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WO/1999/046498A1 |
The invention concerns a turbojet thrust reverser comprising pivoting hollow doors (3), integrated in direct jet in the engine pod external spinner and constituting in reverse jet flux deviation obstacles forming scoops. A mobile deflect...
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WO/1999/005406A1 |
The invention concerns a turboblower thrust reverser comprising obstacles (3) retracted, in direct thrust, in the turboblower primary cowling wall (4) and unfolded to form a ring-shaped flux-deviating assembly providing thrust reversal b...
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WO/1999/005407A1 |
A turning vane arrangement (30) for an IR suppressor having a duct (32) adapted for receiving a primary flow PF of engine exhaust. The turning vane arrangement (30) is operative to direct a pressurized secondary flow PSF of low temperatu...
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WO/1999/002842A1 |
The invention concerns thrust reversers for aircraft turbo-shaft engines and more particularly such reversers (10) specially designed for visual ground control of the locking of throttles (25). Said reverser (10) is characterised in that...
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WO/1999/002843A1 |
The invention concerns an aircraft turbojet thrust reverser specially designed to resist shocks from objects coming from the turbo-shaft engines around which they are arranged, such as wrecks of vanes or disks, said shocks being capable ...
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WO/1998/059162A1 |
A multi-stage mixer-ejector (20) having at least one exhaust nozzle (24 or 28) which includes inlet conduit adapted for receiving a primary flow PF of engine exhaust and a plurality of adjoined lobes (30) integrally formed in combination...
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WO/1998/059163A1 |
An exhaust nozzle (24 or 28) operative to suppress the InfraRed (IR) signature radiated from the high-temperature exhaust of an engine (12) which exhaust nozzle (24 or 28) includes an inlet conduit adapted for receiving the high-temperat...
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WO/1998/057055A1 |
In a turbofan associated with a thrust reverser, the internal structure (11) forming the turbofan primary cowl and the external structure (12) supporting said reverser (10) do not comprise any link in the lower part of the structures (11...
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WO/1998/057056A1 |
The invention concerns a turbojet thrust reverser comprising a fixed upstream ring-shaped structure (11) and a downstream ring-shaped structure (12) movable in translation between an upstream position wherein an upstream part of said dow...
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WO/1998/055755A1 |
The invention concerns a turbojet thrust reverser comprising hollow pivoting doors (3) integrated in direct jet in the external pod cowling and constituting in reverse jet flux deviation obstacles forming scoops. A mobile deflector (24) ...
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WO/1998/055756A1 |
The invention concerns a turbojet thrust reverser comprising hollow pivoting doors (3), integrated in direct jet in the external pod cowling and constituting in reverse jet flux deviating obstacles forming scoops. A mobile part forming a...
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WO/1998/048160A1 |
The invention relates to an air intake system (1) for a gas turbine engine in which a weather hood is arranged in front of a filter device (4). An air conduction device (9) is placed in front of the filter device (4) in order to homogeni...
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WO/1998/040617A1 |
The invention concerns a bypass turbojet thrust reverser comprising pivoting doors (7) integrated in direct jet in the external wall of the fan air duct (15) and constituting flux deviating obstacles providing thrust reversal. The door (...
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WO/1998/040618A1 |
The invention concerns a bypass turbojet thrust reverser comprising pivoting doors (7) integrated in direct jet in the external wall of the fan air duct (15) and constituting deviating obstacles after pivoting providing thrust reversal. ...
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WO/1998/030794A1 |
The invention concerns a turbojet thrust reverser comprising a mobile shroud (7) capable of being displaced in translation downstream by means of actuators (4) uncovering blade rows (13) and driving flap shutters (12) pivoting about an a...
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WO/1998/029654A1 |
Disclosed is a thrust reverser for diverting the bypass flow of a bypass turbojet, comprising shiftable elements or buckets (17). At least one downstream portion of each bucket covers, in the direct flow, a portion of a fixed structure (...
