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WO/2014/107207A2 |
An aircraft fuel tank flammability reduction method includes contacting a membrane filter with air feed, permeating oxygen and nitrogen from the air feed through the membrane, and producing filtered air from the filter. The filtered air ...
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WO/2014/105328A1 |
A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels, including a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tan...
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WO/2014/105462A1 |
A system in one embodiment includes a mixing module (330), an oxidation module (360), and a heat exchanger (320, 350). The mixing module (330) is configured to receive and mix a boil-off gas stream from a cryotank (310). The oxidation mo...
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WO/2014/105335A1 |
An aircraft having a turbine engine (500) having a bleed air output line (501), a cryogenic fuel system (502) having a cryogenic fuel tank (504) for storing cryogenic fuel and a supply line (506) operably coupling the tank to the turbine...
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WO/2014/105333A1 |
A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system includi...
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WO/2014/105334A1 |
An electrical power system for an aircraft including a turbine engine (101) coupled to the aircraft (5) and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system (12) ...
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WO/2014/099203A1 |
A cryogenic tank assembly includes a cryogenic tank having an internal volume that is configured to contain liquefied natural gas (LNG). The cryogenic tank includes an inlet and an outlet that are each fluidly connected to the internal v...
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WO/2014/060751A1 |
An aircraft fuel system, comprising: a fuel tank (1), a fuel line (4), and an engine (5), the fuel line (4) includes a first conduit (41) configured to carry fuel from the tank (1) towards the engine (5), and a second conduit (42) config...
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WO/2014/058515A2 |
An aircraft fuel tank flammability reduction method includes feeding pressurized air into an air separation module containing a carbon membrane, the air feed exhibiting a normal pressure of no more than 55 psig and the carbon membrane co...
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WO/2014/053787A1 |
The present invention relates to a tank (100, 12, 11) of liquid (2) designed to withstand the overpressures caused by projectile impact and placed within a structure (4), said tank comprising an overpressure management device, said devic...
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WO/2014/052045A1 |
A removable joint system for connecting a hose or duct and a shrouding tube includes the hose or duct, a plurality of shrouding tubes (40, 30); and a plurality of couplers (10). The shrouding tubes are configured to encase the internal h...
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WO/2014/043789A1 |
An aircraft comprising a hydrogen-containing envelope, a water-collection system for collecting water from the envelope, an electrolyser to convert the water collected using the water-collection system into hydrogen, and a hydrogen- repl...
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WO/2014/033400A1 |
The aim of the invention is to prevent the formation of smoke at least during the restarting of the engines. To this end, the fuel purged during the engine shutdown is trapped and drained during the beginning of the following flight, mak...
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WO/2014/027320A1 |
Embodiments of the present invention provide improved space utilization concepts for aircraft, and particularly to using under floor space created by the envelope designed to house an airstair system. For example, this space may be used ...
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WO/2014/019833A2 |
A valve (100) for connecting an external tank to an aircraft, the valve comprises a valve body (112); and a seal assembly arranged, in use, to resiliently engage a seal surface on an aircraft. The seal assembly comprises a telescopic sea...
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WO/2014/016484A1 |
A device for protecting a front spar structure (12) of a central casing (13) of an aircraft wing and equipment (14) located in said wing. The device comprises a shielding surface (222) extending along the front of a front spar of a centr...
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WO/2014/018250A1 |
A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the...
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WO/2014/009640A1 |
Filling device (100, 200, 300, 400, 500) for fluid tank (10) comprising a filling pipe (102, 402, 502), a first stopper (110, 210, 420, 510) to prevent the overfilling of the tank, and a second stopper (120, 220, 320, 420, 520) for preve...
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WO/2013/186536A1 |
A method of providing apparatus comprising: providing a first store and a first payload on or in the first store, the first store being for mounting to the outside of an aircraft (4); acquiring aerodynamic properties, moments of inertia,...
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WO/2013/164311A1 |
An aircraft fuel tank system comprising at least one fuel tank comprising a number of interconnected bays and a vent arranged to allow the inward venting of atmospheric air, the system being arranged to direct inwardly vented air along a...
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WO/2013/146335A1 |
The objective of the present invention is to provide: a fuel tank that can prevent an increase in weight and can have reduced cost and working time during a production process; a main wing; an aircraft fuselage; an aircraft, and a mobile...
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WO/2013/140156A1 |
An aircraft fuel tank vent opening having a liquid separation nozzle, the liquid separation nozzle and the opening dimensioned such that migration across the liquid separation nozzle to the underside of a wing, of fuel escaping from the ...
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WO/2013/140152A1 |
A method of conditioning oxygen depleted air (ODA) exhausted from a fuel cell comprising the steps of; taking fuel from an aircraft fuel tank collector cell, delivering said fuel to a rear mounted engine via a primary heat exchanger, tak...
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WO/2013/135232A1 |
The invention relates to a device (10) for monitoring the concentration of oxygen in an aircraft fuel tank (16) containing inert gas, having an ionisation chamber (12) that is in communication with the fuel tank (16) and through which an...
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WO/2013/135981A1 |
The invention relates to an inerting device for a pressurized aircraft fuel tank, i.e. for a tank provided with a main vessel (2) and a separate overflow space (3), the device including a generator (1) of nitrogen-enriched gas, a circuit...
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WO/2013/103436A2 |
A method and apparatus comprising a first composite layer and a second composite layer in which the second composite layer is associated with the first composite layer. The first composite layer and the second composite layer form a stru...
