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WO/2017/103389A1 |
The invention relates to a hydraulic control system for a thrust reverser of an aircraft turbofan nacelle, comprising devices for actuating and controlling the reverser, including hydraulic locks and cylinders, the corresponding hydrauli...
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WO/2017/093710A1 |
Noise attenuating devices and methods, precursors and abrasive blasting masks for manufacturing noise attenuating devices are disclosed. An exemplary method disclosed herein comprises bonding a facing sheet (12) of the noise attenuating ...
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WO/2017/089730A1 |
The invention relates to a turbomachine (24) of "open rotor" or turboprop type, comprising a nacelle (26) defining an air inlet (28), a central hub (30) and an annular air intake duct (32) surrounding the central hub (30) and opening int...
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WO/2017/078805A1 |
An aircraft engine guard, for protecting an aircraft engine against ingestion of large objects, includes a generally cone-shaped body, a base section of the rear end of the guard body and a dome section at the distal forward end of the g...
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WO/2017/024391A1 |
An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine...
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WO/2017/024392A1 |
An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulat...
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WO/2017/024389A1 |
An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having...
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WO/2017/024390A1 |
An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid ...
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WO/2017/024394A1 |
An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fa...
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WO/2017/017368A1 |
The invention relates to a porous body (9) made from a ceramic-matrix composite material and intended for an acoustic attenuation panel, comprising: a plurality of interwoven ceramic fibres (13), a metal oxide matrix (15), and a pluralit...
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WO/2017/013363A1 |
The present invention relates to an aircraft comprising a fuselage (1) and a thruster downstream of the fuselage. The thruster includes a power turbine (7), located inside a main flow jet, and at least one fan (9), located inside a secon...
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WO/2017/013077A1 |
The invention relates to a drive device for an aircraft, comprising a shaft turbine coupled to an impeller by means of a shaft. The impeller comprises a suction side and a thrust side. The shaft turbine is arranged in the region of the s...
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WO/2016/205932A1 |
An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant there...
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WO/2016/201568A1 |
A compound cycle engine having an output shaft; at least two rotary units each defining an internal combustion engine, a first stage turbine, and a turbocharger is discussed. The first stage turbine includes a rotor in driving engagement...
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WO/2016/203015A1 |
The present invention belongs to the field of aeronautics and relates to an aeroplane with reduced installation noise, and specifically to an aeroplane wing and jet engine system including an aeroplane wing and at least one jet engine wi...
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WO/2016/193623A1 |
The invention relates to an aircraft turbine engine nacelle thrust reverser including: at least one translatable thrust reverser cowl, an output nozzle of variable cross-section, an actuator suitable for moving the variable nozzle and th...
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WO/2016/190753A1 |
A shroud for an aircraft having a noise reducing material on or in an inner surface of the shroud adjacent to one or more tips of the propeller. The noise reducing material is preferably an electrospun nanomaterial, particularly a ridged...
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WO/2016/168261A1 |
Devices for producing vacuum using the Venturi effect and systems, such as internal combustion engine systems, including the same are disclosed. The devices include a housing defining a suction chamber, a motive passageway converging tow...
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WO/2016/131150A1 |
An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake co...
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WO/2016/131151A1 |
A compound engine assembly including an air conduit having an inlet in fluid communication with ambient air around the compound engine assembly, a compressor having an inlet in fluid communication with the air conduit, an engine core inc...
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WO/2016/131144A1 |
An engine assembly including an engine core with at least one internal combustion engine, a first casing, a turbine module including a second casing located outside of the first casing, and a compressor module including a third casing lo...
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WO/2016/133501A1 |
An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a perforated sheet that includes a set of perforations with corresponding inlets, the perfor...
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WO/2016/116699A1 |
The invention relates to a method for producing an ablative resin, by carrying out a reduction reaction for the reduction of a compound of formula A, followed by a polymerisation reaction.
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WO/2016/116709A1 |
The invention relates to an aircraft turbojet engine nacelle, the nacelle (1) comprising a rear section (4) with no lower fork, the rear section comprising a thrust reversal system, the thrust reversal system comprising a mobile cowl (20...
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WO/2016/116697A1 |
The invention relates to a method for producing an ablative resin, comprising a step of pre-polymerisation wherein an innovative aldehyde compound is used.
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WO/2016/102691A2 |
The subject of the invention is a device for attenuating sound waves forming the wall of a duct, the sound waves spreading in a stream of air passing along the duct. The device comprises a structure (13) constituting a noise attenuator, ...
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WO/2016/095070A1 |
A protective apparatus for an aircraft engine, formed of three blades (5) made of carbon fibre material, a 120° angle being formed between the three blades (5), a caster being disposed at the tail end of each blade (5), said caster bein...
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WO/2016/087776A1 |
The invention relates to an air supply plenum (12) for an engine, the plenum being disposed upstream of an air intake (2) of said engine, the air intake being provided in a casing (3) of said engine. The air supply plenum (12) comprises ...
