraft engine

The device according to the invention further comprises a wireless communication interface allowing the operator to exchange with the expert, in real time and interactively, the images captured and the results of the measurements performed.... Snecma

01/26/17 / #20170021654

Method for marking the surface of a mechanical part with a predefined graphical representation having a holographic effect

A method of marking the surface of a mechanical part with a predefined graphic having a holographic type effect, the method including using a laser source to apply a succession of laser pulses to the outside surface of a part for marking, with different masks being interposed between the laser... Snecma

01/26/17 / #20170022594

Heat treatment of an alloy based on titanium aluminide

The invention relates to a method for the treatment of an alloy based on titanium aluminide. The method comprises the following steps, during which no hot isostatic pressing is carried out: obtaining a semi-finished product (7) produced by centrifugal casting, then heat treating the semi-finished product in order to obtain... Snecma

01/26/17 / #20170022906

Method for isolating a combustible fluid tank from a downstream portion of a turbomachine supply system in case of a fire, and such a supply system

A supply system for supplying fluid to a turbomachine including a fluid tank, a downstream portion located downstream from the tank, and a cutoff valve located between the tank and the downstream portion. The cutoff valve is configured to be at least partially open when a rotational speed of a... Snecma

01/26/17 / #20170023003

Turbomachine component with non-axisymmetric surface

The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2) has a non-axisymmetric surface (S) bounded by a first... Snecma

01/26/17 / #20170023013

A casing made of organic matrix composite material that facilitates the discharge of smoke

A gas turbine casing made of organic matrix composite material includes reinforcement densified by an organic matrix defines an inside volume. On its inside face the casing has a structural part with a first face facing the inside face of the casing, and an opposite second face defining a flow... Snecma

01/26/17 / #20170023251

Combustion chamber comprising additional injection devices opening up directly into corner recirculation zones, turbomachine comprising such a chamber and fuel supply such a chamber

A combustion chamber (18) for aircraft turbomachine, comprising an annular chamber end wall (40), an annular row of injection systems (42) mounted in the annular chamber end wall (40), each injection system comprising at least one air inlet swirler (56, 58) and a main fuel injection nozzle (54) configured to... Snecma

01/19/17 / #20170016346

Device for cleaning a turbomachine module

A device for cleaning, for example degritting or desanding, a turbomachine module comprising: (i) means for isolating bearings of the module, by containment in a closed enclosure; (ii) means for overpressurising said enclosure; (iii) means for stripping material deposited in the walls of annular recesses of the module; and (iv)... Snecma

01/12/17 / #20170009781

Turbomachine component or collection of components and associated turbomachine

The present invention relates to a turbomachine component (1) or collection of components comprising at least a first and a second blade (3I, 3E) and a platform (2) from which the blades (3I, 3E) extend, characterized in that the platform (2), between the pressure face of the first blade (3I)... Snecma

01/05/17 / #20170001366

Method for adhering parts and device for implementing said method

A method is provided of bonding together at least two parts. The method includes assembling together at least two parts and at least one adhesive layer, the adhesive being configured so that its adhesive power increases on heating as a result of it polymerizing, at least one of the parts... Snecma

01/05/17 / #20170002476

Method for manufacturing a part coated with a protective coating

A method of fabricating a part coated with a protective coating, the method including using micro-arc oxidation treatment to form a protective coating on the outside surface of a part, the part including a niobium matrix having metallic silicide inclusions present therein, the current passing through the part being controlled... Snecma

01/05/17 / #20170002689

Device for retaining drained fluids for a propulsive assembly

A device for retaining drained fluids for a propulsive assembly includes a cavity for storing the drained fluids and two walls mounted at the opening of said cavity. The cavity has a fluid storage volume V1 when the device is in a substantially vertical position, and each wall is configured... Snecma

01/05/17 / #20170002747

Aircraft turbomachine comprising a heat exchanger of the precooler type

The invention relates to an aircraft turbomachine comprising a nacelle and an engine comprising at least one outflowing jet of air, wherein a heat exchanger of the precooler type for supplying air to the aircraft is mounted in the nacelle, said exchanger comprising a primary circuit, the inlet of which... Snecma

01/05/17 / #20170003028

Annular combustion chamber in a turbine engine

The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis (52) in supporting means intended for being... Snecma

11/02/17 / #20170312866

Tool for extracting a metal piece

An extracting tool for extracting a metal piece located in an aerodynamic stream of a turbomachine, such as a flow splitter nose, includes a rod; a first stop located at a distal end of the rod and provided with a claw for bearing against a first edge of the metal... Snecma

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009


This listing is an abstract for educational and research purposes is only meant as a recent sample of applications filed, not a comprehensive history. is not affiliated or associated with Snecma in any way and there may be associated servicemarks. This data is also published to the public by the USPTO and available for free on their website. Note that there may be alternative spellings for Snecma with additional patents listed. Browse our Agent directory for other possible listings. Page by