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WO/1998/029655A1 |
The invention ensures the connection between a mobile element (2) which can be displaced by rotation around its swivels (3), and a fixed structure (1), said connection comprising a shaft (8) situated on a fixed structure element (1) and ...
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WO/1998/029306A1 |
The pod (12) of a turbofan (10) comprises a front structural element (30) the external surface of which is continuous and extends over at least 50 % of the pod geometrical chord. Furthermore, said element (30) is mounted on guiding and m...
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WO/1998/026172A1 |
A thrust reverser of a turbofan comprises pivoting doors (7) integrated in direct jet in the external wall of the ring-shaped conduit (15) and constituting flux deviating obstacles. A streamlined piece (21) connected to the reverser fixe...
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WO/1998/025020A1 |
The invention concerns a thrust reverser for a turbofan comprising doors (7) integrated in direct jet in the external wall of the ring-shaped conduit (15) and pivoting by the operation of a control actuator (8) to constitute deviation ob...
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WO/1998/023852A1 |
The invention concerns a device for connecting the external housing (3) of a turbo-engine (1) with the thrust reverser (15) in two articulated half-shells (16), said thrust reverser (15) and said housing (3) being already connected by th...
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WO/1998/021466A1 |
The electric control system for thrust reverser with movable elements comprises at least an electromechanical control set (7) connected to an electronic control housing (20). The electromechanical control set (7) is essentially made up o...
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WO/1998/016732A1 |
A failsafe nozzle actuating system (2) for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle (14) has a vectoring ring (86) operably linked to a plurality of pivotal flaps (50) which are circumferentially disposed abou...
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WO/1998/015731A1 |
A turbofan thrust reverser comprises pivoting doors (2), integrated in direct jet in the external wall of the flux conduit and constituting flux deviation obstacles in reverse thrust. At least one door (2) comprises in the downstream zon...
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WO/1998/014699A1 |
The invention concerns a method for closing the doors (10) of an aircraft thrust reverser (8) enabling this closure despite the pressure increase of the propulsion air generated by the turbojet engine. This method is characterised in tha...
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WO/1998/014698A1 |
A turbojet thrust reverser comprises pivoting doors (7) capable of pivoting by the action of a thrustor (4) whose linking point (8) with the fixed structure upstream of the reverser and whose linking point (9) with the door (7) are in a ...
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WO/1998/010984A1 |
An apparatus and method for reducing noise within the fuselage of a propeller driven aircraft (20). In one embodiment the propeller blades (38) are spaced apart and in front of an offset inlet (48). The inlet (48) provides air to a gas t...
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WO/1998/009868A2 |
A noise suppression system for a jet engine, the system having a substrate formed of open cell material, a layer of microporous material covering at least a portion of one surface of the substrate, a layer of substantially non-porous mat...
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WO/1998/005857A1 |
A jet engine thrust reverser comprising pivoting doors (20) that are integrated into the outer exhaust duct wall in the direct thrust position, and form deflecting buckets in the thrust reversal position. Said door (20) pivots about a sh...
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WO/1998/005553A1 |
The present invention provides a tailcone and power assembly (10) mountable to the body of an aircraft using a height adjustable dolly (11). The tailcone assembly comprises a longitudinal support member (14), a gas turbine engine (12) mo...
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WO/1997/049608A1 |
A specially contoured barrier type filter (14) disposed in front of a helicopter turbine inlet provides for maximized airflow during forward, as well as sideways flight. The contouring additionally reduces the tendency of the filter to c...
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WO/1997/044577A1 |
A turbofan thrust reverser comprises movable elements (6, 7) integrated in direct jet into the wall of the turbofan primary cowling (10) and forming flow deviation obstacles in reverse jet. Each movable element supported by pivoting axes...
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WO/1997/043537A1 |
A thrust reverser for a twin flow turbo-jet engine comprises pivoting doors (7) integrated in the direct jet pod wall and forming obstacles for deviating the reverse jet flow. Each upstream part of the doors (7) is internally lined with ...
