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WO/2014/001696A1 |
The present invention relates to an electrical heating unit (1) for a device for de-icing an air-intake lip of a turbofan nacelle, including at least one current-conducting portion (3) and at least one resistive portion (7). Said unit is...
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WO/2013/177263A1 |
An inlet duct for an engine or multiple engines includes two or more joining duct legs and a pressure relief pathway located at each duct leg to condition inlet airflow from the duct legs. A method of operating an aircraft includes urgin...
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WO/2013/149936A1 |
A Heat exchanger (100, 200, 300) comprises a plurality of heat transfer modules (10, 20, 30, 40) which are disposed side by side so as to define a multilayer body (102, 202, 302) of the heat exchanger (100, 200, 300), wherein each heat t...
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WO/2013/128129A1 |
The invention relates to a flattened nacelle wherein a link of a front frame and secondary flow diversion grids (120) intended to be mounted on an area of a thrust reverser cowling with a reduced transverse section (121) is plotted on a ...
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WO/2013/128093A1 |
The present invention relates to a nacelle (1) of a turbine engine (2) comprising at least one external cowling (3) defining an external aerodynamic surface and at least one internal cowling (4) defining an internal aerodynamic flow surf...
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WO/2013/112331A1 |
An exemplary turbomachine clutch assembly includes a clutch that moves from a first position to a second position in response to rotation of a turbomachine fan at a speed greater than a threshold speed. The clutch permits rotation of the...
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WO/2013/108999A1 |
Disclosed is a blended wing body provided with a canard. The blended wing body provided with the canard, according to the present invention, is the blended wing body provided with the canard in which main wings and a body are integrally ...
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WO/2013/102739A1 |
The fireproof seal is intended for an assembly comprising a turbojet engine pylon and nacelle, in particular an O-duct type. The nacelle comprises a fixed internal nacelle structure (4) and a primary exhaust nozzle (5) for combustion gas...
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WO/2013/100807A1 |
The invention relates to the aircraft industry field, in particular to tactical aviation aircraft providing for the detection and striking of air, above-water and land-based targets. The technical result to which the invention is dire...
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WO/2013/093256A1 |
Actuator (29) for an aircraft turbine engine nacelle with a notably one-piece annular rear part, comprising: - an engine assembly comprising a nut which is capable of rotating but not of translational movement, and means for turning this...
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WO/2013/092279A1 |
The invention relates to a sound insulation device (12) for an engine inlet (28) of an aircraft engine (10) for sound absorption and/or sound propagation modification, having at least one first liner segment (42) and at least one second ...
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WO/2013/088033A1 |
The present invention relates to an air intake structure (2) for a turbojet engine nacelle comprising a substantially annular main structure having an internal wall (12) and an external wall (11) and an air intake lip structure (13) conn...
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WO/2013/088088A1 |
The invention relates to an acoustic protection device (4) for an aircraft turbomachine fan casing, comprising an acoustic protection panel (6) forming a shell ring sector centred on a central axis (2), the device also comprising one or ...
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WO/2013/084308A1 |
The boss for installing an accessory onto an engine fan case comprises multiple stacked layers of reinforcing fibers and a matrix that binds the reinforcing fibers to each other, and is equipped with a seat provided with a bottom surface...
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WO/2013/079100A1 |
An aircraft comprises a turbine engine (104) suspended from a wing (102) by means of a pylon (105). Compressed hot air is bled off from the turbine engine (104). A bleed air duct (209) in the wing (102) conveys the compressed hot air tow...
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WO/2013/068671A1 |
The invention relates to a composite panel (30) including at least one inner skin (3) and one outer skin (2) and having at least one opening (5) for receiving a sampling scoop, which forms a channel and the sampling opening of which is i...
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WO/2013/045783A1 |
The present invention relates to a lip unit for a turbojet engine nacelle provided with at least one electrical deicing system (10) including at least one electric heating element (4), which is electrically powered by means of at least o...
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WO/2013/017680A1 |
The object of the invention is a drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system, characterised in that the electrical energy is provided at least in part ...
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WO/2013/000036A1 |
An air cooling system for an unmanned aerial vehicle including a propeller (14) driven by an engine (12) has at least one cooling air duct (22) to direct cooling air to cool a vehicle component e.g. a cylinder head. The duct has at least...
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WO/2012/164187A1 |
The invention relates to an air inlet structure (100) for a turbojet engine nacelle, comprising: (i) at least one stationary internal wall (41) intended to be attached to at least one element (20) of a mid-section (2) of the nacelle, and...
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WO/2012/160375A1 |
An air vehicle powered by a gas turbine engine, particularly, but not exclusively, an air vehicle having a blended wing body comprises a gas turbine engine disposed in the body of the vehicle including an inlet face. An inlet channel hav...
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WO/2012/148394A1 |
An inlet system for a rotorcraft includes a cowl door assembly and a plenum assembly. The cowl door assembly includes a door member, a cowl inlet opening, and a cowl inlet duct. The plenum assembly is configured to free float in relation...
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WO/2012/148318A1 |
The invention relates to aviation technology and, more specifically, to air inlets for supersonic aircraft propulsion systems. The invention is intended to achieve the technical result of ensuring the stable operation of the engine in al...
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WO/2012/135300A2 |
An aircraft having a cooling system is disclosed. The cooling system can he used to cool a heat emitting component In one form the cooling system is a refrigerant system and includes a relatively high temperature device such as, but not ...
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WO/2012/130418A1 |
An aircraft tail region (10) includes a cooling system (12) installed in the aircraft tail region (10). The cooling system (12) comprises a cooler (14), which forms a section of an outer skin (16) of the aircraft tail region (10), and in...
