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Safran Helicopter Engines patents


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

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


Assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines

An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.. . ... Safran Helicopter Engines

Turbine engine rapid reactivation method and system

The system for rapidly reactivating a turbine engine of an aircraft includes an electrical machine that is dc powered from an on-board electrical power supply network. The system also includes a switch interposed between the on-board network and the electrical machine, an additional set including a plurality n electrical energy storage elements, and a control unit for controlling a device for discharging the storage elements and adapted to enable a series circuit including at least some of the n electrical energy storage elements to be connected in parallel with the on-board network so that when the rapid reactivation system is in operation the electrical machine is powered by a voltage level higher than the voltage level of its nominal characteristics.. ... Safran Helicopter Engines

Turbine engine cvc combustion chamber module comprising a pre-combustion chamber

A turbine engine combustion chamber module including at least one constant-volume combustion chamber. The module includes, upstream of the at least one constant-volume combustion chamber, a precombustion chamber capable of producing hot combustion gases that supply the at least one constant-volume combustion chamber so as to allow the ignition thereof.. ... Safran Helicopter Engines

Deformation measuring torque meter

A torque meter includes a casing and a part is configured to move in the casing in translation in a longitudinal direction under the effect of an axial thrust representative of the torque to be measured. The torque meter further includes a bearing surface connected to the casing via at least one of the ends thereof. ... Safran Helicopter Engines

Flow limiter

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 being generally tubular, and the pipe having a bottom which has a regular curve so that the pipe does not have one or more areas that retain the fluid circulating in the pipe.. . ... Safran Helicopter Engines

Turboshaft engine mountable in a reduction gearbox

A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. ... Safran Helicopter Engines

Combustion chamber of a turbine engine comprising a through-part with an opening

A combustion chamber of a turbine engine, including at least one wall defining the combustion chamber and including an aperture for enabling a through-part to pass therethrough. The through-part includes, in the portion thereof located within the combustion chamber, at least one opening able to create an air film to cool the area downstream of the through-part.. ... Safran Helicopter Engines

Constant-volume combustion system for a turbine engine of an aircraft engine

A constant-volume combustion system is for a turbine engine. The system includes a plurality of combustion chambers regularly distributed around a longitudinal axis; a toroidal manifold including a radially oriented outlet for supplying compressed air, from a compressor, to each combustion chamber; a toroidal exhaust pipe including a radially oriented inlet for collecting the combustion gases from the combustion chambers, the combustion chambers being radially positioned between the outlet of the manifold and the inlet of the exhaust pipe; and a timing device for each chamber for drawing in compressed air from the outlet of the manifold and ejecting combustion gas towards the exhaust pipe.. ... Safran Helicopter Engines

Turbine engine wheel

The invention relates to a wheel of a turbine engine comprising a plurality of radially extending vanes, one radially internal or external end of which is connected to an annular platform carrying annular lips (42, 44) extending from said platform in a direction opposite the vane in order to sealingly cooperate with a radially facing abradable material (28). According to the invention, the wheel comprises at least one lip (42, 44) having a concave curved upstream face and a convex curved downstream face or having a convex curved upstream face and a concave curved downstream face.. ... Safran Helicopter Engines

Turbine engine wheel

The invention relates to a turbine wheel (34) comprising a plurality of vanes connected to an annular platform (24) carrying annular lips (36, 38). According to the invention, one of the upstream lip (38) and the downstream lip (36) is of a first type or of a second type, with the first type corresponding to one lip (36) having the upstream face (36a) which is concave curved and the downstream face (36b) which is convex curved and the second type corresponding to a lip (38) having the upstream (38a) and downstream (38b) faces which are substantially flat and mutually parallel.. ... Safran Helicopter Engines

Turbine engine combustion assembly

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 flame tube (21) and configured such as to spray fuel into the flame tube by centrifugation; and at least one injector (35), capable of depositing a film of fuel on said injection wheel (41), said combustion assembly being characterised in that said injector (35) is arranged so as to pass through said upstream area of the front wall (23) or the rear wall (24) of the flame tube (21), so that the injection opening thereof (37) opens into said tube (21), opposite the portion (43) of said injection wheel (41) which is located inside said flame tube (21).. . ... Safran Helicopter Engines

Air supply plenum

An air supply plenum for an engine, the plenum being disposed upstream of an air intake of the engine, the air intake being provided in a casing of the engine. The air supply plenum includes a first lateral wall and a second lateral wall which together form a conduit in which an air flow flows as the engine functions. ... Safran Helicopter Engines

Twist-breakable mechanical fuse and cooling unit of a turbine engine fitted with such a fuse

