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Matches 1 - 50 out of 1,011

Document Document Title
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/2014/143451A1
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/2014/083556A2
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...  
WO/2014/078006A1
An aircraft includes a tail extending from a fuselage. The tail defines a structural box having first and second vertical stabilizers that support a horizontal stabilizer. The tail includes at least one sacrificial control surface and at...  
WO/2014/072615A1
The invention relates to an aircraft propelled by a turbojet engine (10) with contrarotating fans, the turbojet engine being incorporated into the rear of a fuselage (2) of the aircraft in the continuation thereof and comprising two gas ...  
WO/2014/074145A1
A propulsion system for an aircraft includes first and second turbine engines mounted within a fuselage of the aircraft. The first turbine engine includes a first engine core that drives a first propulsor disposed about a first propulsor...  
WO/2014/074146A1
An aircraft including a fuselage having a forward portion and an aft portion with a propulsion system mounted within the aft portion of the fuselage. A burst zone is defined that extends outward from the propulsion system. The aircraft i...  
WO/2014/067506A1
The invention relates to an unmanned aircraft (10), the drive (12) of which comprises an internal combustion engine (28) designed as a diesel and/or kerosene engine and having a charging device (30) for charging the engine. In particular...  
WO/2014/062220A1
A turbofan engine structural guide vane is mounted to a forward bulkhead of a core engine case structure at an inner end and to a fan case at an outer end. A plurality of shear pins extend from the aft portion of the structural guide van...  
WO/2014/058463A1
A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid comm...  
WO/2014/053057A1
An aerial vehicle includes at least one wing, a plurality of thrust producing elements on the at least one wing, a plurality of electric motors equal to the number of thrust producing elements for individually driving each of the thrust ...  
WO/2014/055103A1
A gas turbine includes a mounting structure for mounting the engine to a pylon. A propulsor section includes a fan having a fan diameter. A geared architecture drives the fan. A generator section includes a fan drive turbine that drives ...  
WO/2014/051669A1
A turbine engine system mounted on an aircraft wing includes a gas turbine engine having a spool, a turbine coupled with the spool, a fan coupled to be rotated about an axis through the spool, and a gear assembly coupled between the fan ...  
WO/2014/052857A1
An assembly for mounting a turbine engine case to a pylon. The assembly includes a beam and a shackle. The shackle includes a plurality of side segments, and an intermediate segment that is engaged rotatably to the beam. Each of the side...  
WO/2014/042774A3
A waiting link to support an engine on an aircraft includes a body portion including a first body portion opening, a second body portion opening, and a space therebetween. A first bearing is received in the first body portion opening and...  
WO/2014/041310A1
The invention relates to a system for pylon attachment system (31) for mounting an engine (10) on the structure of an aircraft, in particular to the wings, comprising a first attachment means (31) which can be secured to the pylon and a ...  
WO/2014/036818A1
An electrodynamic dish-shaped flying generator comprises a body, a power plant, and a control system. The power plant includes a plurality of annular ferromagnetic guide rails for generating magnetic levitation, a plurality of rising for...  
WO/2014/036328A1
A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. A...  
WO/2014/021966A2
A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly com...  
WO/2014/021966A3
A forward engine mount assembly for a gas turbine engine includes a mount beam having a main body with a fore end and an aft end and a forward shackle assembly supported by the fore end of the mount beam. The forward shackle assembly com...  
WO/2014/021798A3
The invention relates to a system providing vertical take off and landing for military aircrafts or civilian airplanes, unmanned aerial vehicles and so on. The rotating fans working with electric motor taking electricity from the very po...  
WO/2014/021742A3
The group of inventions relates to aerospace engineering, and more particularly to hypersonic aircraft and methods for flying in the upper atmosphere at hypersonic velocities. For travel in the atmosphere (or close to the boundary thereo...  
WO/2014/013270A1
A method of flying an unmanned aerial vehicle (50) at an elevated altitude comprising at least two wings (53) comprising solar-energy collectors (not shown), the method involving flying the vehicle (50) for an extended period of time wit...  
WO/2013/186003A3
The invention relates to a method for providing predefined desired drive characteristics (38, 50) in an aircraft, characterized by the following steps: - driving a thrust generation element of the aircraft by means of an electric motor t...  
WO/2013/186003A2
The invention relates to a method for providing predefined desired drive characteristics (38, 50) in an aircraft, characterized by the following steps: - driving a thrust generation element of the aircraft by means of an electric motor t...  
WO/2013/186009A1
The invention relates to a hybrid aircraft (F). According to the invention, a suitable position for mounting an energy generation unit (14) in the aircraft is identified, said energy generation unit comprising an internal combustion engi...  
WO/2013/181722A3
The Road-and-air transport vehicle is intended to transport people (from 1 to 4 people] on the roads, as a light passenger vehicle, and in the air - as a small aircraft. It has a body (1] with a cabin (13), 4 wheels: 2 front wheels, cont...  
WO/2013/178776A1
The invention relates to an aircraft (1), preferably an unmanned aircraft (UAV), drone, or unmanned aerial system (UAS), comprising a rigid wing (2), which enables aerodynamic horizontal flight, and at least four rotors (4, 4'), which ar...  
WO/2013/162128A1
The present invention relates to a cable connection unmanned aerial vehicle system, wherein electricity required for the thrust motor of an unmanned aerial vehicle and the electronic equipment loaded thereto is supplied from the ground s...  
WO/2013/160390A2
The present invention relates to a device 10 for cabin pressure difference warning for an aircraft or spacecraft 1, comprising a cabin pressure difference sensor means 12 for detecting the current cabin pressure difference ΔΡ, a contac...  
WO/2013/162666A1
A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associ...  
WO/2013/138217A1
A gas turbine engine has a spool, a towershaft connected to the spool, an impeller pump, and a speed control pump connected to the towershaft and to the impeller pump for driving the impeller pump at a constant speed.  
WO/2013/138215A1
An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging ai into a discharge manifold. The discharge manifold containin at le...  
WO/2013/133831A1
A mounting assembly (50) allows components (48) to be mounted on a beam (38) having a rectangularly shaped cross section and flat sides (64). The mounting assembly (50) includes a plurality of adapter members (52-58) and a strap (70). Ea...  
WO/2013/128123A1
According to the invention, the method for holding an adapter piece (19) on a tubular housing (5) of a turbo engine (1), said piece (19) being intended to at least partially cover said housing (5), is characterised in that the following ...  

Matches 1 - 50 out of 1,011