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WO/2009/081020A1 |
The invention relates to an acoustic processing structure provided at a leading edge on which flows an aerodynamic stream, in particular at the air inlet of an aircraft nacelle, wherein said acoustic processing structure includes, from t...
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WO/2009/080904A1 |
The present invention relates to a turbojet engine nacelle (1) comprising: - an air intake structure (4) capable of channelling an airflow towards a fan of the turbojet engine and comprising at least one longitudinal external panel (40) ...
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WO/2009/080168A1 |
The invention relates to an aircraft cooling system (10) comprising a cooling element (12) that comprises a housing (14), a cooling air inlet (18) that is embodied in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38) t...
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WO/2009/077690A2 |
The invention relates to an aircraft nacelle that comprises a duct (32), a peripheral wall (34), a front lip (36) connecting said duct (32) and said peripheral wall (34) and defining an air inlet, as well as an ice treatment system for t...
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WO/2009/077666A2 |
The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing means includes an anti-ice coating (13) cover...
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WO/2009/077689A2 |
The invention relates to an aircraft leading edge including, as an extension, an aerodynamic surface at which flows an aerodynamic flow and where are provided air outlets (30) for preventing the separation of said aerodynamic flow, the a...
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WO/2009/077688A2 |
The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which...
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WO/2009/060137A2 |
The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to...
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WO/2009/048713A1 |
A heat shield (2) includes a ceramic composite heat shield panel (3) having a generally concave first surface and a generally convex second surface and a pair of thickened panel edge portions (9) provided in the heat shield panel. A heat...
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WO/2009/047399A1 |
The invention relates to a nacelle for a turbojet engine, comprising a rear section forming an outer structure which defines, together with a concentric inner structure (4) comprising an inner panel (10) for surrounding a downstream part...
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WO/2009/027591A1 |
The present invention relates to a jet engine nacelle comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and an aft section equipped with at least one thrust reversal system comprising, on the on...
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WO/2009/024660A1 |
The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated...
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WO/2009/024461A1 |
The present invention relates to a jet engine nacelle (1), of the type comprising an aft section forming an external structure (2) which, together with a concentric internal structure (4) comprising an internal panel (10) intended to sur...
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WO/2009/024662A2 |
The present invention relates to a turbofan jet engine nacelle intended to be attached to a structure of an aircraft by an engine strut and comprising a forward air inlet section, a mid-section intended to surround a jet engine fan, and ...
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WO/2009/007564A2 |
The invention relates to a turbojet engine for an aircraft that comprises an engine provided in a nacelle and at least one heat exchanger (13) for cooling down a hot fluid collected in the propulsion system of the turbojet engine before ...
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WO/2009/001002A1 |
The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at lea...
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WO/2008/152259A2 |
The invention relates to an acoustic panel comprising a reflecting layer, at least one cellular structure and an acoustically resistive structure forming an aerodynamic surface of an aircraft at the surface of which at least one acoustic...
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WO/2008/145725A1 |
The invention relates to a propulsion assembly (1) for an aircraft including a turbojet engine (2), a turbojet fixation mast (4) and a nacelle (3) mounted on the fixation mast and surrounding the turbojet engine. According to the inventi...
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WO/2008/142242A2 |
The invention relates to a nacelle rear assembly for a turbojet engine, that comprises: a hood, an inner structure in the shape of a sheath in which at least the rear portion (15) is of the O-duct type and is capable of axial sliding bet...
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WO/2008/142289A2 |
The arrangement of the invention includes mobile means for blocking an air passage channel (10) which are controlled by an aerodynamic surface (20) provided in said air passage channel (10) and capable of generating a lift force (P) unde...
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WO/2008/132321A1 |
The invention relates to a guiding device (100) for part of a jet engine nacelle that can move in translation, comprising: (i) a rail (101) fixedly mounted on part of the nacelle, and (ii) a slide (102) which is connected to the mobile p...
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WO/2008/115273A2 |
A tandem inlet apparatus (10) for use with a high speed mobile platform, for example a commercial or military aircraft. The tandem inlet apparatus includes a Pitot inlet (102) for feeding air to a cabin air compressor (CAC) of an air con...
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WO/2008/102079A2 |
The invention relates to a nacelle, for an aircraft jet engine (10) having a high bypass ratio, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle (12) including a wall (24) concentrically and at least partially...
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WO/2008/097325A2 |
An airfoil for use with an aircraft having an engine (3) positioned such that exhaust from the engine flows under an underside of the airfoil. The airfoil includes an upper surface and a movable control element (14, 16). The upper surfac...
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WO/2008/093447A1 |
A low noise air craft which can reduce engine noise on the ground sharply at the time of take-off and landing by utilizing a well-known mechanism. By utilizing a thrust deflection means constituted of a well-known mechanism for making th...
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WO/2008/076471A2 |
An inlet barrier filter system for an aircraft engine includes a filter panel (35) including filter media for filtering air prior to intake (15) into the engine. The filter panel has a forward edge (F). The system further includes an act...
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WO/2008/059168A2 |
The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least o...
