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Matches 1 - 50 out of 9,295

Document Document Title
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/2018/125327A1
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/2018/106331A1
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/2018/089067A3
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/2018/089057A2
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/2018/075102A3
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/2018/067231A3
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/2018/067253A1
A combustion management device for generating a thrust burst to impart a physical impulse. In operation, a combustion chamber, defined by a valve unit (33), is primed to a set pressure and fueled by fuel injectors (23). An ignitor (22) t...  
WO/2018/060588A1
Flow deflector (4) for a discharge valve system (1) of a dual-flow turbo-engine compressor. The flow deflector (4) comprising a wall (5) provided with a plurality of ejection channels (6) capable of discharging a discharge air flow (FC)....  
WO/2018/060633A1
The invention relates to the field of cryogenics, and in particular to a device and a method for cooling a cryogenic system (1). The cooling device (100, 101) comprises a cryogenic fluid supply circuit (102, 103) and at least one atomisa...  
WO/2018/063945A1
The present disclosure is directed to a fan section positioned on a tail section of an aircraft, in which the fan section defines a circumferential direction, a radial direction, and an axial direction. The fan section includes a fan and...  
WO/2018/054483A1
The invention relates to an aircraft turbine having counter-rotating propellers and a primary drive, the noise development of which is significantly reduced with respect to aircraft turbines which have a primary drive based on the intern...  
WO/2018/051566A1
The electric power-assisted liquid fuel rocket propulsion system comprises: a sub-combustor (11) which generates a combustion gas of a fuel and an oxidizing agent; a main combustor (10) which combusts a mixed gas of fuel and the combusti...  
WO/2018/052616A1
A gas turbine engine includes a fan section and a core turbine engine. The fan section includes a fan and a fan shaft, with the fan including a plurality fan blades rotatable with the fan shaft. The core turbine engine includes a turbine...  
WO/2018/049239A1
Aspects of the present disclosure include branching fluid passages in an apparatus that reduce turbulent flow and generate evenly distributed fluid pressure as the fluids branch off into the different passages. In some embodiments, the b...  
WO/2018/042106A1
A rocket engine having improved stability during its starting phase, the rocket engine (1) comprising a divergent (13) and a securing system (40) configured to retain the divergent (13) when the rocket engine (1) is started, the securing...  
WO/2018/045327A1
In some embodiments, a structural heat exchanger is presented that utilizes liquid fuel as a coolant as it travels through the perimeter of a region (e.g., a chamber) of an engine. The shapes of the coolant channels of the heat exchanger...  
WO/2018/044757A1
A multi-hybrid aircraft engine that includes a primary compressor (1), a multiplier (199) comprising a drive block, a driven block, driven block pistons (54), and primary shafts (78 and 41); an output shaft (105), and a speed regulator (...  
WO/2018/037456A1
A through hole 31 in a sound-absorbing liner 100 is inclined toward the upstream side from the front surface to the back surface of a porous plate 33. Thus, the direction of vibration VL of a hole fluid is inclined in accordance with the...  
WO/2018/039484A1
A propulsion system coupled to a vehicle. The system includes a diffusing structure and a conduit portion configured to introduce to the diffusing structure through a passage a primary fluid produced by the vehicle. The passage is define...  
WO/2018/037182A1
An integrated test method for testing the operation of an electrical power converter that is supplied with power by an on-board power supply network and that controls, using field-oriented control, a three-phase electric motor for a thru...  
WO/2018/037462A1
In this sound-absorbing liner 100, a through hole 31 is inclined toward the downstream side from the front surface 33a to the rear surface 33b of a porous plate 33. With this configuration, the flow of gas is restrained from impinging on...  
WO/2018/038868A1
An actuator produces a displacement that maintains positive contact between an electrically operated propellant and a pair of electrodes to ignite and sustain combustion of an ignition surface. The electrodes are suitably configured such...  
WO/2018/034795A1
Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy ...  
WO/2018/027536A1
An air booster. A first flow channel (A), an air chamber (B), and an output flow channel (C) are formed inside a housing (10) in a successive manner. The first flow channel (A) is a channel extending crookedly. The air chamber (B) is a c...  
WO/2018/026579A1
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming the...  
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/2018/020174A1
The invention relates to an acoustic attenuation panel (30) for a propulsion unit comprising a nacelle and a jet engine, the panel (30) comprising a cellular core (32) arranged between an internal skin (34) and an external skin (36), ref...  
WO/2018/022203A1
Electrical ignition of electrically operated propellant in a gas generation system provides an ignition condition at an ignition surface between a pair of electrodes that satisfies three criteria of a current density J that exhibits a de...  
WO/2018/020184A1
An acoustic panel (10') for a turbomachine, in particular for an aircraft, comprising two skins (12, 14) that are substantially parallel and between which cavities (16) are located and extend, forming Helmholtz resonators, one of the ski...  
WO/2018/022703A1
A turbopump includes a slinger that has a first section and a second section. The first and second sections are disposed substantially radially in a fluid circuit. The second section is downstream of, and radially inward of, the first se...  

Matches 1 - 50 out of 9,295