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JP4635012B2 |
An air guiding flap of an aircraft wherein one surface thereof faces an air duct and is exposed to a prevailing pressure in the air duct and whose opposite surface is exposed to the pressure of the relative wind flowing past the aircraft...
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JP2011502878A |
A process for management of thermal effluents of an aircraft that includes an airframe (110) and at least one propulsion system (112), whereby the at least one propulsion system (112) includes a gas turbine engine (116) that is supplied ...
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JP4619089B2 |
An aircraft propulsion system (25) includes a gas turbine engine having a fan section (115), at least one row of FLADE fan blades (5) disposed radially outwardly of and drivingly connected to the fan section (115), the row of FLADE fan b...
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JP4614972B2 |
A ram air channel (10) for the supply of ambient air in an aircraft includes a first air inlet (12) and a main flow channel (16) which extends downstream of the first air inlet (12). In order to guarantee that the systems on board the ai...
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JP4602753B2 |
A basesheet (52) for use in an aircraft gas turbine engine exhaust nozzle includes a plurality of basesheet segments (80) extending between longitudinally extending spaced apart basesheet leading and trailing edges (56 and 58), respectiv...
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JP2010281277A |
To provide an FOD preventing device capable of appropriately preventing a foreign object, such as, birds from entering an engine.An FOD preventing device 1 is equipped with a filter 6 arranged on a front side of the engine 3; an intake a...
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JP2010538888A |
A hydraulic drive for an aircraft includes: a gear, a first hydraulic pump and a second hydraulic pump, wherein the gear is installed in a gear housing and wherein the first hydraulic pump and the second hydraulic pump in each case are i...
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JP4589394B2 |
An airframe (1a) having a main body (4) and a tail body, a main rotor (6) disposed above the main body (4) and driven by an engine inside the airframe (1a), and a tail rotor disposed in a rear part of the tail body (5) are provided. A pa...
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JP4574841B2 |
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JP2010203290A |
To provide a device for enabling an aircraft with respect for human life, by preventing engine breakage or stop due to bird strike by providing safety and ease to the aviation industry, since there is no end of an engine stop due to the ...
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JP4546770B2 |
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JP4540282B2 |
A supersonic external-compression inlet comprises a generally scoop-shaped supersonic compression section for diffusing a supersonic free stream flow. The supersonic compression section includes a main wall having a leading edge and a th...
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JP4531926B2 |
An exhaust nozzle (20) includes cascade vanes (24) mounted in a duct (22) for discharging exhaust. The vanes have a dolphin profile which is effective for turning subsonically the exhaust near leading edges (32) of the vanes, and then di...
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JP4516022B2 |
An aircraft fluid cooling system has an air heat exchanger passed by this fluid, the air heat exchanger including a structure for introduction of air and an air exhaust. The air heat exchanger is installed in a housing located in a flap ...
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JP4475956B2 |
A vertical take off and land (VTOL) jet aircraft may have a jet engine mounted in a forward portion of the aircraft. A thrust deflection assembly may be provided rearward of the jet engine, and include a cascade and control box for defle...
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JP2010519445A |
A process for the producing a coating for acoustic treatment relative to a leading edge such as an air intake of an aircraft nacelle, the coating including a reflective layer, an alveolar structure, and an acoustically resistive layer, i...
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JP2010517845A |
The nacelle has a thrust reversal device comprising a flap (34), and a wall for determining a conduit (16) in which flow passes to deviate. A movable part (30) is interposed between the flow with deviation and the flap in one position, a...
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JP2008510913T5 |
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JP2010510120A |
An aircraft leading edge, such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, includes a coating (26) for the acoustic treatment that includes—from the outside to the inside—an acoustically resistive poro...
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JP2009541659A |
The object of the invention is a process whose purpose is to reduce, cancel or reverse the thrust generated by at least one air flow exiting from a propulsion unit of an aircraft by deflecting at least a portion of the flow that is able ...
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JP2009539682A |
An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary ex...
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JP2009540195A |
An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary ex...
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JP4349737B2 |
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JP4298677B2 |
Nozzles for discharging high velocity air are positioned on either side of an aircraft engine exhaust duct exit. High velocity air is discharged tangential to an outer surface of each nozzle and follows the contour thereof. The nozzles a...
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JP4300682B2 |
To provide a traveling body with the improved energy efficiency in starting a propulsion engine or in the air-conditioning system in an aircraft. An auxiliary power unit of the aircraft as the traveling body comprises a power source unit...
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JP4293573B2 |
A gas turbine engine exhaust nozzle (10) includes an exhaust duct (16) for channeling a gas jet (12). A plurality of adjoining chevrons (18) are disposed at an aft end of the duct to define an exhaust outlet. Each of the chevrons is tria...