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 the 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 said drive unit (8, 9) and receiver unit (10). The invention is characterized in that said body (13) comprises a plurality of longitudinal bars (14), each bar (14) being deformable by bending, such as to form a twist-breakable mechanical fuse.. ... Safran Helicopter Engines

Device and method for controlling an auxiliary engine suitable for supplying thrust power to the rotor of a helicopter

The invention relates to a device for controlling an auxiliary engine (8) comprising a gas generator and a free turbine suitable for being able to be connected mechanically to the rotor (12) of a helicopter in order to supply it with thrust power, characterised in that said control device comprises a proportional-integral controller (30) having a proportional gain (kp) and an integral gain (ki), which are dependent on the rotation speed of said gas generator, said controller (30) being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (sc) for correcting the drive speed of said gas generator obtained by adding a signal proportional to said error signal in accordance with said proportional gain (kp), and an integrated signal (si) resulting from the addition of a signal proportional to said error signal in accordance with said integral gain (ki) and a memory signal (sm), supplied by a feedback loop (31) of said integrated signal (si), said memory signal (sm) being dependent on a measurement representing the rotation speed of said free turbine.. . ... Safran Helicopter Engines

11/09/17 / #20170321601

Propulsion unit with selective coupling means

A propulsion unit, notably for an aircraft, including a turbomachine; a propeller that can be selectively coupled to the turbomachine; a rotary electrical machine able to drive at least the turbomachine, and selective coupling of the rotary electric machine to the propeller and/or the turbomachine that is able to couple only the propeller to the rotary electrical machine during a defined stage of operation of the propulsion unit and that is able to couple or not couple the rotary electric machine to a gas generator and/or a free turbine of the turbomachine.. . ... Safran Helicopter Engines

10/12/17 / #20170292491

Ignition system for a combustion chamber of a turboshaft engine

A system for igniting a combustion chamber of a turboshaft engine, comprising: a plurality of start-up injectors which are suitable for injecting fuel into said chamber during a combustion-initiating phase; a circuit for supplying fuel to said start-up injectors, comprising a first sub-circuit, referred to as the primary start-up circuit, designed to supply fuel to some of said plurality of start-up injectors; a second sub-circuit, referred to as the secondary start-up circuit, designed to supply fuel to the other start-up injectors of said plurality.. . ... Safran Helicopter Engines

09/28/17 / #20170277152

Two-way architecture with redundant ccdl's

The present invention concerns a flight control system of an aircraft comprising: —a first processing unit (1), —a second processing unit (2), —communication means configured to establish a first two-way digital link (3) and a second two-way digital link (4) between the first processing unit (1) and the second processing unit (2), said second link (4) being redundant with the first link (3), and said first link (3) and second link (4) being likely to be active concomitantly, said system further comprising backup communication means enabling data exchanges between the first processing unit (1) and the second processing unit (2) in the case of a failure in the first link (3) and second link (4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14).. . ... Safran Helicopter Engines

09/28/17 / #20170277151

Two-way architecture

The present invention concerns a method for switching, by a local processing unit (1,2) of a flight control system of an aircraft, configured to control at least one local actuator, connected to at least one local sensor and connected via at least one link (3,4) to an opposite processing unit (2,1) configured to control at least one opposite actuator and be connected to at least one opposite sensor, said local processing unit (1,2) being further configured to be connected to backup communication means (13,14) enabling data exchanges between the local processing unit (1,2) and the opposite processing unit (2,1) in the case of failures of the links connecting same (3,4), said backup communication means comprising an array of sensors or actuators (13) and/or a secure onboard network for the avionics (14), comprising steps of: •—sending, to the opposite processing unit (2,1), acquisition data relative to the at least one local sensor and actuator data relative to the at least one local actuator, •—receiving, from the opposite processing unit (2,1), acquisition data relative to the at least one opposite sensor and actuator data relative to the at least one opposite actuator, •—receiving an item of opposite health data and determining an item of local health data, •—switching said local processing unit (1,2) from a first state to a second state chosen from an active state (15), a passive state (16) and a slave state (18), depending on the opposite health data received and the local health data determined.. . ... Safran Helicopter Engines

09/14/17 / #20170261390

Hydraulic torquemeter

A hydraulic torquemeter comprising a rod which is translatable in a longitudinal direction under the effect of axial thrust which is representative of the torque to be measured, and a hydraulic circuit in which a fluid flows. It also comprises a manometric capsule comprising a pressure chamber which is supplied with fluid by said hydraulic circuit, a sealed flexible membrane which is in contact with the fluid in the pressure chamber, extends in a plane which is substantially perpendicular to said rod, and is rigidly connected to one end of the rod in such a way that a longitudinal movement of the rod deforms the membrane, a drain port for the fluid in said pressure chamber, and a valve designed to adjust the pressure of the fluid in said pressure chamber according to the deformation of said membrane.. ... Safran Helicopter Engines

