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Patent Searching and Data


Matches 451 - 500 out of 9,683

Document Document Title
WO/2016/092239A1
A device (44) for controlling an exhaust nozzle (32) with variable cross-section of a turbojet engine (20) nacelle (10) of an aircraft, the device (44) comprising a computer (46) suitable for determining a position setpoint of the nozzle...  
WO/2016/092183A1
The invention relates to the field of technical tests and specifically to a machine testing method including: - at least one step of determining (S101) a plurality of operating points for said machine, each operating point being defined ...  
WO/2016/088776A1
Provided is a ship propulsion apparatus which has few frictional portions in the main driving mechanism and has a simple structure, generates little water pollution or noise, and is easy to handle. This ship propulsion apparatus 10 for g...  
WO/2016/085705A1
A valve assembly includes a housing (22) that has a fluid input (24) and a fluid output (26). A pintle (30) is disposed in the housing, and an actuator (36) is operatively coupled to move the pintle. The pintle includes a passage (32) th...  
WO/2016/012161A4
The present invention relates to a heat exchanger (50) comprising a plurality of plates (10, 20) provided with a planar peripheral area (19, 29), an internal area provided with sinusoidal undulations (13, 23, 14, 24) and two chimneys (11...  
WO/2016/081047A2
A propulsion system for use with a satellite comprises a substrate, a communication network and a cluster of individually selectable solid fuel motors mounted on the substrate and operatively connected to the communication network. A con...  
WO/2016/081070A1
A vehicle propulsion system includes an air heating chamber that receives inlet air from an air intake chamber and provides thrust through an exhaust chamber. A battery powered pulse generator generates a pulsed electrical output signal....  
WO/2016/071242A1
The invention relates to a system for actuating a movable structure of a thrust reverser comprising a first motor (11), a first actuator (21) that is driven by the first motor, a second actuator (22) and a first transmission shaft (31) t...  
WO/2016/073245A1
Aspects of the invention generally provide a heat engine system and a method for activating a turbopump within the heat engine system during a start-up process. The heat engine system utilizes a working fluid circulated within a working ...  
WO/2016/062155A1
An array multi-point set explosion-type pulse detonation engine consists of a plurality of detonation tubes (3), a consolidating detonation chamber (2), an inlet control valve (1), a tail jet (4), a fuel auxiliary mixer (5) and a control...  
WO/2016/062977A1
The invention relates to an assembly of a fixed inner structure (5) of a nacelle (3) of a turbojet (2) and a thermal protection element, said structure (5) comprising an inner face to which the thermal protection element is applied, and ...  
WO/2016/062949A1
The invention relates to a method for starting a spacecraft engine combustion wherein: a propellant tank heater (25) is ignited; a first tank (23), containing the first propellant, and a second tank (24), containing a second propellant, ...  
WO/2016/059332A1
The invention relates to a method comprising the deposition of a coating consisting of a metallic material on the inner surface of the body (4) of the stator (36), the impregnation of said coating with a self-lubricating composite materi...  
WO/2016/059331A1
In order to assist deployment, the invention relates to a deployable grille (32) with fins (44) for a thrust-reversal system (6) for an aircraft turbine engine. The grille can adopt a rest position and a deployed, active position in whic...  
WO/2016/060581A1
A method for organizing an operating process in a continuous detonation combustion chamber of a liquid-fuelled jet engine comprises supplying an oxidant, supplying a liquid fuel in the form of near-wall films, or in the form of jets, or ...  
WO/2015/052470A8
Mounting assembly for a rocket nozzle (17) for an engine operable in rocket mode, in which the engine combusts stored oxygen and hydrogen, or in air-breathing mode, in which the engine combusts air from the atmosphere and stored hydrogen...  
WO/2015/052473A8
The present disclosure relates to an engine having two modes of operation— air breathing and rocket— that may be used in aerospace applications such as in an aircraft, flying machine, or aerospace vehicle. The engine's efficiency can...  
WO/2016/057237A1
A thrust-vectoring rocket motor nozzle includes a forward assembly (102) having a forward shell (118) with a flange (104) configured for connection to a motor and a throat portion (126) opposite the flange. A ball joint sleeve (110) may ...  
WO/2016/055722A1
Nozzle (1) of a spacecraft engine (M), comprising a fixed portion (2) and a moving portion (3), the nozzle (1) comprising a pneumatic deployment system (4) comprising: - a deployment cylinder (5), deploying the moving portion (3) of the ...  
WO/2016/056486A1
In the present invention, when the combination of airfoils of two stator vanes for one rectifying plate is the same as the combination of airfoils of two stator vanes for another rectifying plate, the positions of a first rectifying-plat...  
WO/2016/056463A1
[Problem] To provide a stator-vane structure with which it is possible to suppress a pressure loss caused by a gap or a level difference between liners, while forming an air channel by using stator vanes made of a composite material and ...  
WO/2016/051047A1
The invention relates to the field of jet propelled craft and more specifically to a method for eliminating the POGO effect in such a craft (1). A supply system (4) feeding the jet engine (2) of the craft (1) is equipped with a hydraulic...  
WO/2016/050575A1
The invention is directed to a turbomachine component (10), particularly a gas turbine engine component, comprising at least one part (2) built in parts from a curved or planar panel (11), particularly a sheet metal, the part (2) compris...  
WO/2016/046924A1
[Problem] A heat exchanger generally employs a method for supplying liquid having a critical pressure or more or a high pressure in order to suppress a boil. However, because gas obtained in a carburetor behind the heat exchanger has a r...  
WO/2016/047343A1