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WO/2016/083743A1 |
The invention relates to an arrangement, in a pod of an aircraft propulsion assembly, for drawing in air and trapping foreign bodies. Said arrangement includes a main air inlet duct (11) separating into, on one hand, a channel (13) for l...
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WO/2016/070480A1 |
An air-entraining port cover. The air-entraining port cover is arranged at an air-entraining port of an airplane body (30) and comprises a fixing frame (10) and an air filtering member (20). An annular groove (11) is formed in an inner s...
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WO/2016/066009A1 |
A rotorcraft (1000). The rotorcraft (1000) comprises: a fuselage (100); a craft arm (200), where one extremity (201) of the craft arm (200) is connected onto the fuselage (100); rotor blades (300), where the rotor blades (300) are connec...
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WO/2016/062945A1 |
The hybrid propulsion system for a multi-engine aircraft comprises a plurality of free turbine turbomachines each one equipped with a gas generator, these including at least one first turbomachine (1) or hybrid turbomachine able to opera...
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WO/2016/042271A1 |
The invention relates to a device (36) for attaching a downstream end of an air inlet onto a fan casing (30) of an aircraft turbojet nacelle. The air inlet comprises an acoustic ferrule (28) that is radially defined by an inner skin (32)...
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WO/2016/027187A1 |
An outlet door is provided for covering an outlet defining an outlet area in a skin (24) of an aircraft component to exhaust a flow of heated air to an outside of the aircraft. The outlet door includes a body defining a door area and ext...
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WO/2016/025029A1 |
A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to me...
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WO/2016/020623A1 |
The invention concerns a method for producing a honeycomb core panel (10) suitable for producing a sound absorbing panel of an aircraft nacelle, the panel comprising a honeycomb core (12) delimited by a first face (16) and an opposing se...
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WO/2016/005711A1 |
The invention relates to a front lip of a turbofan engine nacelle, defined at the rear by a partition wall (6), the lip comprising an annular de-icing space (4) comprising a tube for supplying hot air (40) in order to de-ice the outer wa...
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WO/2016/000484A1 |
A fuselage opening and closing system of an unmanned helicopter. The unmanned helicopter comprises a fuselage, a motor, rotor blades and a tail pipe; one end of both the motor and the tail pipe is installed in the fuselage; the fuselage ...
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WO/2016/000486A1 |
A tail gas balance system of an unmanned helicopter. The unmanned helicopter comprises a fuselage, an engine, a rotor wing, a parachute device and a tail pipe. The parachute device is mounted on the rotor wing head of the rotor wing. A c...
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WO/2015/200468A1 |
A cooling air bypass is disclosed which prevents premature failure of an engine in the event the cooling air from an external blower is somehow obstructed or shut off.
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WO/2015/183715A1 |
An exhaust system for a rotary wing aircraft includes a diffuser located at an airframe of the rotary wing aircraft and operably connected to an engine of the rotary wing aircraft, and a chimney extending upwardly from a diffuser wall. A...
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WO/2015/177454A1 |
The present invention concerns a method for starting a test testing the operation of at least one fan designed to cool at least one computer of an aircraft turbojet engine, said method comprising steps of: - comparing (E1) the number of ...
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WO/2015/166430A1 |
Aircraft (10) of the type comprising: - a fuselage (11); - a main wing (12), a front tab (13) and a horizontal tail plane (15) so as to make three lifting surfaces; - two turboprop units (34) mounted on the main wing (12) on opposite par...
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WO/2015/160679A1 |
An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The...
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WO/2015/151621A1 |
This jet engine is provided with an inlet that takes in air, a combustor (12) that combusts a fuel using air, and a fuel control unit (37) that controls the supply of fuel. The combustor (12) is provided with a fuel supply unit (22) that...
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WO/2015/145081A1 |
The invention relates to an acoustic sandwich panel comprising a plurality of alveolar units (2) joined by means of an intumescent adhesive (3) arranged between the edges of the alveolar units (2) to be joined, thereby forming at least o...
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WO/2015/136210A1 |
The invention relates to a nacelle (11) for a propulsion unit, comprising: - at least one scoop (2) opening to the external air, and - a canal (3) supplying external air from the scoop (2) to two ducts (13, 14) which separate downstream ...
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WO/2015/136276A1 |
A heat exchanger (2) comprising a duct (4) through which a first fluid (e.g. a coolant such as ram air) may flow, and one or more vanes (18) disposed within the duct (4) and configured to disrupt the flow of the first fluid through the d...
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WO/2015/112554A1 |
A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The ...
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WO/2015/104494A1 |
The invention relates to a structure (100) for the suspension of a turboprop engine (10) having two unducted propellers on a structural element of an aircraft, comprising a suspension frame (102) which is to be fastened to a structural e...
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