08/31/17 / #20170247114

Hybrid propulsion system for a multi-engine aircraft

The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. ... Safran Helicopter Engines

08/24/17 / #20170241347

Removable pack for reactivating a turboshaft engine, architecture for a multi-engine system for propelling a helicopter, provided with such a pack, and corresponding helicopter

The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine (6) being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.. . ... Safran Helicopter Engines

08/03/17 / #20170218847

Device and method for testing the integrity of a helicopter turbine engine rapid restart system

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter includes a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurised air from the turboshaft engine; a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas the device further includes a sensor for determining the rotational speed of the pneumatic turbine.. ... Safran Helicopter Engines

07/27/17 / #20170211483

Pneumatic device for rapidly reactivating a turbine engine, architecture for a propulsion system of a multi-engine helicopter provided with such a device, and corresponding helicopter

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (6), characterised in that it comprises a pneumatic turbine (7) mechanically connected to said turbine engine (6) so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage (9) connected to said pneumatic turbine (7) by means of a pneumatic circuit (10) for supplying pressurised gas to said pneumatic turbine (7); a controlled fast-opening pneumatic valve (11) arranged on the pneumatic circuit (10) between said storage (9) and said pneumatic turbine (7) and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (7), or in a closed position in which said pneumatic turbine (7) is no longer supplied with pressurised gas.. . ... Safran Helicopter Engines

07/27/17 / #20170211413

Overspeed protection device of an aircraft engine

The invention relates to an overspeed protection device of an aircraft engine. . ... Safran Helicopter Engines

07/13/17 / #20170198915

Assembly for turbomachine combustion chamber comprising a boss and an annular element

An assembly for a turbomachine combustion chamber, including a boss for turbomachine combustion chamber, including a tubular body configured to be inserted in a receiving orifice formed in an annular wall of a flame tube and to accommodate a shank of a connecting pin for connecting the flame tube to an external casing, a first end of the boss including an annular flange configured to prevent radial translational movement of the boss in a first direction, and a second end of the boss being configured to be crimped to the wall of the flame tube so as to prevent radial translational movement of the boss in a second direction, and an annular element configured to fit coaxially with the receiving orifice and in radial contact with the annular wall of the flame tube on the one hand and with the annular flange of the boss on the other.. . ... Safran Helicopter Engines

06/22/17 / #20170175643

System for the emergency starting of a turomachine

. . The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum (2) rigidly connected to a rotary shaft (3), the axes of symmetry (ll) of the drum (2) and of the shaft being coincident, the flyer further comprising at least one exhaust nozzle (4) for ejecting gas, which is positioned on the periphery of the drum (2) and oriented substantially tangentially to the rotation about said axis (ll), and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle (4), said emergency start system further comprising a support in which the shaft of the flyer rotates, and a volute for recovering the gases, which radially surrounds the flyer and is rigidly connected to said support.. . ... Safran Helicopter Engines

05/11/17 / #20170131687

Method of optimized global management of an energy network of an aircraft and corresponding device

. . The invention relates to a method and to a device for optimised global management of a power network of an aircraft comprising a plurality of items of power equipment, characterised in that it comprises a module 40 for selecting at least one optimisation objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimisation objective (19).. . ... Safran Helicopter Engines

05/04/17 / #20170122221

Turboshaft engine, twin-engine helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a twin-engine helicopter

The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator (5), characterised in that it comprises a device (20) for spontaneously mechanically coupling said gas generator (5) and said free turbine (6) that is capable of mechanically and spontaneously connecting said gas generator (5) and said free turbine (6) as soon as the ratio of the rotational speed (ngg) of said gas generator to the rotational speed (ntl) of said free turbine reaches a predetermined threshold value.. . ... Safran Helicopter Engines

04/27/17 / #20170114659

Turbine engine compressor with variable-pitch blades

A turbine engine compressor has at least one annular row of variable-pitch stator vanes that are substantially radial and have pivots at their radial ends. The radially outer pivots of the vanes are received in first openings in a stator casing and the radially inner pivots are received in second openings in a floating ring that surrounds a rotor of the compressor. ... Safran Helicopter Engines

04/13/17 / #20170101938

Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device

The invention relates to a method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (4), of a twin-engine helicopter, and for controlling a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device which define a maximum power regime, characterised in that it comprises: a step (10) of detecting an indication of failure of said inoperative engine (4); a step (11) of modifying said protective stops of said healthy engine (5) into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure; a step (12) of confirming a failure of said inoperative engine (4); a step (13) of controlling an increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure.. . ... Safran Helicopter Engines