This vertical take-off and landing aircraft (1) is provided with: a fuselage (2); a plurality of engines (3) that are installed on the fuselage and generate jet streams to produce thrust; an abnormality signal-acquiring unit for acquirin...  
WO/2016/042271A1
The invention relates to a device (36) for attaching a downstream end of an air inlet onto a fan casing (30) of an aircraft turbojet nacelle. The air inlet comprises an acoustic ferrule (28) that is radially defined by an inner skin (32)...  
WO/2016/012161A3
The present invention relates to a heat exchanger (50) comprising a plurality of plates (10, 20) provided with a planar peripheral area (19, 29), an internal area provided with sinusoidal undulations (13, 23, 14, 24) and two chimneys (11...  
WO/2016/039068A1
A fairing is formed around the axis of a turbo fan engine and between an outer casing and an inner casing. The fairing is disposed in a bypass duct bypassing compressed air from a low pressure compressor and provided with: a front portio...  
WO/2016/039993A1
A liquid propellant rocket engine includes a combustion chamber that has a throat. A nozzle diverges from the throat. The nozzle includes an afterburner combustor section that has a fuel injector orifice. A gas generator includes an exha...  
WO/2014/182546A3
A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the ...  
WO/2016/034795A1
The invention relates to a jet nozzle of a turbine engine, comprising an outer wall and an inner wall defining, between each other, a flow channel for the exhaust gas; the inner wall forming a central frustoconical body oriented in a lon...  
WO/2016/030646A1
Variable-pitch bladed disc comprising: -a plurality of blades (2), each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades comprising at least one first blade (21) and at least...  
WO/2016/030645A1
Variable pitch bladed disc comprising: - a plurality of blades (2), each being of variable pitch about a blade axis of rotation and having a root, the plurality of blades comprising at least one first blade (21) and at least one second b...  
WO/2016/003517A3
A thrust reverser system may comprise a cascade radially positioned about a centerline of an engine or a nacelle centerline. Various cascade features may be positioned at a constant radius from the centerline while other features vary ac...  
WO/2015/160403A3
A septum-tied tube pack is provided that includes a first outer wall formed by a multiple of first connected radiuses. A second outer wall is formed by a multiple of second connected radiuses. A first end radius connects the first outer ...  
WO/2016/025885A1
An exhaust arrangement is for an aircraft having sensing equipment and a front prop engine. An extension mounts on the underside along an edge of the fuselage to direct exhaust from the engine's exhaust pipes to a point to or past the se...  
WO/2016/025699A2
The present disclosure describes various embodiments of a plasma actuator device that can be affixed to a vehicle and configured to inject small turbulent structures to break down large vortical structures in a wake of the vehicle while ...  
WO/2016/020607A1
The quick-assist device applies to a free-turbine turbomachine (11) of an aircraft comprising at least a first free-turbine turbomachine (11) provided with a gas generator, combined with an electric machine (12) that can operate as a sta...  
WO/2016/020618A1
The present invention relates to a twin-flow, double body turbojet comprising a fan (S) positioned upstream from a gas generator and delimiting a primary flow and a secondary flow, said gas generator being traversed by the primary flow a...  
WO/2016/018171A1
The invention relates to methods for the detonation combustion of fuel mixtures and to apparatuses for carrying out same, and can be used in aircraft engines and vehicle engines, in stationary power plants, and in the chemical industry. ...  
WO/2016/018172A1
The invention relates to methods for detonation burning of fuel mixtures and to apparatuses for carrying out same, and can be used in aircraft engines and vehicle engines, in stationary power-generating plants, and in the chemical indust...  
WO/2015/092787A3
A compressor-less jet engine configured to generate thrust when the engine is at standstill.  
WO/2016/007171A1
A turbofan engine assembly (10) having a turbine engine (16) and a nacelle (20) that surrounds at least a portion of the turbine engine (16) to define an annular bypass duct (22) that defines a forward-to-aft bypass air flow path. The tu...  
WO/2016/007328A1
Disclosed are exemplary embodiments of systems and methods for gas envelope propulsion. In an exemplary embodiment, a propulsion system generally includes a power plant, and an inelastic gas envelope configured to receive a gas independe...  
WO/2016/001608A1
The present invention relates to the field of aircraft nacelles and concerns thrust reverser devices. More particularly, the present invention concerns a rear frame (132) for a thrust reverser structure with a diversion grid of an aircra...  
WO/2016/001587A1
The invention relates to a turbofan nacelle including a thrust reverser, the thrust reverser including a movable cover (10) moving back from a closed position in which the thrust is not reversed to an open position for uncovering grates ...  
WO/2016/000673A1
The invention relates to a chevron nozzle (13, 14, 21, 22, 30) for an engine (10, 12) of an aircraft (11), comprising at least one nozzle ring (31) and chevrons (32) arranged on the nozzle ring (31). The aim of the invention is to furthe...  
WO/2015/168793A3
A flex spline torque transfer device has a flex spline that is deflected in the radial direction by magnetic attraction to form a wave. The flex spline may be deflected radially inward by magnetic attraction to form a wave. The flex spli...  
WO/2015/197939A1
System comprising a test bed (1) and assembly (2, 4) comprising a divergent section (2) of a spacecraft motor, the assembly exhibiting the divergent section comprising a proximal end (41) and a distal end (22), the test bed (1) comprisin...  
WO/2015/197949A1
The invention relates to a turbojet engine comprising a shaft of a fan (12) driven by a turbine shaft (16) via a device (20) that reduces the rotational speed, characterized in that it comprises an uncoupling means (28) interposed betwee...  

Matches 451 - 500 out of 9,683