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WO/1997/043536A1 |
A thrust reverser for a twin flow turbo-jet engine comprises pivoting doors (7) integrated in the direct jet pod wall in and forming obstacles for deviating the flow in the reverse jet mode. Each upstream portion of the door (7) is inter...
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WO/1997/035105A1 |
A diverterless engine inlet (10) system that integrates a "bump" (20) surface with a forward swept, aft-closing cowl (30) to divert substantially all of the boundary layer air from the inlet. The bump includes an isentropic compression s...
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WO/1997/030278A1 |
A bypass jet engine thrust reverser comprising pivoting doors (7) integrated into the outer pod wall in the direct thrust position and pivoted out by a hydraulic cylinder (8) to form deflecting buckets for thrust reversal. An internal up...
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WO/1997/002985A1 |
The invention concerns a turboprop engine (2) in the pod (1) of which an air-oil cooler (5) is disposed downstream of a cooling air inlet opening (7). The oil cooler exhaust air is discharged via an air duct (10) with which a cooling air...
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WO/1997/002984A1 |
The invention concerns a turboprop engine comprising an oil cooler (5) which is disposed in the engine pod (1) and upon which cooling air acts. The oil cooler (5) is disposed in a flow duct (6) which at the rear opens into the environmen...
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WO/1996/014516A1 |
A seal including a body (11) with a recess (8) at one end engageable by a spanner, and a screw thread (2) at the other end for engaging a complementary screw thread (7) in an opening (6) of a housing (3). A locking ring (31) biased by a ...
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WO/1996/009206A1 |
The invention is a shroud (30) for a reversible thrust fan, the shroud (30) having an inlet duct (38) and an exhaust nozzle (42) with the fan (36) located therebetween. In general terms, the shroud (30) includes a system for increasing t...
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WO/1995/019289A1 |
Nozzles (3, 5) for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct (1) exit. High velocity air is discharged tangential to an outer surface of each nozzle (3, 5) and follows the contour ther...
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WO/1995/013467A1 |
A system for removing and/or preventing ice build-up on an aircraft includes at least one heat exchanger (10, 60, 66, 72, 78) mounted within an aperture (22) in the tailpipe of a gas turbine engine (14). The heat exchanger includes an in...
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WO/1995/008473A1 |
A duct cover (12) for use with a duct (4) within a vehicle, the duct cover (12) operative for directing a fluid flow. The duct cover being further operative for minimizing the entrance of foreign object debris into the duct (4). The duct...
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WO/1994/001735A1 |
An improved S-duct (10c) for turbo-jet engined aircraft. The present invention allows a high volume of high energy air to traverse the S-duct (10c) at a high pressure recovery ratio.
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WO/1993/016280A1 |
A method and apparatus for cooling the heat generated by a gas turbine engine mounted in a compartment is provided. The apparatus comprises a novel eductor (60) that incorporates a mixer nozzle (70) to entrain sufficient air flow through...
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WO/1993/006005A1 |
An aircraft structural component comprises a forward compartment (17) formed by a forward bulkhead (19) and a skin structure (21) which extends forwardly of the forward bulkhead (17) and which has an outer surface which requires to be pr...
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WO/1990/009313A1 |
A Vertical Take-off and Landing Aircraft (10) using top-surface blowing to generate lift in conjunction with thrust reversing means (68) to react forward travel such that vertical flight is achieved. In a preferred embodiment, the aircra...
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WO/1990/006440A1 |
A starting system for an aircraft propulsion engine is disclosed. An electrical motor (62 or 122) is mounted within a case (14) in which first and second hydraulic units (102, 104) are operated as part of a constant speed drive transmiss...
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WO/1990/003309A1 |
A ducted fan turbine engine (2) includes an inner discharge nozzle (18) and an outer discharge nozzle (8) surrounding the inner discharge nozzle. The engine (2) is mounted on an aircraft wing by a pylon. The rear part of this pylon suppo...
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WO/1989/005757A1 |
A service valve (10) is provided to provide an apparatus and method for filling a constant speed drive without overfilling and for preventing gas entrapment in the oil circuit of the drive. The valve (10) has a spool (12) movable in resp...
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