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WO/2007/016085A1 |
An air induction system for an engine having an improved mechanism for control of an intake door. The system includes a housing having an opening for receiving intake air. A power activated door (56) is pivotable between a closed positio...
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WO/2006/049553A1 |
The invention relates to an outlet device (4) for a jet engine, the outlet device comprising an outlet nozzle (5) and a plurality of guide vanes (24, 25, 26, 27, 28) arranged movably in the outlet nozzle for guiding a gas from the jet en...
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WO/2006/034462A2 |
The present invention provides a means for inducing (educting) a 'passive' secondary flow stream (122) using an exhaust eductor system (110) including a primary exhaust nozzle (112) designed to transport an active flow stream (120) and a...
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WO/2006/016031A1 |
The invention relates to a multi-engine aircraft whose at least two engines (2, 3) are fixed to the fuselage wings symmetrically with respect to the longitudinal vertical plane of symmetry thereof, respectively and the third engine (7) i...
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WO/2006/012809A1 |
The essential elements of a total flow resistance of an engine driven heavier than air flying body are determined by the flow resistance induced by airfoils and the engine head resistance. The invention makes it possible to simultaneousl...
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WO/2005/090156A1 |
An aircraft engine assembly (10) is provided that is adapted to reduce noise produced by an engine (14) included in the engine assembly. The engine assembly (10) includes a nacelle (26) having an inlet section (34) and a main section (38...
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WO/2005/073600A1 |
An accessory driving apparatus for an aircraft system is connected to an accessory unit to be driven, such as a PCU pump. A gear set for transferring rotational power from the driving shaft to the driven shaft is provided for selective a...
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WO/2005/066536A1 |
The invention relates to a support device (1) which is designed to be installed between an aircraft engine and an associated thrust reverser, said device being equipped with a support means which can support at least one fire-detection e...
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WO/2005/063564A2 |
The invention relates to an air guiding flap of an aircraft wherein one surface (28) thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface (30) is exposed to the pressure of the rela...
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WO/2005/063579A1 |
A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the ai...
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WO/2005/061323A1 |
The inventive fluid cooling system for an aircraft (30) comprises an air-cooled heat exchanger (40) through which said fluid passes and which is provided with air intake means (52) and air exhaust means (54). Said air-cooled heat exchang...
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WO/2005/039978A2 |
In the operation of a turbojet engine of an aircraft, a method of reducing the infrared radiation in the engine's exhaust; comprising: 1) releasing infrared radiation masking material selected from the group consisting of liquid nitrogen...
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WO/2005/021934A2 |
An exhaust nozzle (38) includes an outer duct (50) surrounding an inner duct (36). The inner duct (36) includes a main outlet (46), and a row of aperture (48) spaced upstream therefrom. The outer duct (50) includes a row of intake (52) a...
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WO/2005/016748A2 |
An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) (10) contained within an aircraft housing (12) is provided. The inlet assembly includes an inlet duct (21), an actuator (46) and a door (44). The inl...
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WO/2004/090346A1 |
In order to modify a flow (for e.g. air or water) which drives a driving unit, or which is generated by a driving unit, placing of a ball like structure (21) is suggested. The ball like structure (21) is, thereby, located preferably in t...
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WO/2004/074096A1 |
A fire protection apparatus (90, 92) for an oil cooler (26) in an aircraft auxiliary power unit compartment (10) adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oi...
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WO/2004/016504A1 |
A single pilot aircraft that can be carried and bound to a pilot, comprises a turbojet engine, two propulsion air-outlet nozzles which are arranged on either side of the turbojet engine and which can be adjusted to change the direction o...
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WO/2004/013481A1 |
A thrust reverser system that includes a pass-through torque activated brake assembly (410) that limits the torque applied in portions of the thrust reverser system drive train. The brake assembly (410) includes two plates (602, 604) tha...
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WO/2003/100241A1 |
A turbofan exhaust nozzle (1A) includes a jet pipe (2) having a pair of thrust reverser doors (3) disposed on opposite sides thereof. Each door (3) has a hinge arm (4) joined to a swing arm (20), which in turn is joined to the pipe. Each...
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WO/2003/099654A2 |
A turbofan exhaust nozzle (28) includes a fan duct (40) defined between a fan nacelle (32) and a core engine cowling (30). The fan duct (40) includes a longitudinal endwall (48) and a partition (50) spaced therefrom to define a secondary...
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WO/2003/080432A1 |
The present invention provides an apparatus and method for varyi ng a wall skin to alter airflow over the skin. The apparatus has a first and second end-plates, a plurarity of flexible rods (106) are arranged substantially parallel to su...
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WO/2003/068597A2 |
A vertical take off and land (VTOL) jet aircraft (100) may have a jet engine mounted in a forwardportion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine,and include a cascade (206) and control box...
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WO/2003/057561A2 |
An aircraft equipped with peripherally configured directional thrust capability has an onboard primary power source producing compressed air, and at least two thrust producing modules (11). Each thrust producing module (11) has a fuel so...
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WO/2003/048543A1 |
The invention relates to a device for de-icing an external wall (4) of an aircraft, said wall being disposed at the front of a housing (6), and, in particular, the wall forming the annular lip of an air inlet of an aircraft engine. The i...
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WO/2003/037715A1 |
A passive cooling system for an auxiliary power unit (APU) installation (10) on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion (36) of a gas turbine engine (12) and an oil cooler (...
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WO/2003/033898A1 |
A thrust reverser system that has one or more moveable thrust reverser components for redirecting the thrust of a jet engine. The thrust reverser system has a torque limiter coupled between synchronization mechanisms that mechanically co...