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WO/2008/059169A2 |
The subject of the invention is an aircraft leading edge such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, comprising a covering (26) for acoustic treatment comprising, from the outside inwards, an acoustic...
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WO/2008/059167A2 |
Process and installation for anaerobic treatment of material having a high solids concentration. The invention relates to a process for anaerobic treatment of material having a solids concentration greater than 15% in a digester in the f...
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WO/2008/054500A2 |
Integrated engine exhaust systems and methods for reducing drag and thermal loads are disclosed. In one embodiment, a propulsion system includes an engine installation 120 configured to be mounted on a wing assembly 104 of an aircraft. T...
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WO/2008/047357A2 |
The present invention is about an automatic temperature regulating device for turning on and off a flow of cooling gas through a conduit. The flaps of the regulative valve are made of memory shape metal alloy. In the austenite phase the ...
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WO/2008/049054A1 |
Disclosed is an air conditioning system for an aircraft which utilizes high pressure bleed air. The bleed air is pressure controlled and introduced into a vortex cooler which can be operated in two modes using a valve. In a first mode, t...
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WO/2008/045108A2 |
Embodiments of the invention relate to a supersonic inlet employing relaxed isentropic compression to improve net propulsive force by shaping the compression surface of the inlet. Relaxed isentropic compression shaping of the inlet compr...
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WO/2008/040877A1 |
The present invention relates to a nacelle (1) for a turbojet engine comprising an air intake structure (4) capable of ducting a flow of air towards a fan and a central structure (5) intended to surround the said fan and to which the air...
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WO/2008/017567A1 |
An air inlet (2, 3) for a jet engine (1) is disclosed. The air inlet (2, 3) has a housing (5) with an inlet lip (51) which is mounted on the surface (6) of the aircraft. The flow upstream of the air inlet (2, 3) has a boundary layer (9)....
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WO/2008/016341A2 |
An air induction system for an engine to remove contaminants from intake air prior to delivery to the engine. The system includes a filtering unit having barrier filter panels attachable to a mounting frame. The filter panels are interch...
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WO/2007/122307A1 |
The present invention relates to a lip (4a) of an air inlet (4) of a turbojet pod (1) intended to be fastened to an air inlet downstream structure (4b) and including at least one electric heating element for defrosting, said electric hea...
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WO/2007/110494A1 |
The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and an inner skin (13), designed to be orien...
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WO/2007/110491A1 |
The present invention relates to a nacelle for a turbojet, comprising an air inlet structure capable of channelling a flow of air to a turbojet fan and a middle structure (5) comprising a casing (9) designed to encircle said fan, with th...
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WO/2007/108787A2 |
A pre-hung air inlet door assembly comprises an inlet door (41), a door box frame (42), and an actuation system(43). The door box frame is fastened to the support structure of an aircraft. The inlet door is operationally connected to the...
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WO/2007/090011A2 |
An inlet barrier filter system (11) is mountable on an aircraft (13) and is disposed for filtering air prior to intake into an engine of the aircraft. The filter system (11) generally includes a filter element (21) having filter media (3...
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WO/2007/053932A1 |
The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine (10), the engine (10) having an electrical motor (30) in a torque-driving engagement with a low pressure spool of the engine (10). The l...
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WO/2007/055088A1 |
An aircraft with a jet engine, in which air resistance acting on the front side of the aircraft is reduced to save energy during its flight. An air feeding duct (7) running from the head of a fuselage to the vicinity of an ejection openi...
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WO2007001372A9 |
A system for cooling a ducted fan aircraft engine includes a first nacelle surrounding the engine and a second nacelle substantially concentrically surrounding the first nacelle. The system includes a first spinner coupled around a base ...
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WO/2007/036523A1 |
The invention concerns an engine assembly (1) for an aircraft comprising an engine and an engine mounting structure for (4) the engine, the assembly also comprising a heat exchanging system (104) provided with a second outlet (122a) loca...
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WO/2007/036522A1 |
The invention concerns an engine assembly (1) for an aircraft comprising an engine and an engine mounting structure (4) the engine, the assembly also comprising a heat exchanging system (104) provided with a second outlet (122a) located ...
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WO/2007/037725A1 |
The invention relates to an arrangement (2) for propelling an aircraft comprising a jet engine (4) and an outlet nozzle (5) arranged downstream of the jet engine. The jet engine (4) is of a type which generates an internal core flow (20)...
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WO/2007/031616A1 |
The invention concerns a catching device (1) between a first structure (2) and a second structure (3), characterized in that it comprises at least one bolt (5) linked to the first structure and mounted in opposition to at least one elast...
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WO/2007/016086A1 |
An air induction system (20) for an engine (22) to receive intake air and provide for improved performance. The system includes a housing (30) having two separable sections (40, 42) interengageable at a seam (100). A seal located along t...
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WO/2007/015447A1 |
An unmanned helicopter has a fuselage (1a) with a main body (4) and a tail body; a main rotor (6) provided above the main body (4) and driven by an engine in the fuselage (1a); a tail rotor placed at the rear of the tail body (5); a pair...
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