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Matches 101 - 150 out of 1,011

Document Document Title
WO/2015/170091A1
A liquid storage system comprising: a tank (16) for containing a liquid, said tank (16) enclosing a liquid storage space (14); multiple layers of a fabric material (22a-d); and attachment means attaching the multiple layers of the fabric...  
WO/2015/170094A1
Disclosed is a liquid storage system comprising a tank (16) for containing a liquid, said tank (16) enclosing a liquid storage space (14), and a plurality of spaced apart protrusions (18b) extending from an internal surface of the tank (...  
WO/2015/170092A1
Disclosed is a liquid storage system comprising: an outer tank (16) (e.g. an aircraft fuel tank) for containing a liquid (e.g. aircraft fuel), said outer tank (16) enclosing a liquid storage space (14);an inner tank (18a, 18b) located wi...  
WO/2015/170088A1
A liquid storage tank (16), for example an aircraft fuel tank, comprising a tank wall enclosing a liquid storage space (14), and a tie assembly located at least partially within the liquid storage space (14). The tie assembly comprises a...  
WO/2015/170090A1
An aircraft fuel tank(16), comprising: a plurality of tank walls enclosing a liquid storage space (14), the plurality of tank walls including a first tank wall (10) (e.g. an external skin of the aircraft) and a second tank (8) wall (e.g....  
WO/2015/170089A1
A liquid storage system comprising: a tank (16) for containing a liquid, said tank (16) enclosing a liquid storage space (14); and a tank liner (18) fixedly attached to an internal surface of the tank (16). The tank liner (18) comprises:...  
WO/2015/170095A1
BAFFLE Disclosed is a baffle (40) for locating in a tank (16) for containing liquid (e.g. an aircraft fuel tank). The baffle (40) is a tubular member through which a liquid may flow. The baffle (40) comprises: a first tubular portion (42...  
WO/2015/159227A2
An exemplary bulkhead connector assembly may include a housing that has an inner diameter surface, a first opening and a second opening. The assembly may further have a retainer attached to the housing and one or more feet extending radi...  
WO/2015/159228A1
An exemplary bulkhead (104A) connector assembly (100) includes a housing (106) having a first opening (138) and a second opening (130). The assembly (100) may further include a collar (108) that has a portion received within one of the f...  
WO/2015/082913A3
An aircraft fuel system architecture which reduces the fleet-wide flammability exposure of the fuel tanks. In one embodiment, the aircraft center fuel tank fuel is cooled at certain times in a flight to reduce its flammability exposure t...  
WO/2015/145379A1
Embodiments of the present invention relate generally to fuel tanks (100) for aviation, and particularly to construction of rigid tank walls (104) that have been found useful in absorbing energy of a magnitude expected during a crash. In...  
WO/2015/099860A3
A fuel feed system for a rotary-winged aircraft includes a fuel feed line extending from a fuel source to an engine and an engine fuel suction pump disposed at the fuel feed line to urge a flow of fuel through the fuel feed line to the e...  
WO/2015/136138A1
The invention relates to a system for obtaining a continuous image of the environment of an operation such as that of in-flight refuelling, using a camera (8) (or two in the case of a redundant system being required, since the geometry o...  
WO/2015/063400A3
The invention concerns a method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit comprising a fuel tank (10); an engine fuel system (20) connected to the fuel tank, said engine fuel syst...  
WO/2015/063401A3
The invention concerns a method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, said fuel circuit comprising: a fuel tank (10); an engine fuel system (20) connected to the fuel tank (10), said fuel syst...  
WO/2015/116260A1
A method of protecting fuel hardware for a gas turbine engine in an aircraft is disclosed. The method may include determining a current altitude of the aircraft, and controlling a temperature of fuel for the gas turbine engine based at l...  
WO/2015/069345A3
A boost pump unit (110) includes a liquid ring pump (116) and an air/ fuel separator (118) having an inlet (124) and first (126) and second (130) outlet ports. The separator inlet (124) is operably fluidly coupled to an outlet of the liq...  
WO/2015/094903A1
A fuel filter comprises a filter screen, a heating element, and a coating. The filter screen includes a first hollow member. The heating element is disposed within the first hollow member. The coating is formed of a thermally conductive,...  
WO/2015/082913A2
An aircraft fuel system architecture which reduces the fleet-wide flammability exposure of the fuel tanks. In one embodiment, the aircraft center fuel tank fuel is cooled at certain times in a flight to reduce its flammability exposure t...  
WO/2015/082057A1
An aircraft fuel system (100) comprises a fuselage tank (102) and wing fuel tanks (104, 106) each connected to the fuselage fuel tank by a respective fuel line (107, 109). A first fuel line (101) connects the fuselage fuel tank to a coll...  
WO/2015/063401A2
The invention concerns a method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, said fuel circuit comprising: a fuel tank; an engine fuel system connected to the fuel tank, said fuel system comprising a...  
WO/2015/063406A1
The present invention concerns a device for inerting one or a plurality of fuel tanks (3) of an aircraft, such as an aeroplane or a helicopter, for example, or similar, comprising at least one inert gas generator (1) referred to as OBIGG...  
WO/2015/063400A2
The invention concerns a method for detecting a failure in a fuel return valve of an aircraft engine fuel circuit, the fuel circuit comprising a fuel tank; an engine fuel system connected to the fuel tank, said engine fuel system being c...  
WO/2015/059427A1
The present invention relates to a method for inerting a tank (S) of fuel (6) of a moving aircraft and to a related device (1a, 1b, 1c). Said method includes dispensing an inerting gas into said tank (5) while the volume (V) of fuel (6) ...  
