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Matches 151 - 200 out of 9,637

Document Document Title
WO/2018/167204A1
The invention relates to an improved method for operating a thrust chamber device and to a thrust chamber device, comprising a thrust chamber having a thrust space having three adjacent sections. The thrust space is delimited in all thre...  
WO/2018/162839A1
The invention relates to a device for actuating a thrust reverser, comprising mobile thrust-reversing elements (1) carried by a nacelle in order to move between a retracted position and a deployed position, the actuating device comprisin...  
WO/2018/162259A1
A lockable actuator (1) comprising; - a frame (8); - a screw (15) for pivoting relative to the frame - a nut (19) engaged on the screw so as to move on the screw (15) between a first over-retracted position and a second deployed position...  
WO/2018/162260A1
Actuator (1) comprising: – a screw (15) mounted on a frame (8) so as to pivot; – a nut (19) connected to an element that is to be moved and which is engaged on the screw (15) in order to be moved between a first, over retraction, pos...  
WO/2018/158537A1
A mechanical decoupler (15) at the inlet to a turbomachine is positioned on the outside of an intake casing, where radiating arms (27) meet an external casing (13) so as to partially unload a low-pressure shaft when a significant out-of-...  
WO/2018/154908A1
This scramjet engine is provided with first and second flow path forming members. A flow path is formed between a first surface of the first flow path forming member and a second surface of the second flow path forming member. The flow p...  
WO/2018/156263A1
The present disclosure is directed to an aircraft including a fuselage to which a pair or more of wings attaches. The aircraft defines a transverse direction, a longitudinal direction, and a latitudinal direction. The aircraft includes a...  
WO/2018/156262A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial center...  
WO/2018/156235A1
The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial center...  
WO/2018/154005A1
The invention relates to a jet engine (10) comprising a flow channel (36) which is located in a nacelle (15) and is delimited radially inside by a centerbody (44) and radially outside by an outer jet wall (45). The free cross-section of ...  
WO/2018/128684A3
A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature senso...  
WO/2018/147949A1
The subject matter of this specification can be embodied in, among other things, a lock apparatus that includes a latch hook having a catch at a first latch end, a first pivotal mount at a second latch end opposite the first latch end, a...  
WO/2018/146405A1
The invention relates to a turbofan (1) comprising a low-pressure compressor (3); a series of housings (9, 10) arranged downstream of said low-pressure compressor (3) for defining a primary stream, and comprising an upstream edge (19) de...  
WO/2018/147950A2
The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine...  
WO/2018/144451A1
The present subject matter can be embodied in, among other things, a two-speed thrust reverser actuation system for actuating a thrust reverser element experiencing an assisting load during movement between a stowed and deployed position...  
WO/2018/142075A1
Cardan joint spider (1) comprising a body comprising four right-angle brackets (10), each right-angle bracket (10) having two branches (10a, 10b) perpendicular to one another, the branch (10a) of one right-angle bracket (10) being assemb...  
WO/2018/144468A1
An engine assembly includes a nacelle configured to at least partially surround an engine and a thrust reverser coupled to the nacelle. The thrust reverser includes: a thrust-reversing element movable relative to the nacelle between a st...  
WO/2018/138296A1
The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includ...  
WO/2018/136066A1
A gas turbine engine has an exhaust system (12) that forms the perimeter of the volute outlet (19) using chevrons (23a). The use of chevrons (23a) helps mix the exhaust fluid flow (27) as it moves into the exhaust system stack (18). The ...  
WO/2018/134541A1
The invention relates to a rocket engine (1) including a main combustion chamber (5) and a main nozzle; two propellant supply pumps (8a, 13) arranged on propellant supply circuits of the engine to supply the main combustion chamber; two ...  
WO/2018/130616A1
A rocket propellant tank arrangement (40) for storing fuel and oxidizer for launching a rocket includes an oxygen tank (42) for storing liquid oxygen and a fuel tank (52) for storing liquid fuel, wherein the fuel tank is at least partial...  
WO/2018/130787A1
The invention relates to a concentric gas flow mixer in a multiple-flow turbomachine, comprising a nominally cylindrical upstream part and a downstream part having outer and inner lobes distributed peripherally around the tower of said m...  
WO/2018/128684A2
A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature senso...  
WO/2018/127899A2
The present invention relates to a combustion thruster with a mini-scale engine for the use thereof in small satellites and to reduce the manufacturing cost, forged inside of a material suitable for its performance with the aim of formin...  
WO/2018/128791A1
A gas turbine engine defines a radial direction and an axial centerline. The gas turbine engine includes a core turbine engine that defines a core inlet. The core inlet is oriented with respect to the axial centerline and positioned alon...  
WO/2018/122224A1
The invention relates to an electromechanical actuator (1) comprising: - a screw (15) extending along a longitudinal axis; - a nut (19) fitted on the screw (15) and provided with means (24) for connecting to an element (2) to be moved; -...  
WO/2018/067231A3
A gas turbine engine includes a compressor section and a turbine section together defining a core air flowpath. Additionally, a rotary component is rotatable with at least a portion of the compressor section and at least a portion of the...  