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WO/2012/131211A1 |
The present invention relates to a method for inspecting impacts (Ii) present on an internal face (104) of a fan casing (100), said method being characterized in that it comprises the following steps consisting in: - spotting (201) a fir...
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WO/2012/120227A1 |
The invention relates to a turbine engine pipe having a longitudinal axis A, which, at the upstream end thereof, includes an outer wall (11) and a core (200), only the upstream portion (210) of which is surrounded by said outer wall (100...
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WO/2012/118516A1 |
Ceramic matrix composite sandwich structures, gas turbine engine components that comprise such sandwich structures, and methods of producing such sandwich structures. The ceramic matrix composite sandwich structure includes a core having...
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WO/2012/110845A1 |
An aircraft (10) with improved aerodynamic performances, adapted to keep the directional stability and a very good aerodynamic behaviour at medium-high incidence. Said aircraft (10) comprises a fuselage (12) to which shaped wings (18, 20...
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WO/2012/104560A1 |
The present invention relates to a method for manufacturing an air-intake structure (1) for a turbojet-engine nacelle including at least two component parts, i.e. at least one air-intake lip structure (2) and at least one outer cowl (3) ...
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WO/2012/098321A2 |
The invention relates to a nacelle for a turbojet engine, including an upstream section forming an air intake lip and defining a space (10) for the circulation of a main air flow (12). The nacelle includes a device (100) for modulating t...
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WO/2012/098322A2 |
The invention relates to a nacelle for a turbojet engine, having a longitudinal axis and a rear section including an annular flow path comprising walls (110) defining a space (3, 10) through which a main air flow (12) passes. The nacelle...
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WO/2012/095592A1 |
The invention relates to a turbofan engine comprising a fan wheel (1) which supports blades (2) and is surrounded by an annular casing (3), the casing (3) including an air suction means (9, 10) in the annular clearance (8) formed between...
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WO/2012/085379A1 |
The invention relates to an inner structure (8) for a nacelle (1) for a aircraft turbofan including a plurality of active (103) and passive (101) movable elements. Each active movable element (103) consists of one or more movable portion...
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WO/2012/077857A1 |
The present invention relates to an airplane equipped with a wing booster. An airplane (1), which includes a fuselage (3) forming the body thereof and a main wing (5) coupled to intersect the central portion of the fuselage, is character...
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WO/2012/072457A1 |
A missile comprises a propulsion system, a passageway for delivering air to the propulsion system and a ducting element associated with the passageway. The ducting element has a ducting surface for ducting air into the passageway, and th...
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WO/2012/066211A1 |
The invention relates to a turbojet engine nacelle comprising a fixed structure comprising a fan casing (4) of said turbojet engine and a front frame (7) designed to be mounted downstream of said fan casing (4) and directly or indirectly...
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WO/2012/066210A2 |
The invention relates to a nacelle (1) for an aircraft bypass turbojet engine comprising, in downstream cross section, an inner fixed structure (8) intended to surround part of the bypass turbojet engine and an outer structure (9) at lea...
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WO/2012/056155A2 |
The invention relates to a leading edge structure (1), in particular for an air inlet of an aircraft nacelle, including a leading edge (2) and an inner partition (3) defining a longitudinal compartment (5) that is located inside said lea...
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WO/2012/056138A1 |
The present invention relates to a turbojet engine nacelle (1) comprising a rear section (4) having an internal structure (9), intended to surround a rear part (5) of an engine compartment and to delimit, with an ejection jet pipe (6), a...
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WO/2012/026846A1 |
The invention relates to multimode aircraft which can be operated at supersonic and subsonic flying speeds in a wide range of flying altitudes. The primary field of use of the invention is multimode super-manoeuvrable aircraft capable of...
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WO/2012/022869A2 |
The present invention relates to an acoustic panel (5) comprising at least one cellular core arranged between at least an internal skin and an external skin (53), characterized in that said external skin incorporates at least one fastene...
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WO/2011/157965A1 |
Aircraft turbo jet engine fan casing, notable in that it is in the form of a box section (6), the radially interior wall (6a) of which is able to form the internal skin of the cold air flow duct (17) of a nacelle in which said turbo jet ...
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WO/2011/157926A1 |
The invention relates to a turbojet engine nacelle, comprising at least one nacelle element (31) having a wall (33) defining a main flow channel (34), said channel (34) having a variable cross-sectional flow area, wherein the cross-secti...
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WO/2011/157953A1 |
The invention relates to an air inlet duct (11) for a turbojet nacelle, comprising an upstream annular lip (13) and a downstream outer annular structure (14Ex). The invention is characterised in that the upstream annular lip (13) and the...
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WO/2011/144836A2 |
The nacelle (1) comprises a stationary shroud (9) and an intake lip (8) that can move axially in relation to the shroud (9) between a rear operating position and a front maintenance position. The aerodynamic element (15) is flexible and ...
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WO/2011/141890A1 |
The present invention relates to an arrangement (or structure) (1) for passenger (2) on a means of transportation, in particular an aircraft. It comprises a seat (3) with a variable arrangement, and a shelf (5), and offers to the passeng...
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WO/2011/135216A1 |
The present invention relates to a thrust reverser (1) having doors, which thrust reverser includes at least one stationary structure (3) on which at least one door (7) is mounted so it can pivot between a closed position in which said d...
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WO/2011/131651A1 |
The invention relates to an exhaust gas diffuser 10 for a gas turbine, comprising a flow duct 22 which expands toward the diffuser outlet 20 and at the center of which an axially extending conducting body 14 is provided. In order to prov...
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WO/2011/117521A1 |
The invention relates to a turboshaft engine supporting pylon covered with a porous material and to a turboshaft engine/pylon assembly. More specifically, the invention relates to a pylon (2) supporting a turboshaft engine (1) on an airc...
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