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Analysis

1 / 486,530
1.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.
2.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).
3.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.
4.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.
5.WO/1998/029654THRUST REVERSER FOR A BYPASS TURBOJET WITH DOWNSTREAM BUCKETS
WO - 09.07.1998
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/FR1997/002338 Applicant HISPANO SUIZA Inventor GONIDEC, Patrick
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 (20) which forms the outer wall of the bypass flow canal, the outer surface of said bucket (17) forming a portion of the outer pod surface. Attachment, retention, and guidance during the displacement of the bucket (17) are ensured by a system of connecting rods placed upstream (36) and downstream (27), said rods (27, 36) being situated on the fixed structure of the pod and disposed in the direct flow inside the thickness of the fixed beam that separates two buckets (17).
6.WO/1998/030794THRUST REVERSER WITH BLADE ROWS WITH OPTIMISED ACTUATOR CONTROL
WO - 16.07.1998
Int.Class F02K 1/72
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
72the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
 Appl.No PCT/FR1998/000032 Applicant HISPANO SUIZA Inventor VAUCHEL, Guy, Bernard
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 articulation (15) integral with the internal wall (16) of the annular channel (17), by means of connecting rods (14), so as to close the channel (17) or to deviate the flux ejected through the rows (13), providing thrust reversal. The longitudinal geometrical axis of the actuator (4) is in line with the link (9) with the mobile shroud (7) and with a contact point (2), at the level of the device for installing the reverser, between a blade (3) integral with the fixed upstream reverser structure (6) and an interface flange (5) integral with the casing of the turbojet.
7.WO/1992/018865IMMUNOASSAY FOR THE DETECTION OF HIV SPECIFIC IgM
WO - 29.10.1992
Int.Class G01N 33/569
GPHYSICS
01MEASURING; TESTING
NINVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
33Investigating or analysing materials by specific methods not covered by groups G01N1/-G01N31/131
48Biological material, e.g. blood, urine; Haemocytometers
50Chemical analysis of biological material, e.g. blood, urine; Testing involving biospecific ligand binding methods; Immunological testing
53Immunoassay; Biospecific binding assay; Materials therefor
569for microorganisms, e.g. protozoa, bacteria, viruses
 Appl.No PCT/US1992/002585 Applicant CEDARS-SINAI MEDICAL CENTER Inventor BRUNELL, Philip, Alfred
A method of immunoassay for detecting antibodies to human immunodeficiency virus (HIV). The assay detects HIV specific IgM antibody thereby distinguishing those infants who are infected with HIV from those who have passively acquired maternal HIV specific IgG antibodies. Additionally, the assay can be used to detect individuals infected with HIV who have not yet mounted an IgG immune response.
8.WO/1996/019641PROTECTIVE SHIELD FOR A TURBOMACHINE
WO - 27.06.1996
Int.Class F01D 21/04
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
21Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
04responsive to undesired position of rotor relative to stator, e.g. indicating such position
 Appl.No PCT/FR1995/001698 Applicant SOCIETE HISPANO SUIZA Inventor GLOWACKI, Pierre, Antoine
Shield for protecting the outer fairing (3) of a turbomachine. Said shield consists of a ring of ductile material retained by fastening means with fairly easy breaking properties. When a piece of the rotor (17) comes loose accidentally and impacts said shield, the denting caused ruptures some or all of the fastening means. This allows the shield (9) to undergo considerable deformation thus enhancing its energy absorbing capability.
9.WO/1998/057055TURBOFAN ASSOCIATED WITH A THRUST REVERSER WITH SHROUD DIRECTLY MOUNTED IN THE FILAMENT OF FLOW
WO - 17.12.1998
Int.Class F02K 1/52
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
52Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
 Appl.No PCT/FR1998/001199 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor GONIDEC, Patrick
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, 12) and form between them (11, 12) a ring-shaped air flow channel (15). A shroud (25) is arranged in said channel (15) on the downstream side of an arm (3) forming the external support structure of the turbojet aft fan duct external wall.
10.WO/1997/020137JET ENGINE THRUST REVERSER HAVING DOORS WITH A HINGED REAR PANEL
WO - 05.06.1997
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/FR1996/001882 Applicant HISPANO SUIZA Inventor GONIDEC, Patrick
A bypass jet engine thrust reverser comprising pivoting doors that are closed and integrated into the outer wall of the exhaust duct (15) in the direct thrust position and pivot out into a deployed position to form deflecting buckets and thereby provide thrust reversal. Each door (7) comprises a downstream rear element (21) hinged to the door, and the rear surface (23) of said rear element (21) forms part of the outer wall of said exhaust duct (15) in the direct thrust position so that the forces exerted by the exhaust flow on said rear element (21) urge the door (7) into the undeployed position.
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