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Analysis

1 / 489,077
1.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.
2.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.
3.WO/1997/002419SINGLE-CLAMSHELL TURBOJET THRUST REVERSER
WO - 23.01.1997
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/FR1996/001039 Applicant SOCIETE HISPANO-SUIZA Inventor METEZEAU, Fabrice, Henri, Emile
A turbojet thrust reverser comprising a fixed upstream structure (10) with a downstream end having a tapered edge (14) that does not lie in a plane perpendicular to the reverser axis (15), and a movable portion consisting of a single clamshell (16) which, when in the closed position, forms the downstream portion of the direct-flow exhaust nozzle, and may be pivoted about two side pivots (22) on the fixed structure (10) by a control system comprising at least one actuator (23) mounted between a pivot secured to the fixed structure and a pivot secured to the clamshell, so that, in the deployed position, said clamshell forms a bucket for deflecting the gas flow (13a) to reverse the thrust.
4.WO/2001/036692METHOD FOR ULTRASONIC SHOT BLASTING OF LARGE-DIMENSIONED ANNULAR SURFACES ON THIN PARTS WORKPIECES
WO - 25.05.2001
Int.Class C21D 1/04
CCHEMISTRY; METALLURGY
21METALLURGY OF IRON
DMODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
1General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
04with simultaneous application of supersonic waves, magnetic or electric fields
 Appl.No PCT/FR2000/003182 Applicant SNECMA MOTEURS Inventor DUQUENNE, Catherine, Dominique, Béatrice
The invention concerns a method for ultrasonic shot blasting of large-dimensioned annular surfaces (5) on thin workpieces (1). Said method is characterised in that the surface to be shot blasted (5) performs at least N = five revolutions in front of the shot blaster opening (10) during the shot blasting process, so as to reduce the deformations of the workpiece (1).
5.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.
6.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).
7.WO/1998/005857JET ENGINE THRUST REVERSER WITH SCOOP-LIKE DOORS
WO - 12.02.1998
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/FR1997/001406 Applicant HISPANO SUIZA Inventor GONIDEC, Patrick
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 shaft (21) located downstream therefrom, the upstream edge projects into the duct and the door (20) remains within the space occupied by the pod. The door (20) comprises an internal nozzle space (37) between a first upstream opening (36), an inner panel (27), an outer panel (29) and a second opening (32) provided on the downstream side between a downstream edge and said outer panel (29). In the thrust reversal position, at least part of the deflected flow passes through said internal space (37) of the scoop-like door (20), whereas in the direct thrust position, the second opening (32) is covered by a covering member (33) integral with the fixed structure, and the forces exerted by the flow on the inner panel (27) maintain the door (20) in the closed position.
8.WO/1999/051870TURBOJET THRUST REVERSER WITH DOORS FORMING SCOOPS ASSOCIATED TO AN ARTICULATED EXTERNAL COWLING
WO - 14.10.1999
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/FR1999/000743 Applicant HISPANO-SUIZA AEROSTRUCTURES Inventor VAUCHEL, Guy, Bernard
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 cowling (20) covers in direct jet, both the reverser fixed structure front frame (8) and the door (3) flux outlet section. The external cowling (20) is mounted pivoting (29) downstream of the door (3) pivot (9) and its upstream edge moving in centrifugal direction so as to clear a space both above the front frame (8) and the deviated flux outlet section.
9.WO/1997/030278JET 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/FR1997/000272 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 pivoted out by a hydraulic cylinder (8) to form deflecting buckets for thrust reversal. An internal upstream panel (20) lines the inner surface of each door (7), and the door (7) and the upstream panel (20) are pivotable about separate respective pivots (27, 28). The door (7) and the upstream panel (20) are joined together via a so-called three-point linkage (30) hinged to a first point (31) on a support (32) secured to the upstream panel (20), to a second point (33) on the door (7), and to a third point (34) at the end of the rod of the control cylinder (8), whereby no opening torque is transmitted to the door (7) in the direct thrust position by the pressure forces exerted on the upstream panel (20).
10.WO/1995/004363DEVICE FOR TRANSMITTING ELECTRIC POWER SIGNALS TO A ROTARY UNIT
WO - 09.02.1995
Int.Class H01F 38/18
HELECTRICITY
01ELECTRIC ELEMENTS
FMAGNETS; INDUCTANCES; TRANSFORMERS; SELECTION OF MATERIALS FOR THEIR MAGNETIC PROPERTIES
38Adaptations of transformers or inductances for specific applications or functions
18Rotary transformers
 Appl.No PCT/FR1994/000937 Applicant HISPANO SUIZA Inventor GIRARD, Françis
Device for transmitting variable phase and frequency electric power signals from a stationary unit (1) to a rotary unit (2). The primary winding (4) of a rotary transformer is fed by a fixed frequency electric source and the secondary winding (6) feeds a switching power supply (8), while a digital memory (9) provides a digital signal with the desired characteristics, which, after transformation in a digital/analog convertor (10), is amplified in an amplifier (11).
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