WO/2015/048695A1
An aircraft auxiliary fuel tank system comprising a master tank and a plurality of slave tanks connectable to the master tank. The slave tanks can be easily added or removed to adjust fuel capacity. A rail assembly is provided to assist ...  
WO/2015/029805A1
For a left wing engine (5a) and a right wing engine (5b), there are respectively installed two lines of pump units of a first pump unit (7a) and a third pump unit (7c) that supply fuel from a fuselage fuel tank (3a), and a second pump un...  
WO/2015/023870A1
Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequenc...  
WO/2015/015129A1
The invention relates to a fuel circuit of an aircraft engine comprising a fuel tank (10); an engine fuel system (20) comprising a low-pressure pump (21) and a high-pressure pump (22), and a fuel recirculating pipeline (2) connected to t...  
WO/2015/002716A1
A heating body for an electrically heated filter screen includes a heater element having an outer surface and a metallic protective layer having an inner surface. An insulating layer is disposed between the heater element outer surface a...  
WO/2014/209454A1
A hybrid fuel airplane and methods are presented. A cryogenic fuel is transferred to an airplane propulsor from an airplane fuel system comprising a cryogenic fuel tank (302) and a jet fuel tank (310). The cryogenic fuel tank (302) confo...  
WO/2014/208680A1
An unmanned helicopter (10) has a fuel tank (48) for holding fuel that is supplied to a drive source (36). The fuel tank (48) has a main unit (56) and a fuel holding unit (60). The fuel holding unit (60) protrudes obliquely downward to t...  
WO/2014/107207A3
An aircraft fuel tank flammability reduction method includes contacting a membrane filter with air feed (17), permeating oxygen and nitrogen from the air feed through the membrane (22), and producing filtered air (21) from the filter (22...  
WO/2014/124473A3
A system (100, 110) for cooling an (100, 110) includes a fuel tank (160), a fuel delivery system (165), a cooling system (120), and a heat exchanger (135). The fuel tank is configured to hold cooled fuel (155) for the aircraft. The fuel ...  
WO/2014/200582A1
A method and apparatus of using cryogenic fuel (12) in an engine (101) for an aircraft (5) wherein the cryogenic fuel (12) is supplied to the engine for combustion.  
WO/2014/199132A1
An aircraft fuel vent pipe (1) with a pipe body containing a duct (4) which extends along a duct axis (5) between an open end (6) and a closed end. A burst disc (7) closes the closed end of the duct (4). One or more devices (10-12) are p...  
WO/2014/130124A3
A system in one embodiment includes a detection unit (116), a boil- off auxiliary power unit (140), and a controller (190). The detection unit is configured to detect a characteristic of a boil-off gas stream (123) from a cryotank (110) ...  
WO/2014/186881A1
A fuel cell power module is used to provide nitrogen enriched air for, in one application, fuel tank inerting in an aircraft. The fuel cell power module has a recirculation line between its cathode side outlet and cathode side inlet. At ...  
WO/2014/174247A1
A tank assembly with a tank (8) for storing liquid hydrocarbon, the tank (8) having a floor (16) for supporting a weight of the liquid hydrocarbon (18). A filter (20) is fitted to the floor (16) of the tank (8). The filter (20) is arrang...  
WO/2014/139840A1
In a fixed wing aircraft including at least one main fuel tank (14) in the wing and an associated surge tank (16), an aircraft fuel tank inerting system comprises a source (20) of inerting fluid, a flow passage (22) for supplying said in...  
WO/2014/136085A1
A tank wall connector system (10) for use with a composite tank, the connector comprises a connector (20, 22) having a body extending from an interior of the tank to an exterior of the tank when installed through a hole in the composite ...  
WO/2014/133632A2
An in flight refueling probe for an aircraft includes a circular shaped hollow tubular member having a first end attached to the aircraft and a second end extending from the aircraft terminating in an external convex shape with a plurali...  
WO/2014/126655A1
A method and apparatus for electrically separating two fluid lines across a structural boundary. Fluid is transported between a first channel through a first fluid line and a second channel through a second fluid line across the structur...  
WO/2014/124473A2
A system (100, 110) for cooling an (100, 110) includes a fuel tank (160), a fuel delivery system (165), a cooling system (120), and a heat exchanger (135). The fuel tank is configured to hold cooled fuel (155) for the aircraft. The fuel ...  
WO/2014/122124A1
The present invention relates to a device for mounting and supporting a generally cylindrical or tapered tank (100), having a main axis X, that includes: a pair of first means (2a, 2b, 2c, 2d) for retaining the tank along a vertical axis...  
WO/2014/122127A1
The invention concerns a tank retainer (100) for retaining a tank in the fuselage of an aircraft which comprises, between the tank and a frame (12) rigidly connected to the fuselage of the aircraft, a hinged retaining means (4) and a fas...  
WO/2014/108884A1
Embodiments of the present invention provide a lever quick connect and disconnect fitting (10) that provides a secure fit for tank-to-tank connections and prevents any leakage from occurring. The fitting provide two separate, independent...  
WO/2014/027250A9
A fuel supply system for an aircraft (10) for delivering in use fuel from a fuel tank (20) to an aircraft powerplant (12), comprises a fuel flow passage (18) along which in use fuel may flow from said tank (20) to said powerplant (12), t...  
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 ...  
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...  
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...  

Matches 101 - 150 out of 1,011