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WO/2009/133218A1 |
The invention relates to a system comprising two independent pneumatic compressors (CAC) (2) with an electric power supply, connected to an independent CAC controller (5), and an auxiliary power unit (APU) (3) with dimensions such as to ...
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WO/2009/132846A2 |
The invention relates to an aircraft which comprises: a fuselage having a fuselage part (1), a power supply device (E), and at least two receiving devices (A) on the fuselage part (1) for fastening the power supply device (E). The invent...
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WO/2009/095218A1 |
Disclosed is an aircraft fuel cell system (10) comprising a fuel cell (12a, 12b, 12c, 12d) that has an oxidant inlet (14a, 14b, 14c, 14d) for supplying an oxygen-containing medium into the fuel cell (12a, 12b, 12c, 12d). An oxidant suppl...
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WO/2009/083066A1 |
The invention relates to a device (22) for mechanically decoupled mounting of components having hot gas flowing through the same in an aircraft, having a coupling component (42) for coupling to a component emitting hot gas and a componen...
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WO/2009/083073A2 |
A fuel cell system module (10) for use in an aircraft (32) comprises at least one fuel cell system component (12, 22, 24). The fuel cell system module (10) can be connected in a modular manner to a fuselage section (30) of the aircraft (...
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WO/2009/054926A2 |
The present invention broadly comprises an aircraft motion control auxiliary- power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric...
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WO/2009/046805A1 |
In order to relieve the strain on the on-board power supply system of commercial planes from a substantial consumer, namely the galley with its heating and cooling units, the planes are provided with an autonomous, easy-to-handle power s...
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WO/2009/043775A2 |
A fuel cell system for an aircraft is specified which has a fuel cell unit and a suction module. The suction module is used for the intake of oxygen and/or of oxygen-containing air through the fuel cell unit. Vacuum generators are not ne...
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WO/2009/030836A2 |
The invention relates to a device (9) for controlling the maintenance actuators (7a, 7b) of the cowlings of a turbojet engine nacelle of an aircraft, that comprises a first stage (12) to be connected to an electric power network (10) of ...
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WO/2008/146110A1 |
The present invention relates to an aircraft service pit (10) accommodating a GPU (12) for supply of electrical power to an aircraft (2) on the ground. More specifically it relates to a pit with a GPU comprising a housing enclosing a fre...
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WO/2008/132401A2 |
The invention relates to a device for balancing power generators, comprising a plurality of converters each including an elementary conversion cell with a switch (2) driven by a comparator (3) that receives a ramp on one input thereof an...
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WO/2008/132375A1 |
According to the invention, in order to generate an efficient aerodynamic braking force independently from the speed of a vehicle such as an aircraft moving in the air, the method comprises a step of generating energy using the vehicle, ...
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WO/2008/069844A2 |
Thermally compliant auxiliary power unit (APU) (120) ducts arrangements (130), and associated systems and methods are disclosed. A system in accordance with one embodiment includes an auxiliary power unit exhaust (123), that in turn incl...
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WO/2008/049886A1 |
The invention relates to a system for generating, converting, distributing and electrically starting on board an aircraft of the “bleedless” type, that is to say with an electrical power architecture and no pneumatic network, charact...
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WO/2008/033132A2 |
A modular prefabricated deck system which includes a plurality of rectangular flooring modules. Each module may include a plurality of laminations, such as a decorative upper element, and a lower support element for supporting the module...
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WO/2008/001006A1 |
A fuel cell (10) has a compressed air inlet for compressed air supplied by a compressor (20) and a fuel inlet, and produces continuous electrical power. A turbine (30) receives a flow of gas under pressure from the fuel cell and is mecha...
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WO/2007/128637A1 |
The invention relates to an electricity distribution system and method inside an aircraft. This system comprises at least two electrical electricity distribution systems (10, 11) from at least one power source (14-16) to current loads (1...
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WO/2007/115882A1 |
The invention concerns a device and a method for standby power supply on board an aircraft, capable of powering the aircraft "essential" electrical system. Said device comprises a separately energized synchronous machine (MSI) associated...
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WO2007085422B1 |
The invention relates to an emergency supply unit (1) with a ram-air turbine (2) which can be driven by an air stream (14) and with an energy converter (4) for at least partly maintaining the functioning of a hydraulic system and/or elec...
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WO/2007/108787A2 |
A pre-hung air inlet door assembly comprises an inlet door (41), a door box frame (42), and an actuation system(43). The door box frame is fastened to the support structure of an aircraft. The inlet door is operationally connected to the...
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WO/2007/093319A1 |
The invention relates to a system utilizing synergetic potentials of different systems, e.g. of a fuel cell system and of an aircraft hydraulic system, through coupling them via a common cooling circuit system (4).
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WO/2007/064388A1 |
A mount system for an auxiliary component includes two side brackets (42, 44) and a top bracket (46) for rigidly attaching an auxiliary component (32) to an engine casing (22). Each side bracket (42, 44) defines mount segment (50, 52), a...
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WO/2007/053932A1 |
The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine (10), the engine (10) having an electrical motor (30) in a torque-driving engagement with a low pressure spool of the engine (10). The l...
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WO/2007/039211A1 |
An energy supply system 100 for an aircraft comprises at least one fuel cell 101 and at least one energy storage device 103, wherein the fuel cell 101, of which there is at least one, is coupled to the energy storage device 103, of which...
