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Matches 1 - 50 out of 9,228

Document Document Title
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/2018/020174A1
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...  
WO/2018/020111A1
The invention relates to a pod for a turbojet engine, which comprises: an outer cowl (11), comprising: a structure (17), comprising at least one opening (19); a panel (21), pivotably mounted about an axis (31) between a closed position a...  
WO/2018/022723A1
A liquid propellant rocket engine includes a pump that is disposed along a central axis. The pump includes a purge system, a collection annulus in fluid communication with the purge system, and a drain. The collection annulus has an oute...  
WO/2018/015672A1
The invention relates to a nacelle (3) for a turbofan engine with a variable-pitch fan, the nacelle comprising a front section (300) intended to surround the fan of the turbofan engine, and a rear section, the rear section comprising an ...  
WO/2018/017788A1
A liquid propellant rocket engine includes a main turbo-pump and a boost turbo-pump. The main turbo-pump has a main pump with an outlet that is fluidly coupled with a supply line. The boost turbo-pump includes a housing, a rotor, a boost...  
WO/2018/013196A1
Ceramic matrix composite (CMC) components and methods for forming CMC components of gas turbine engines are provided. In one embodiment, a CMC component for a gas turbine engine includes an inner wall defining a first inner surface; an o...  
WO/2018/013504A1
An engine start system includes a facility that has a ground based hydraulic pressurization system and a combustor of a liquid propellant rocket engine. The engine is fluidly coupled to the ground based hydraulic pressurization system. T...  
WO/2018/009084A1
A bell-mouth scoop assembly (280, 800) includes an actuator (1302) comprising a plurality of hinge members (802) configured to rotate in unison about a respective hinge axis of rotation (804) from a first stowed position (502) to a secon...  
WO/2018/009420A1
A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine (52) and fan blades (54). Each unitary turbin...  
WO/2018/002523A1
A jet nozzle having a longitudinal axis (ZZ') comprises: a combustion chamber which is made of a metal material (14) and has a downstream end (141); and a divergent nozzle section (16) made of a composite material and formed of a cone-sh...  
WO/2018/004828A1
A duct includes first and second bellows sections. First and second torsional rings are attached to, respectively, the first and second bellows sections. First and second dynamic seals are sandwiched between the first and second torsiona...  
WO/2018/002560A1
The present invention relates to an arrangement (30) for the attachment of at least one connecting rod (20) of a thrust reversal flap (18) to a fixed internal structure (8) of a jet engine nacelle (1), the arrangement (30) being characte...  
WO/2018/004803A1
A solid rocket motor (20) includes a case (32), a throat (24a), a nozzle (22), a nitinol ring (138a) at least partially surrounding the throat, and a spring-loaded pin (36) to which the ring is attached. The spring-loaded pin abuts the t...  
WO/2017/220898A1
Disclosed is a thrust reverser for a device receiving a propulsion element, e.g. a turbojet engine nacelle (2), said thrust reverser (1) comprising: • - a stationary structure (4) that includes a deflector (24) deflecting at least a po...  
WO/2017/222908A1
A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The ...  
WO/2017/220754A1
The invention relates to an ignition device (120) for igniting a mixture (16), in particular for an engine, comprising an energy conversion device (123) and a fluid flow injection device (122). The energy conversion device (123) is desig...  
WO/2017/222614A2
Passive reactivity control technologies that enable reactivity control of a nuclear thermal propulsion (NTP) system with little to no active mechanical movement of circumferential control drums. By minimizing or eliminating the need for ...  
WO/2017/218841A1
A system and method for vectoring the thrust of a supersonic, air-breathing engine. A thrust vectoring mechanism uses two asymmetrically staggered ramps; one placed at the throat, the other positioned at the exit lip of the nozzle of the...  
WO/2017/216502A1
An axial guiding system is provided to guide a movable part (2) comprising the cowls of a thrust reverser relative to a stationary structure (6) of a nacelle of an aircraft containing a turbofan, said guiding system comprising slides gui...  
WO/2017/216450A1
The invention relates to a combustion chamber (1) for a rocket motor extending along a longitudinal axis A and comprising a longitudinal envelope, this longitudinal envelope comprising a longitudinal internal wall (10) made of a first al...  
WO/2017/216679A1
A method of and a system for actuating a cowl door. The method comprises detecting that current is drawn in a solenoid valve, the solenoid valve being selectively operable in a first mode to direct fluid from a fluid reservoir to an hydr...  
WO/2017/216463A1
The invention concerns a nacelle (100) for an aircraft turbojet engine, comprising: - a fixed internal structure (19) intended to receive an aircraft turbojet engine; - an external structure (21) that defines, with said fixed internal st...  
WO/2017/208117A1
An aircraft has a fuselage, left and right wings, and left and right engine assemblies connected to the wings. Each engine assembly has a nacelle, an engine housed in the nacelle, the engine having a plurality of rotors defining an uncon...  
WO/2017/204941A1
The low pressure turbine includes a rotor, an outer casing, a plurality of stages of rotor blades, and a plurality of stages of stator vanes. The rotor includes a longitudinal centerline. The outer casing circumscribes the rotor. The plu...  
WO/2017/203145A1
Annular combustion chamber of continuous detonation wave type enabling, from a mixture of a fuel and an oxidiser injected in an axial direction F, the delivery of a continuous production of hot gases from the detonation waves, the combus...  
WO/2017/198999A1
A compressor system for a turbo machine (10), comprising a low pressure shaft (36) coupled to a low pressure turbine (34), and a high pressure shaft (38) coupled to a high pressure turbine (32). The compressor system may comprise a fan (...  
WO/2017/197544A1
Four aeronautic/astronautic turbofan engines, which are respectively a turbofan engine comprising an air inlet for introduction of oxygen-enriched air, a turbofan engine comprising two oxygen-enriched air inlets, a turbofan engine free o...  
WO/2017/201279A1
A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permittin...  

Matches 1 - 50 out of 9,228