WO/2018/125327A1
Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstre...  
WO/2018/115763A1
A turbomachine (10) comprising a fan (12) shaft driven by a turbine shaft (16) by the intermediary of a rotational speed reduction device (20), said turbomachine comprising decoupling means (28) interposed between the reduction device (2...  
WO/2018/117359A1
The present invention relates to: a nanoenergetic material (nEM) composite-based solid propellant in which a potassium nitrate-sucrose (KNSU) composite propellant and an nEM are mixed so as to prepare a solid propellant (KNSU/nEMs compos...  
WO/2018/117904A1
A ram-jet and turbo-jet detonation engine consists of an inlet part, a middle part and a discharge part, and a firing system. The inlet part and the discharge part are in the form of axisymmetrical round hollow rotating cones which are i...  
WO/2018/115731A1
The invention relates to a nacelle (3) for an aircraft turbofan, comprising a rear section (34), a thrust reversal device (42), the thrust reversal system (42) comprising an upper door (44) and a lower door (46), the doors being mobile i...  
WO/2018/109401A1
The invention relates to an ignition system (2) for a spacecraft engine comprising a combustion chamber (11) and a nozzle (1); the ignition system (2) being designed to be inserted into the nozzle (1) and comprising an electric spark-gen...  
WO/2018/089067A3
A propulsion system (300) for an aircraft (10) includes an electric propulsion engine. The electric propulsion engine includes an electric motor (334) and a fan (304) rotatable about a central axis (302) of the electric propulsion engine...  
WO/2018/075102A3
An injector element for a liquid propellant rocket engine includes an oxidizer conduit, a central cavity that is fluidly coupled with the oxidizer conduit downstream of the oxidizer conduit, a first annulus that at least partially surrou...  
WO/2018/106331A1
An electric machine is provided which includes a rotor disk extending along a radial direction and having a rotor flange attached to or formed integrally with the rotor disk and extending substantially along the axial direction. A plural...  
WO/2018/104632A1
The present invention relates to a nacelle (41) for an aircraft turbojet engine, comprising a thrust-reversing device, said nacelle comprising: - a fixed structure (43) and - a movable structure (45), translatably movable along an axis (...  
WO/2018/100278A1
The invention relates to a guide vane (24) for an aircraft bypass turbomachine, the aerodynamic part (34) thereof comprising a first internal lubricant cooling passage (50a) in which heat transfer means are arranged and a second internal...  
WO/2018/100274A1
A system for correcting POGO effect for a system for supplying liquid propellant to a rocket engine, comprising a liquid propellant supply line portion (70), a hydraulic accumulator (11), comprising a tank (12) connected to the supply li...  
WO/2018/100288A1
The invention relates to an aircraft turbojet engine nacelle, the nacelle (1) comprising a rear section (4) without lower fork, the rear section comprising a thrust reversal system, the thrust reversal system comprising a mobile cowl (20...  
WO/2018/096236A1
Device and method for regulating a flow rate of gas intended to supply a propulsion apparatus for a spacecraft comprising xenon tank (2), a circuit comprising a withdrawing pipe (3) having an upstream end connected to the tank (2) and a ...  
WO/2018/096244A1
The invention relates to a system for correcting pogo oscillation for a system for supplying liquid propellent to a rocket engine, comprising a supply duct portion (70) for supplying liquid propellent, a hydraulic accumulator (11), compr...  
WO/2018/096254A1
The invention relates to a housing of a cryogenic body of a spacecraft, said housing consisting of a plurality of segments (2), each one comprising: an inner wall (22) defining an inner space, and an outer wall (23) opposite the inner wa...  
WO/2018/089057A2
A method of preventing standing waves in an installed gas turbine having a fan, having a fan speed, and a compressor, having a compressor speed, includes correcting the fan and compressor speeds for temperature and monitoring the correct...  
WO/2018/084902A1
A turbofan engine includes a core (30); and a low-pressure turbine (22) configured to drive a fan (46) to produce a fan flow that exits the engine without passing through a turbine. The fan includes a rotor having at least one rotor stag...  
WO/2018/076958A1
An apparatus for measuring axial displacement of a solid rocket motor grain in a launching process, comprising a body (1), fixed blocks (2), and a reference block (3). The body (1) is a test motor. The front and rear ends of the undersid...  
WO/2018/078579A1
This description presents the design of propellant valve-injector of a spacecraft thruster with a heat (thermal) control system. The valve-injector consists of: the actuator for moving the valve in order to open and close the orifice of ...  
WO/2018/075105A1
Aspects of the present disclosure are presented for a hybrid rocket engine with regenerative fuel capability having a permeable inner wall structure that allows for non-solid fuel propellant to seep through and be used to generate thrust...  
WO/2018/026408A3
The gas turbine engine includes a core engine including a HP compressor, a combustor, and a HP turbine in a serial flow arrangement, A LP turbine is positioned axially aft of the core engine and includes a plurality of stages of rotor bl...  
WO/2017/041018A9
A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore condu...  

Matches 151 - 200 out of 9,637