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Analysis

1 / 489,999
1.WO/1996/026359THRUST REVERSER WITH DOWNSTREAM FLAPS FOR TURBOJET ENGINES
WO - 29.08.1996
Int.Class F02K 1/70
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
64Reversing fan flow
70using thrust reverser flaps or doors mounted on the fan housing
 Appl.No PCT/FR1996/000249 Applicant SOCIETE HISPANO-SUIZA Inventor VALLEROY, Laurent, Georges
A bypass turbojet engine thrust reverser wherein flaps (20) are built into the outer wall (14) of a bypass duct for operation with undeflected thrust, and form the downstream end of the fan exhaust nozzle. In the deployed position, the flaps (20) pivotably mounted on pivots (21) and combined with displacement means constitute bypass flow deflecting obstacles. The back of each flap (20) is connected to the internal fixed structure (18) of the duct via a connecting rod (23), and the flap pivots (21) are supported by sliding members (22) that are rearwardly slidable in a direction parallel to the engine axis when the flaps (20) are deployed.
2.WO/1995/016866DISTRIBUTED-LOAD ORBITAL GEAR TRANSMISSION
WO - 22.06.1995
Int.Class F16H 1/28
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
16ENGINEERING ELEMENTS OR UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
HGEARING
1Toothed gearings for conveying rotary motion
28with gears having orbital motion
 Appl.No PCT/FR1994/001460 Applicant SOCIETE HISPANO SUIZA Inventor LEFRANC, Bénédicte, Anne-Marie
A transmission having orbital gears (1) comprising at least one planet pinion (5) meshing with a central planet gear (2) and an outer planet gear (8), each planet pinion (5) being rotatably mounted at a free end (19) of a flexible shaft (6) while the other end (18) of the flexible shaft (6) is secured to a planet pinion carrier (4). Said transmission (1) is remarkable in that the gears are helical, and the planet pinions (5) swivel and are combined with an overturning moment compensation device (34, 80) which holds them in place.
3.WO/1998/014699METHOD AND DEVICES FOR CLOSING THE DOORS OF A THRUST REVERSER
WO - 09.04.1998
Int.Class F02K 1/76
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
76Control or regulation of thrust reversers
 Appl.No PCT/FR1997/001739 Applicant HISPANO-SUIZA Inventor BAUDU, Pierre, André, Marcel
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 that it comprises the following steps: a) holding the door (10) by its front end (10a) before the door (10) is completely closed; b) pulling the door (10) by its front end (10a) until it is in closed position; c) repeating the tractive force thus produced on the part (8a) of the structure (8) in straight line with the front end (10a) of the door (10). The invention also concerns devices specially designed for implementing the method.
4.WO/1997/018389JET ENGINE THRUST REVERSER HAVING DOWNSTREAM BALANCE-BIASED BUCKETS
WO - 22.05.1997
Int.Class F02K 1/60
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
56Reversing jet main flow
60by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
 Appl.No PCT/FR1996/001792 Applicant HISPANO SUIZA Inventor LARDY, Pascal
A jet engine thrust reverser comprising clamshells (16) that are integrated into the outer wall of the jet engine exhaust duct in the direct thrust position and form gas flow deflecting buckets in the deployed position to provide thrust reversal. The clamshells (16) are pivotably mounted about shafts (19) supported on stationary side beams (10) that also support a motion control system (20). The beams (10) are broad, the ratio of the beam width to the exhaust outlet length is of at least 0.60, and said shafts (19) are located at the centre of pressure of the inner wall (17) of each clamshell, so that said clamshells (16) are stable in the undeployed position and have a tendency to balance towards the closed position.
5.WO/1999/015771TURBOJET THRUST REVERSER WITH INTERNAL BUCKETS
WO - 01.04.1999
Int.Class F02K 1/60
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
56Reversing jet main flow
60by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
 Appl.No PCT/FR1998/002054 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor METEZEAU, Fabrice, Henri, Emile
The invention concerns a turbojet thrust reverser comprising a mobile part consisting of two internal buckets (12) mounted on fixed pivots (18) of the fixed structure (1) and an axially mobile annular structure (11) constituting the pod downstream external part (13) and in direct jet, the downstream part (15) of the airstream channel radially external wall, forming the trailing edge and covering said buckets (12) which constitute part of said airstream radially external wall.