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WO2006015857A9 |
A system comprises an H2/O2 steam generator (2) for generating superheated steam which is either fed directly to a gas turbine (8) to bring it to a rotary speed that is sufficient to result in a compressed-air ratio in the gas turbine th...
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WO/2007/001366A2 |
Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power ...
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WO/2006/137908A2 |
A mechanical flight control system for a rotary-wing aircraft is disclosed. The flight control system comprises an upstream portion (113), a downstream portion (1 15) and a booster means (117) for connecting the upstream portion (113) to...
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WO/2006/115657A2 |
Combined aircraft hybrid fuel cell auxiliary power unit and environmental control system and methods are disclosed, hi one embodiment, an auxiliary power unit includes a fuel cell component which chemically converts combustible fuel into...
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WO/2006/100094A1 |
Modern aircraft carry larger quantities of water. One exemplary embodiment of this invention describes a supply system that encompasses a vapor generator (109) The vapor generator is supplied with hydrogen (104) and oxygen (101-103), and...
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WO/2006/094743A1 |
In contemporary aircraft, ram air turbines are used to provide emergency power given a failure of the engines or hydraulic systems. The ram air turbine system is mechanically complex in light of the out-folding mechanism and rotating com...
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WO/2006/087379A1 |
The invention concerns an electric supply for an aircraft gas turbine engine equipment comprising a first bus (24) for distributing a direct or alternating voltage to first electrical equipment items of the engine, a second bus (30) for ...
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WO/2006/087139A1 |
The invention relates to a system for producing electric power for a land, water or air vehicle (10) comprising an energy converter (20) for converting an airflow energy into a kinetic energy and an electric machine (26) for converting t...
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WO/2006/081037A2 |
A hinging bellmouth (40) for an exhaust duct of an auxiliary power unit (APU) comprises a fixed nozzle portion (41), a motive nozzle portion (42) of substantially the same geometry, a revolute joint interface (43) comprising at least two...
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WO/2006/069434A1 |
An emergency electrical power generating apparatus (50) for use with a turbofan engine comprises an electrical generator (52) and a clutch assembly (54). The clutch assembly (54) connects the electrical generator (52) with a fan assembly...
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WO/2006/058774A2 |
A supply system (100) for the energy supply in an aircraft comprising an engine (101) for propelling an aircraft, a fuel cell (102) for supplying an aircraft with electric energy, a first fuel reservoir (103) for supplying the engine (10...
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WO/2006/034461A1 |
Methods and apparatus are provided for an exhaust duct (200) having an externally replaceable acoustic liner (208). The exhaust duct (200) includes a forward section (202) that is configured to be axially coupled with a bulkhead collar (...
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WO/2006/034460A1 |
The present invention provides a method for replacing an acoustic liner (210) through the forward end or aft end of an integrated exhaust duct muffler (“IEDM”) (200). The IEDM includes a bellmouth (202) coupled to a forward end of th...
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WO/2006/029058A1 |
Integrated axially varying engine mufflers, and associated methods and systems are disclosed. An arrangement in accordance with one embodiment of the invention includes a tailcone (120) having a tapering external surface (121), a cavity ...
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WO/2005/113335A1 |
The invention pertains to a suction arrangement for drawing off boundary layers on an aircraft with a structure, the outer skin of which contains suction surfaces in critical flow areas, and with at least one air breathing engine. Bleed ...
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WO/2005/113334A1 |
An aircraft with a fluid-duct system for extraction of the laminar layer and/or blowing out of fluid at vulnerable places of the outer skin, wherein the fluid-duct system (26, 19, 18) by means of switchable valves (6, 4) is connectable t...
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WO/2005/098218A1 |
A gearbox (30, 130) for rotating a propeller in a selected one of a first or second direction provided. The second direction being opposite with respect to the first direction. The gearbox includes common gas turbine gear components sele...
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WO/2005/042342A2 |
Method and systems for starting propeller driven aircraft and other devices. A system in accordance with one embodiment of the invention includes a removable fixture (130) that is coupled to the propeller (120) and has at least one porti...
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WO/2005/016748A2 |
An inlet door assembly and method for reducing noise from an auxiliary power unit (APU) (10) contained within an aircraft housing (12) is provided. The inlet assembly includes an inlet duct (21), an actuator (46) and a door (44). The inl...
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WO/2004/074096A1 |
A fire protection apparatus (90, 92) for an oil cooler (26) in an aircraft auxiliary power unit compartment (10) adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oi...
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WO/2004/065215A1 |
A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control syst...
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WO/2004/037641A2 |
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture (300) for providing power to an environmental control system (340a, 340b) includes an electric generator (316a, 316...
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WO/2003/053782A1 |
A ram air turbine power system (10) includes a ram air turbine (18) having a turbine shaft (22), turbine blades for rotating the turbine shaft; and an electrical generator or other power source device driven by a power shaft (28), for pr...
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WO/2003/037715A1 |
A passive cooling system for an auxiliary power unit (APU) installation (10) on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion (36) of a gas turbine engine (12) and an oil cooler (...
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WO2002040347A9 |
A system for supporting an auxiliary power unit (30) in an aircraft tailcone (20) wherein the auxiliary power unit is supported by a focalized suspension system (40a-40d) supporting the power unit, the focalized suspension system having ...
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WO/2002/098736A1 |
A ram air turbine system (10) provides liquid cooling of its generator (14) by employing a closed loop liquid cooling line originating from a pump (20) in the gearbox (16) of the system. In the preferred embodiment the pump may be a pito...
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