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WO/2003/020585A1 |
The present invention provides wing assembly of a flying object for flapping motion of the wing, wherein said wing assembly is assembled to the engine frame of the flying object, comprising a wing lever and a wing frame with a wing cloth...
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WO/2002/103189A1 |
An electric thrust reverser actuation system Includes an electric motors that is controlled to operate in both a motoring mode and a generating mode. During normal actuation system operations, the electric motor is controlled to operate ...
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WO/2002/079631A1 |
A tortuous path quiet exhaust eductor system may be mounted to a gas turbine engine, such as commercial aircraft APU. The system includes an oil cooler, eductor primary nozzle, oil cooler nozzle, and surge air dump nozzle. The primary no...
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WO/2002/074621A1 |
A swirl generator for creating bulk swirl in a compressor plenum (22) in the opposite direction to the direction of rotation of the compressor rotor (12). The generator includes a continuous flow pasageway formed by an inlet duct (40) an...
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WO2002042150B1 |
A pneumatic deicer (10) which can withstand temperatures in excess of about 200 DEG F, in excess of about 300 DEG F and in excess of about 400 DEG F whereby it can be used on the guide vane surfaces (14) of jet engines. The deicer (10) i...
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WO/2002/044105A1 |
A method of surely manufacturing a porous sound absorbing material having low weight and excellent heat resistance enough to be used for the exhaust nozzle of a jet engine, high sound absorbing effect on the noise in wide band from the j...
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WO/2002/029224A1 |
An air intake guard (2) for an engine, turbocharger or supercharger; the guard (2) is securable over an air intake and extends outwards from the intake; the guard (2) is closed at its outer end and provides a plurality of spaced aperture...
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WO/2002/014149A1 |
The invention concerns an air intake of a turbofan engine, capable of being fixed at the front of an engine casing enclosing said fan, and comprising an annular inner wall (6), an annular outer cowl (5) radially spaced apart from the inn...
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WO/2001/062592A2 |
An air inlet assembly for bringing air to an auxiliary power unit (10) mounted in the APU compartment (12) of an aircraft (14). The assembly includes a duct (30) extending from an intake (32) contoured to conform to the aircraft fuselage...
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WO/2001/054981A2 |
A propulsion module (21) including a wave rotor detonation engine having a rotor (35a) with a plurality of fluid flow channels (35). The fluid flow channels (35) extend between an inlet rotor plate (34), which has a pair of fixed inlet p...
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WO/2001/054978A1 |
An improved aerobatic aircraft design having a first engine (18) located in the nose portion (14) of the fuselage (12) and a second engine (22) located in the tail portion (16) of the fuselage (12). The thrust components of both the firs...
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WO/2001/019675A2 |
A supersonic external-compression inlet (20) comprises a generally scoop-shaped supersonic compression section for diffusing a supersonic free stream flow (24). The supersonic compression section includes a main wall having a leading edg...
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WO/2001/012506A1 |
The present invention relates to an aircraft engine (2) which on its front is provided with an air inlet through which the air flows into the engine during use, the engine comprising a device (4) for protecting the air inlet, in which en...
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WO/2001/004485A1 |
An engine nozzle arrangement for an aircraft comprises a nozzle (18) for hot exhaust gases, and a shroud (20) for the stream of hot exhaust gases emerging from the exhaust nozzle. The shroud includes means (22, 24) providing an intake fo...
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WO/2000/074831A1 |
Gases are mixed in a mixing device having an elongate, tubular mixing chamber (16). At an inlet end of the mixing chamber (16), an annular nozzle (15) directs a drive gas under pressure longitudinally into the chamber (16). Inwardly, and...
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WO/2000/056602A1 |
A modular air intake duct system for a vehicle comprising: at least one intake duct (11, 13); and attachment means (17) for attaching said at least one intake duct to at least one structural member of a vehicle (1); wherein said at least...
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WO/2000/020272A1 |
In accordance with the present invention, there is provided an aircraft engine air intake cover (16) for use with an air intake (14) which is characterized by an air velocity profile therewithin. The air intake cover (16) is provided wit...
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WO/2000/012382A1 |
A jet aircraft has an elongated fuselage (12) with an intermediate section (16) of maximum lateral cross section, a generally conical aft fuselage section (18) of relatively smaller cross section and a single vertical stabilizer (20) ext...
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WO/2000/009392A2 |
A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (...
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WO/1999/061316A2 |
In a scarfed nacelle inlet for channelling aiflow to an engine having a longitudinal center line axis (ENGINE C/L), the duct including a crown (26) and a keel (28), an improvement including an inlet with a biplanar forward hilite. When v...
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WO/1999/058401A1 |
An IR Suppressor (20) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) and comprising a primary exhaust manifold (22), first and second mixing ducts (24a, 24b), and a secondary flo...
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WO1999033701A9 |
This invention pertains to supersonic air intakes intended for aircraft jet engines. The self-adjusting air intake comprises a supersonic area, a neck, a subsonic area and at least one additional channel connecting the supersonic area to...
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WO/1999/054204A1 |
An aircraft construction having an aircraft engine (1) and an engine nacelle (3) having a wall housing the engine. A cowl door (5) is provided in the wall of the nacelle providing access to the engine (1) to service it. An exhaust duct (...
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WO/1999/051870A1 |
The invention concerns a turbojet thrust reverser comprising pivoting hollow doors (3), integrated in direct jet in the pod external cowling and constituting in inverse jet flux deviating obstacles forming scoops. A mobile external cowli...
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