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JP4290883B2 |
An IR Suppressor (20) operative to suppress the infrared signature radiated from the high-temperature exhaust of an engine (12) and comprising a primary exhaust manifold (22), first and second mixing ducts (24a, 24b), and a secondary flo...
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JP2009507179A |
An InfraRed Suppression System (IRSS) vectors engine exhaust flow away from the exhaust manifold plane, the high aspect ratio exhaust duct defined as a ratio of a maximum nozzle length to a maximum nozzle width, the ratio greater than 2:1.
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JP2009500553A |
A pod for an aircraft including a cowling, an engine housed in the inner volume of the cowling, an annular channel circulating a secondary thrust flow arranged between the engine and the cowling, and at least one thrust reverser for form...
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JP4161755B2 |
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JP4159519B2 |
The device (12) has a set of grooves that is provided in the extension of an end of a tailpipe (10) of a turbomachine. A set of indentations is provided between two successive grooves. The set of grooves and indentations are unsymmetrica...
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JP4116984B2 |
The flap has a conical hollow body and a rectilinear generator (11). The body has a thin wall (12) that is divided transversally into a cold wall (14) and a warm wall (13) and two symmetrical lateral walls (15). The thin wall has a conti...
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JP4098946B2 |
Adjustable structure (12) is placed on downstream end of ejection carter (2) using intermediate ring (9). Intermediate ring rotates around first axis relative to ejection carter, and around second axis, perpendicular to first axis, relat...
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JP4101080B2 |
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JP4090977B2 |
The thrust reverser has two doors (10a, 10b) moved between open and close positions by a control jack. An electronic calculator (20) has two paths (20a, 20b) connected to respective electronic control units (18a, 18b). The paths receive ...
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JP2008114838A |
To provide an auxiliary power unit assembly (10) of an embodiment of the technology described in this specification.The auxiliary power unit assembly (10) comprises an auxiliary power unit installable in an aircraft (18) having a cabin (...
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JP4043679B2 |
The thrust reverser for an engine with primary and secondary variable-section nozzles consists of two identical shutters (16, 17) pivoted to the engine housing (11) on either side of its axial plane of symmetry (P1). Each of the shutters...
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JP2008019864A |
To provide a thrust reverser assembly for an aircraft gas turbine engine.The thrust reverser assembly 100 comprises: a plurality of first rotary vanes 180 for allowing increase in lift by channeling air flow from a gas turbine engine 10 ...
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JP4034715B2 |
The reverser has a turntable maintenance (30) that swivels between two positions. A turntable prohibits a hand drive operation in case of a manual operation of a moving part (12) e.g. sliding door while authorizing an electric drive and ...
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JP4015605B2 |
The reverser has sliding doors (10a, 10b) movable between opening and closing positions and controlled by electric motors (14a, 14b) assembled on ordering black boxes (18a, 18b) that are connected to an electronic computer with a full au...
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JP4005552B2 |
The thrust reverser has doors moved between open and closed positions by a control jack (12). A door control unit enables a synchronized placement of the doors based on variation of loads exerted on the reverser and difference in the loa...
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JP3956283B2 |
To provide a lobe mixer for a jet stream in which an internal flow of high speed and an external flow of low speed are sufficiently mixed, a vibration with high stress and displacement hardly occurs, and a long life and a low noise are m...
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JP2007519866A |
An accessory driving apparatus for an aircraft system is connected to an accessory unit to be driven, such as a PCU pump. A gear set for transferring rotational power from the driving shaft to the driven shaft is provided for selective a...
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JP2007168491A |
To provide an intake duct for an airplane which improves stealthiness of the airplane while maintaining the degree of freedom of body development without increasing the disturbance of flow at the inlet port of the engine.The intake duct ...
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JP2007131288A |
To provide an energy-saving type jet place capable of saving energy for the flight by reducing the air resistance on a front face of the jet plane.An air-feed duct extending from a leading end of a fuselage of a jet plane to a part in a ...
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JP2007509270A |
An aircraft engine assembly is provided that is adapted to reduce noise produced by an engine included in the engine assembly. The engine assembly includes a nacelle having an inlet section and a main section that is houses the engine an...
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JP3884482B2 |
A failsafe nozzle actuating system for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle has a vectoring ring operably linked to a plurality of pivotal flaps which are circumferentially disposed about a nozzle centerli...
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JP2006518297A |
A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the eve...
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JP3803326B2 |
To provide an auxiliary power device integrally formed with an engine. In the auxiliary power device integrally formed with an engine, the engine 10 has: a high pressure spool including a high pressure compressor 20 connected to a high p...
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JP3747244B2 |
An air intake (10) includes a spike (11) and a cylindrical cowl (26). The spike is composed of a plurality of plates (22) which are arranged axial symmetrically around a central axis thereof, and the cowl includes an inner wall parallel ...
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