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Matches 1 - 50 out of 1,083

Document Document Title
WO/2015/057544A1
A compressor impeller for an Auxiliary Power Unit (APU) includes a hub including a plurality of splitter blades interposed between a plurality of main blades. Each of the plurality of splitter blades and the plurality of main blades incl...  
WO/2015/050652A1
An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveyi...  
WO/2015/047539A1
A mounting system for a gas turbine engine includes a compressor case portion, an inlet frame, an outlet frame, and a mounting structure. The compressor case portion houses rotatable compressor blades. The inlet frame connects to an inle...  
WO/2015/039378A1
A self-powered electric aircraft of the present invention is an electric aircraft provided with autonomous electricity generation and autonomous electricity storage and having continuous and uninterrupted motive power, characterized in t...  
WO/2015/033040A1
Case structure interposed between the engine and the nacelle of an aircraft, comprising: a shell ring surrounding the engine and comprising a plurality of sectors (12A, 12B), at least one radial arm (14) for connecting to the nacelle, a ...  
WO/2015/033041A1
Case structure of an aircraft, comprising: a shell ring surrounding the engine and comprising a plurality of sectors (12A, 12B), a number of radial arms (14), each mounted between two adjacent shell ring sectors and each having a base (1...  
WO/2015/033042A1
Case structure interposed between the engine and the nacelle of an aircraft, comprising: a shell ring surrounding the engine having an engine axis and comprising a fixed part (30) and a plurality of sectors (12A, 12B), at least one radia...  
WO/2015/028747A1
The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said co...  
WO/2015/022711A1
The proposed convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft comprises : - a variable incidence front wing of variable span located below the fuselage and m...  
WO/2015/019015A3
The invention concerns an electricity distribution circuit intended to supply at least two loads (CH1, CH2, CH3) from two sources (S1, S2), comprising conductors (F1 to F11), some of which (F3, F4, F5, F1, F2) form outputs capable of bei...  
WO/2015/015122A1
A method for producing a woven preform for a beam made from composite materials provided with transverse inner reinforcements. A method for producing a woven preform designed to be impregnated, in order to form a beam (2) representing an...  
WO/2015/015262A1
A method for installing a pre-assembled powerplant and pylon assembly on an aircraft comprises determining a first length of a first link, determining a second length of a second link, determining a first distance occupyable by the first...  
WO/2015/010315A1
An aircraft engine pylon comprises an upper fitting, an upper panel located below the upper fitting, a shear pin at least partially coupling the upper fitting to the upper panel, and many tension fasteners at least partially coupling the...  
WO/2015/003261A1
A curved body (830), for propelling fluids, crafts and harvesting fluid power, comprises a convex outer leading surface securely connected to a concave inner trailing surface to define an open vessel. Upon oscillation, ambient fluids are...  
WO/2015/004059A1
The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one ...  
WO/2014/204549A3
Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a method to harvest renewable energy includes providing an aircraft suitable for untethered flight in an open airspace and an airborne kinetic en...  
WO/2014/203593A1
The present invention addresses the problem of providing an unmanned flight vehicle capable of stably flying for a long time even when an expert operator is not present. As a means of solving this problem, the present invention first cap...  
WO/2014/202842A1
- An aircraft capable of passing from the aerial domain to the spatial domain and method for automatically adapting the configuration of same. - The invention involves providing, on said aircraft, an additional breathable gas supply (25)...  
WO/2014/204549A2
Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a method to harvest renewable energy includes providing an aircraft suitable for untethered flight in an open airspace and an airborne kinetic en...  
WO/2014/198923A1
The invention relates to an electric propulsion assembly for an aircraft, including a nacelle (10) comprising a nacelle cover (10) which defines an inner space in which an electric propulsion unit, which includes a blower (13), of the ai...  
WO/2014/195657A1
Connecting rod designed to be positioned in an aircraft engine flow (F), comprising a profiled longitudinal tubular bar (2) which at each end has fixing means (8), characterized in that it comprises a main part (4) comprising a longitudi...  
WO/2014/195246A1
The present invention relates to an electrical power supply device (25) for electric propulsion aircraft comprising a first and a second electric motor (20, 21) which are able to ensure the propulsion of the aircraft, a first and a secon...  
WO/2014/189588A2
An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be...  
WO/2014/189588A3
An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be...  
WO/2014/184497A1
The invention relates to a hot gas exhaust nozzle for an aircraft turbojet, provided such as to be placed in a pod supported by a pylon including a fairing (8) placed near the outer surface of said nozzle (12). The space between said fai...  