6.WO/1997/047179VEGETAL SOIL MIXTURE FOR CULTIVATED TURF AND METHOD FOR PRODUCING THE SAME
WO - 18.12.1997
Int.Class A01G 1/00
AHUMAN NECESSITIES
01AGRICULTURE; FORESTRY; ANIMAL HUSBANDRY; HUNTING; TRAPPING; FISHING
GHORTICULTURE; CULTIVATION OF VEGETABLES, FLOWERS, RICE, FRUIT, VINES, HOPS OR SEAWEED; FORESTRY; WATERING
1Horticulture; Cultivation of vegetables
 Appl.No PCT/RU1996/000171 Applicant MYLNIKOV, Vladimir Nikolaevich Inventor MYLNIKOV, Vladimir Nikolaevich
The present invention relates to a vegetal soil mixture for cultivated turf that also comprises a rocky material, preferably marble crumbs having a fraction size between 3 and 10 mm. This mixture comprises the following components in wt.%: from 60 to 80 % of sandy or clayey soil or black earth; from 5 to 20 % of peat; from 2.5 to 10 % of rocky material; the balance being sand. The method for producing this mixture comprises sifting the sandy or clayey soil or black earth using a screen having cells not exceeding 12 mm. The mixture is then fed under dry weather conditions into a drainage system or spread onto the subsoil in a layer having a thickness between 3 and 50 cm depending on the future use of the turf. This layer is applied from the centre of the lawn towards its edges while maintaining the slope of the subsoil or drainage system. The surface of the added or flattened mixture is then rolled using a wooden compactor that weighs up to 100 kg and comprises a drum with a diameter and a length varying from 80 to 120 cm and from 130 to 150 cm respectively. The mixture thus applied is further submitted to vapour treatment for 3 to 4 weeks in order to settle and watered daily in the absence of rain.
7.WO/1998/047763TRACTION SYSTEM FOR PROPELLER-DRIVEN TRANSPORT AEROPLANE
WO - 29.10.1998
Int.Class B64D 27/14
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
27Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
02Aircraft characterised by the type or position of power plants
10of gas-turbine type
14within, or attached to, fuselages
 Appl.No PCT/FR1998/000764 Applicant SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION Inventor DUSSERRE-TELMON, Guy, Franck, Paul
The invention concerns a traction system for a propeller-driven transport aeroplane comprising at least a first and second pair of propellers (11, 12; 31, 32) mounted in the aeroplane wing plane. Each pair of propellers comprises two propellers symmetrically arranged on either side of the aeroplane central and longitudinal axis XX'. The first and second propeller pairs(11, 12; 31, 32) are driven independently of each other, respectively by first and second engine units (10, 30) arranged side by side in the aeroplane fuselage and by first and second independent transmission assemblies (13, 33).
8.WO/1997/009526TURBOJET THRUST REVERSER HAVING DOORS COMBINED WITH AN UPSTREAM SCOOP PANEL
WO - 13.03.1997
Int.Class F02K 1/68
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
1Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
54Nozzles having means for reversing jet thrust
64Reversing fan flow
68Reversers mounted on the engine housing downstream of the fan exhaust section
 Appl.No PCT/FR1996/001359 Applicant SOCIETE HISPANO-SUIZA Inventor GONIDEC, Patrick
A dual flow turbojet thrust reverser has pivoting doors (7) forming deflection members when operating in thrust reversing mode. Each door (7) is lined on its inner surface, in a closed position thereof, with an upstream panel (22) smoothing the fluid stream in direct jet mode. The upstream panel (22) which is not connected to the door (7) can rotate, when in thrust reversing mode, in a direction opposite to that of the door (7) so that its upstream edge is radially closer to the duct axis than its downstream edge, thus forming a scoop that picks up an inner portion of the stream to control the reverse flow layers and to provide for efficient thrust reversal.
9.WO/1999/002843SHOCKPROOF THRUST REVERSER
WO - 21.01.1999
Int.Class B64D 29/06
BPERFORMING OPERATIONS; TRANSPORTING
64AIRCRAFT; AVIATION; COSMONAUTICS
DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
29Power-plant nacelles, fairings or cowlings
06Attaching of nacelles, fairings, or cowlings
 Appl.No PCT/FR1998/001482 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor BAUDU, Pierre, André, Marcel
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 of deforming the thrust reverser ring-shaped structure or break the stiffeners thereof. Said reverser is characterised in that the emergency locking systems (33) comprise each an articulated slide bolt (38) one end of which has the shape of a hook (40) partially enclosing the locking interface (43), the slide bolt (38) being automatically returned for closing by elastic means (47). Such arrangement enables to produce additional mechanical links capable of compensating deformations of the thrust reverser ring-shaped structure or the breakage of stiffeners.
10.WO/1994/002739PLASMA MOTOR WITH CLOSED ELECTRON DRIFT
WO - 03.02.1994
Int.Class F03H 1/00
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
03MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
HPRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
1Use of plasma to produce a reactive propulsive thrust
 Appl.No PCT/FR1993/000610 Applicant SOCIETE EUROPEENNE DE PROPULSION Inventor MOROZOV, Alexei
A plasma motor comprises a main annular ionisation and acceleration channel (24) defined by components (22) made of an insulating material, and open at its downstream end (225), at least one hollow cathode (40) with means (41) for supplying an ionisable gas, and an annular anode (25) concentric with the main annular chamber (24) and positioned remotely from the open downstream end (225). An annular buffer chamber (23) radially larger than the main annular channel (24) is located upstream of the latter beyond the zone in which the annular anode (25) is placed. Means (26) for supplying an ionisable gas open through an annular distributor (27) into a zone upstream of said anode (25), different from that in which the anode (25) is placed. Means (31 to 33, 34 to 38) for creating a magnetic field in the main channel (24) are provided for producing an essentially radial magnetic field in said main channel (24), the gradient of said field showing maximum induction at the downstream end (225) of the channel (24).
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