04/13/17 / #20170101936

Turboshaft engine comprising a controlled mechanical coupling device, helicopter equipped with such a turboshaft engine, and method for optimising the zero-power super-idle speed of such a helicopter

The invention relates to a turboshaft engine comprising a gas generator (5) that is capable of being rotated, and a free turbine (6) that is rotated by the gases of said gas generator, characterised in that it comprises a device (40) for controlled mechanical coupling of said gas generator (5) and said free turbine (6) that is capable of connecting said gas generator (5) and said free turbine (6) mechanically and on demand as soon as the rotational speed of said gas generator (5) reaches a predetermined threshold speed.. . ... Safran Helicopter Engines

04/06/17 / #20170096946

Improved fuel injection architecture

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 at least both injection manifolds (30a, 30b); and a distribution proportioning device (31), located between the main fuel-proportioning device (32) and the injection manifolds (30a, 30b) and suitable for distributing at least part of the total fuel flow between both manifolds. The architecture is characterized in that it also includes a bypass valve (35) suitable for discharging a flow from a first manifold (30a, 30b) to a second manifold (30b, 30a), in the event of excess fuel pressure in the first manifold. ... Safran Helicopter Engines

04/06/17 / #20170096233

Architecture of a multi-engine helicopter propulsion system and corresponding helicopter

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low dc voltage onboard network (7) for supplying helicopter equipment during flight, characterised in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).. . ... Safran Helicopter Engines

03/16/17 / #20170074120

Device for positioning an inspection tool

The present disclosure relates to a device (30) for positioning an inspection tool (130) relative to a flange (10) of a casing (1). The device (30) comprises first and second positioning parts (40, 70) that are assembled together. ... Safran Helicopter Engines

03/09/17 / #20170067640

Annular turbomachine combustion chamber

An annular combustion chamber (10) for a turbomachine (100), the combustion chamber presenting an axial direction (x), a radial direction, and an azimuth direction, and comprising a first annular wall (12) and a second annular wall (14), each wall delimiting at least a portion of the volume of the annular combustion chamber (10), the first and second walls (12, 14) presenting complementary fitting elements (12d, 14d), the first wall (12) presenting at least one first through hole (12f), while the second wall (14) presents at least one second through hole (14f), the combustion chamber (10) also having at least one pin (18) engaged in a pair of holes comprising a first hole (12f) and a second hole (14f), said pin (18) locking the fitting of the first and second walls (12, 14).. . ... Safran Helicopter Engines

01/19/17 / #20170016399

Method for assisting a turboshaft engine in standby of a multiple-engine helicopter, and architecture of a propulsion system of a helicopter comprising at least one turboshaft engine that can be in standby

The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (5, 6), characterised in that it comprises: at least one hybrid turboshaft engine (5) that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines (6) operating alone during this stable flight; an air turbine (30) that is mechanically connected to the gas generator (17) of the hybrid turboshaft engine (5) and is suitable for rotating said gas generator (17); means for withdrawing pressurised air from the gas generator (27) of a running turboshaft engine (6); and a duct (31) for routing this withdrawn air to said air turbine (30).. . ... Safran Helicopter Engines

01/19/17 / #20170016398

Hydraulic device for emergency starting a turbine engine, propulsion system of a multi-engine helicopter provided with one such device, and corresponding helicopter

Emergency start-up device for a turboshaft engine of a helicopter, comprising: a hydraulic motor which is mechanically connected to said turboshaft engine; a hydropneumatic store which is connected to said hydraulic motor by a hydraulic circuit for supplying pressurised liquid to said hydraulic motor; and a hydraulic valve which has controlled quick opening, arranged on the hydraulic circuit between said store and said hydraulic motor, and is suitable for being placed on command at least in an open position in which the liquid can supply said hydraulic motor, or in a closed position in which said hydraulic motor is no longer supplied with pressurised liquid.. . ... Safran Helicopter Engines

01/19/17 / #20170015411

Drive chain for a helicopter incorporating a pyrotechnic assistance drive module and helicopter comprising the same

The invention relates to a drive chain for driving the rotor(s) (21, 22) of a helicopter, comprising a main transmission gearbox (24) capable of driving the rotor(s) (21, 22) when said gearbox is moving, a main engine (23) for providing the power for the flight, and at least one assistance drive module (31), the main engine (23) and the assistance drive module (31) being mechanically connected to said main transmission gearbox (24) so as to induce the movement of said gearbox. The drive chain is characterised in that the assistance drive module comprises a pyrotechnic device for generating a torque on a power transmission shaft that is mechanically connected to the main transmission gearbox (24). ... Safran Helicopter Engines








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