WO/2014/185998A2
A propulsion system for a supersonic aircraft includes an engine, a compression surface upstream of the engine, a shroud surrounding the engine configured to direct airflow passing over the compression surface towards the engine, and a p...  
WO/2014/183230A1
The present invention relates to an electromagnetic air fluid pressure reduction and propulsion apparatus, which is characterized in that it comprises a lift force bottom plate, a pair of electrodes, a magnet, more than two laser sources...  
WO/2014/174222A1
The invention relates to a structure for suspending a twin prop-fan engine (10) from a structural element of an aircraft, comprising a cradle (18) intended to be fixed to a structural element of the aircraft and having two lateral beams ...  
WO/2014/175934A3
An auxiliary power unit bracket, according to an exemplary aspect of the present disclosure includes, among other things, a gearbox mounting face and a compartment mounting face, the gearbox mounting face configured to attach to an auxil...  
WO/2014/164586A1
A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbin...  
WO/2014/165502A1
Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a wind-powered aircraft (100) includes an airframe (110, 120, 130) suitable for untethered flight in an open airspace; and an airborne kinetic en...  
WO/2014/163688A1
An aircraft power plant is disclosed having a plurality of bladed rotors (64) in flow communication driven by separate work producing devices (70, 72). The work producing devices (70, 72) can take a variety of forms including an internal...  
WO/2014/158247A1
A flight vehicle (10) includes a fuselage (12) and a gas turbine engine (14). The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted...  
WO/2014/154980A1
Ball-jointed device (10) for suspending a turbomachine from a pylon or for suspending equipment from the body of a turbomachine, comprising a link rod (12) of which one end bears a ball (14) and which is interposed between the two flange...  
WO/2014/149101A3
An aircraft 1 is provided with a gas turbine engine 20 having a plurality of shafts. A first output shaft 32 provides power to an electrical machine 40 and a propeller 50, while a second output shaft 33 provides power to a refrigerant co...  
WO/2014/143334A3
One embodiment of the present disclosure is a unique system. Another embodiment is a unique fastener system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, a...  
WO/2014/143451A1
A multi-member assembly including a first structural member (18), a second structural member (16) opposed from the first structural member, a crossover seal (28) positioned between the first and second structural members, wherein the cro...  
WO/2014/135431A1
A propulsion nacelle (1) for an airplane has a housing (2) in which an electric machine (3), a converter unit (4), and a control device (5) are arranged. The electric machine (3) is supplied energy via the converter unit (4). The propuls...  
WO/2014/131914A1
As described in the title, the invention relates to an electric power system that performs the functions of auxiliary engine, internal combustion engine starter and generating system for the electrical power supply of an aircraft. The ma...  
WO/2014/128397A1
Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on ...  
WO/2014/121632A1
Disclosed is a front installation node integrated with an aircraft pylon. The front installation node is suitable for integral forming with a front end frame (100) of an aircraft pylon and comprises: a first lug (10) and a second lug (20...  
WO/2014/111654A1
The invention concerns a suspension structure (100) with variable geometry of a turboprop engine (4) on a structural element of an aircraft, comprising a rear cradle (102) intended to be attached to a structural element of an aircraft an...  
WO/2014/108125A1
The invention relates to an aircraft, wherein at least one rotatably mounted, bladed rotor (R) for generating propulsion surrounds a fuselage arrangement (F)and is arranged relative to the components of the aircraft in a defined manner a...  
WO/2014/109811A3
A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fa...  
WO/2014/096144A1
The subject of the invention is a system for recharging the batteries (6) carried on board an electrically powered aircraft (10), characterized in that it comprises a charging aircraft (1), means (2, 3a, 3b, 4) of temporarily electricall...  
WO/2014/092750A1
A gas turbine engine comprises an outer nacelle. A nose cone is spaced radially inward of the outer nacelle. The nose cone defines a particle separator for directing an outer air flow and an inner airflow. The inner airflow is directed t...  
WO/2014/083556A9  
WO/2014/083556A2
A method for creating a barrier blade of a conventional wind turbine, or a fixed wing of an aircraft (22), (23), to intercept the winds of spacetime, to power their movements. Layers of originally reflected foci of beta, or X-Rays are cr...  
WO/2014/076403A1
The invention concerns an aircraft comprising a fuselage (30) extending along a main longitudinal axis (AA), two wings (10, 20) positioned on either side of the fuselage, two propulsion units (11, 21), each fixed respectively to one wing...  
WO/2014/075609A1
Methods and apparatus for unmanned aerial vehicle (UAV) with improved reliability are provided, wherein onboard sensors are located on said UAV at a position separated from onboard electrical components. Therefore, interference experienc...  

Matches 1 - 50 out of 1,083