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WO/2013/099110A1 |
The purpose of the present invention is to prevent blocking of an opening part of a vent member so that ventilation is carried out reliably. A plurality of opening parts (40A, 40B) are formed in a single vent stringer (20), and when one ...
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WO/2013/079454A1 |
An on board inert gas generation system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed air or ram air and passes it to a positive displacement compressor (40) to increase the pressure...
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WO/2013/079466A2 |
An on board inert gas generation system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed air or ram air and passes it to a positive displacement compressor (20) to increase the pressure...
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WO/2013/056626A1 |
Disclosed is a tool for aircraft fuel oil precipitate discharge, which is used within an aircraft wing rectifier hump for opening an aircraft fuel oil precipitate discharge valve to discharge precipitate in a fuel tank. The tool for airc...
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WO/2013/056625A1 |
Disclosed is a telescopic tool for fuel oil precipitate discharge, comprising an initiating apparatus, a collecting bowl (3), a telescopic rod and a locking device (10) and a sheet iron bucket with a magnetic base (12). Use of the telesc...
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WO/2013/058929A1 |
A mounting system for tubular structures within a wing structure provides for positioning of the tubular structure as it passes through wing ribs. The system provides for electrostatic protection from discharges between the rib and the t...
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WO/2013/025133A1 |
The invention aims at pressurising a volume (2) that needs to have a relative air pressure, in comparison with an ambient pressure, where the ambient air pressure can change rapidly and with large amplitude and where the access to pressu...
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WO/2012/177352A1 |
Described herein is a novel method and apparatus for preventing spark propagation from a hydraulic joint (110) to a surrounding medium, such as a fuel source. The hydraulic joint (110) includes a fitting (112) and a tube (114, 116). A ti...
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WO/2012/177334A1 |
A rigid coupler (300) for use in electrically isolating an electrically conductive fluid conveyance system is described. The rigid coupler (300) includes a nonconductive liner (306) having a first end configured to couple to a first adjo...
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WO/2012/173651A1 |
An aircraft engine fuel system 900 is disclosed having a gas turbine engine 101, a turbocharger 910, a compressor bleed air system 930 for providing compressor air (A) from the gas turbine engine 101 to the turbocharger 910, and a fuel d...
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WO/2012/173594A1 |
A system and method to mitigate the effect of hydrodynamic ram. The system including a chamber adapted to receive fluid and a core disposed within the chamber. A plurality of columns extend through the core and a plurality of orifices ex...
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WO/2012/170956A1 |
A hollow fiber fluid separation device lOOg includes a hollow fiber cartridge 11, comprising a plurality of hollow fiber membranes arranged around a central tubular core 15, a first tubesheet 17a and a second tubesheet 17b encapsulating ...
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WO/2012/170933A1 |
A hollow fiber device (11) includes a hollow fiber bundle (13), comprising a plurality of hollow fibers, a first tubesheet (17a) and a second tubesheet (17b) encapsulating respective distal ends of the hollow fiber bundle. The tubesheets...
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WO/2012/149292A2 |
An apparatus for facilitating fluid bladder removal from a support structure through an access opening includes a frame defining a central opening dimensioned to conform to the access opening, the frame having opposed first and second su...
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WO/2012/103875A1 |
What is specified is a double-wall pipe for a transportation means which comprises an outer pipe (102) and an inner pipe (101) extending therein. The outer pipe (102) has two pipe segments (103, 104) which are formed like half-shells and...
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WO/2012/101439A1 |
Embodiments of the invention relate to a stringer (108) adapted to transport fluid in an aircraft wing (100). For example, the stringer may be adapted to provide venting to one or more fuel tanks (111) in the aircraft wing, or may be ada...
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WO/2012/082278A1 |
An electrically conductive structural connection employs a feedthrough or fastener (10) having a first diameter. A fastener hole (18), with a second diameter larger than the diameter of the feedthrough (10), extends through a thickness o...
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WO/2012/076373A2 |
An on board inert gas generation system receives cabin air, or air from another relatively low pressure source, passing a portion thereof through an energy recovery turbine (12) to ambient to extract power which is used to provide all, o...
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WO/2012/074639A1 |
A method, apparatus, and composite fuel tank for manufacturing a structure is provided. A first composite layer ( 318 ) and a second composite layer ( 320 ) are placed on a mold. The second composite layer and the first composite layer a...
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WO/2012/057039A1 |
A pipe support structure for an aircraft is provided with: a translation mechanism for supporting a pipe so that the pipe can be translated; and an angle adjustment mechanism for supporting the pipe so that the angle thereof can be adjus...
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WO/2012/056076A1 |
The invention relates to filler panels for aircraft fuel tank coveringings. The filler panels (45) cover the gaps between the upper and lower coverings (19, 21), stiffened by stringers (25, 25', 25"), of an airfoil of an aircraft structu...
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WO/2012/045031A1 |
An aircraft system (5) is disclosed including: a fuel storage system (10) comprising a first fuel tank (21) capable of storing a first fuel (11) and a second fuel tank (22) capable of storing a second fuel (12); a fuel cell system (400) ...
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WO/2012/013957A1 |
The invention provides a refuel control system for controlling refuel of at least one tank (111,112,113, 14,115,116) onanaircraft100,the refuel control system comprising monitoring apparatus (241, 242, 280, 371, 372, 380, 311, 312, 313, ...
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WO/2012/013351A1 |
To save weight und to enhance safety, a hydrogen tank 18 for supplying an engine 12 with hydrogen is attached externally to an aircraft 10.
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