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Analysis

1 / 486,981
1.WO/1993/004273TURBOREACTOR THRUST REVERSER HAVING A PROGRESSIVE CURVATURE DEFLECTING EDGE
WO - 04.03.1993
Int.Class F02K 1/56
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
 Appl.No PCT/FR1992/000802 Applicant SOCIETE ANONYME HISPANO SUIZA Inventor CARIMALI, Félix
A reverse path (17) for the passage of flow reversed by a turboreactor thrust reverser is delimited on one side by deflecting edge (108) integral with a stationary part (1). The longitudinal sections (A, B, C, D) of the deflecting edge (108) have a progressive curvature from one lateral edge to the other of the reverse path such as to improve control of the reverse thrust layers.
2.WO/1997/030279JET ENGINE THRUST REVERSER WITH DOORS LINKED TO AN UPSTREAM PANEL
WO - 21.08.1997
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/FR1997/000273 Applicant SOCIETE HISPANO-SUIZA Inventor JEAN, Michel, Christian, Marie
A bypass jet engine thrust reverser comprising pivoting doors (7) integrated into the outer pod wall in the direct thrust position and forming deflecting buckets for thrust reversal. An internal upstream panel (20) lines the inner surface of each door (7) and is hinged to the same pivot (27) as the door (7). The linkage between the door (7) and the upstream panel (20) consists of an epicyclic gear train assembly comprising a planet gear (31) secured to the door (7), an outer sprocket wheel (34) secured to the upstream panel (20), and at least one freely rotatable planet pinion (33) secured to the fixed structure of the reverser. When a control means switches to the thrust reversal position, the door (7) and the upstream panel (20) pivotally rotate in opposite directions.
3.WO/2001/096711DEVICE FOR LOCKING HAMMER CLAMP BLADES ON A DISC
WO - 20.12.2001
Int.Class F01D 5/30
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members; Heating, heat-insulating, cooling, or antivibration means on the blades or the members
30Fixing blades to rotors; Blade roots
 Appl.No PCT/FR2001/001843 Applicant SNECMA MOTEURS Inventor GOGA, Jean-Luc, Christian, Yvon
The invention concerns a device for locking hammer clamp blades in the groove (2) of a disc (1) of a gas turbine engine wheel comprising a body (15) whereof the cross-section is shaped to match the cross-section of the groove (2), a locking element (16) mounted radially mobile in a through hole provided in the body (15) and capable of being partly received in a lock housing (9a, 9b), and a screw for manoeuvring (17) the locking element (16). The locking element (16) comprises stops (32a) sliding in the windows (22a) of the body (15). The screw head (41) is large-sized and is radially locked between the base of the groove (2) and the seat (20) of the body (15).
4.WO/2001/067026SYSTEM FOR REACTIVE ARMOR OF MILITARY EQUIPMENT. SYSTEM FOR REACTIVE ARMOR OF A TURRET.
WO - 13.09.2001
Int.Class F41H 5/007
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
41WEAPONS
HARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
5Armour; Armour plates; Shields
007Reactive armour; Dynamic armour
 Appl.No PCT/EA2001/000001 Applicant GRIGORYAN, Valery Armenakovich Inventor GRIGORYAN, Valery Armenakovich
The inventive system relates to the protection of military equipment against shells and is directed at developing a modular protection. The system for reactive armor of a hull (1) and a turret (2) is embodied in the form of modules (3, 4, 5). A hull module (3) is embodied as a single unit assembled from load-carrying side rails (6) and cross ribs (7) which are rigidly connected to each other and form sections wherein protective blocks (8) are placed. The hull (2) modules are unified in the form of protective rigidly connected blocks (8). The protective blocks (8) comprise armored layers (9, 10) and form a cavity wherein one or several layers of active elements (11) can be arranged. Metal plates (12, 13) can be arranged in the cavity between the layers of active elements (11) and between the armored layer (9, 10) and the active elements (11). The armored layers (9, 10) can be made of various materials and embodied in the form of composite structures (14, 15). In addition, a layer of a protective material can be applied to the layer of protective elements (11), to the metal plates (12, 13) and to the cavity surface.
5.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.
6.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).
7.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.
8.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.
9.WO/1998/038425TURBOJET THRUST REVERSE SYSTEM WITH DOORS ASSOCIATED WITH A CONTROL SYNCHRONISING DEVICE
WO - 03.09.1998
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/FR1998/000310 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor BAUDU, Pierre, André, Marcel
The invention concerns a bypass turbojet thrust reverse system comprising pivoting doors (7a, 7b) integrated in direct jet in the outer wall of the fan air duct (15) and constituting flux deviating obstacles providing thrust reversal. At least two actuators (23) controlling the door (7a, 7b) movements are associated with a synchronising device (19) consisting of an electric motor (20) and its electronic power system (21) and a bezel box (22) connected by a transmission linkage (26) to each actuator (23) respectively. Thus the security of operation is ensured in the event that the door is not locked.
10.WO/1998/057056TURBOJET THRUST REVERSER HAVING DOORS WITH VARIABLE EXHAUST SECTION
WO - 17.12.1998
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/FR1998/001200 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor GONIDEC, Patrick
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 downstream structure (12) is housed inside the upstream structure (11) and a downstream position wherein it produces a variation in the exhaust section between the turbojet primary cowl (15) and the downstream structure (12) radially inner wall. The downstream ring-shaped structure (12) further comprises doors (20) integrated in closed position, in direct jet, in the pod wall and deviating at least part of the turbojet exhaust flow, in unfolded position providing thrust reversal after the translation of the downstream structure (12).
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