Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 1 - 50 out of 9,168

Document Document Title
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...  
WO/2017/200665A1
A gas turbine engine includes a core engine, a low pressure turbine, a fan assembly, a gearbox, and a lubrication scavenge pump. The core engine includes a high pressure compressor, a combustor, and a high pressure turbine configured in ...  
WO/2017/194866A1
The invention relates to a rotating front part (1) of an aircraft turbomachine intake comprising bolts (34) for attaching a cone tip (20a) to an internal support (24), each bolt comprising a rear end (50) that is screwed into the support...  
WO/2017/196208A1
The group of inventions is intended to improve the energy efficiency of internal combustion engines by improving the conversion of fuel combustion energy into mechanical energy. The claimed method is characterized in that, in a working c...  
WO/2017/194897A1
A nozzle of variable cross section (100) comprises an ejection casing (101) and a plurality of internal flaps (110) that are disposed in a ring downstream of the ejection casing. Each internal flap is connected to the ejection casing by ...  
WO/2017/193052A1
A thrust reverser assembly (44) for a gas turbine engine (10) and a method to operate it. The gas turbine engine comprises a core engine (14), a nacelle (12) surrounding at least a portion of the core engine (14) defining a bypass duct (...  
WO/2017/190940A1
The invention relates to a drive system for an aircraft (1) comprising an electrical generator (15) and an internal combustion engine (13) having a gas expansion turbine (25). The generator (15) has a rotor (17) rotatably mounted by mean...  
WO/2017/187093A1
The invention relates to a double-flow turbomachine (26) having an upstream fan wheel (36) and a downstream rectification unit (24) for an air outflow from a secondary annular air stream which is delimited radially on the inside by a rad...  
WO/2017/182748A1
A pitch actuation system (22') for a turbomachine propeller (10), comprising an actuator (24) with a movable portion (26) configured to be connected to blades (14) of the propeller in order to rotate them relative to the blade-pitch sett...  
WO/2017/182334A1
The invention relates to an energy conversion system for a turbomachine, characterized in that at least one transmission (10, 20a, 20b, 20c) and/or at least one bearing housing (40) is thermally coupled to at least one thermoelectric ele...  
WO/2017/184235A3
A thrust reverser includes: a thrust-reversing element movable between a stowed position and a deployed position; at least one hydraulic actuator operably coupled to move the thrust-reversing element between the stowed and deployed posit...  
WO/2017/182734A1
A pitch actuation system (22') for a turbomachine propeller (10), comprising an actuator (24) with a movable portion (26) configured to be connected to blades (14) of the propeller in order to rotate them relative to the blade-pitch sett...  
WO/2017/182565A1
The invention relates to a thrust reverser door (18) for a jet engine nacelle, said door comprising an inner skin (32), an outer skin (30) and a frame (34, 36, 40) arranged between said inner and outer skins, said frame comprising two lo...  
WO/2017/176311A1
A thruster includes multiple segments of electrically-operated propellant, electrodes for igniting one or a few of the electrically-operated propellant segments at a time, and a propellant feeder for moving further propellant segments in...  
WO/2017/168079A1
The invention relates to a casing (20) for a propellant feed turbopump (10) for a rocket engine (50), comprising a cooling circuit (30), said cooling circuit being arranged at least partially in a wall of the casing (20).  
WO/2017/164773A1
The group of inventions relates to detonation combustion reaction devices. A detonation combustion reaction device contains a ceramic pendulum gate, which is disposed inside a detonation combustion system and divides the system into two ...  
WO/2017/158298A1
The invention concerns a bypass turbojet engine (1) comprising: a low pressure shaft (6) supported by at least two low pressure bearings (BP#1 to BP#4), a high pressure shaft (8) supported by at least two high pressure bearings (HP#1, HP...  
WO/2017/158856A1
A jet engine is provided with an inlet 11 and a combustor 12 having a fuel injection port 30a. The combustor 12 has a wall part 16 that defines an air flow path FA. The wall part 16 has a ramp part 60, which has an inclined face 62, and ...  
WO/2017/158296A1
The invention relates to a turbofan (1) comprising: - a low-pressure shaft (6); - a high-pressure shaft (8); - a fan shaft (7); - a reducing mechanism (10) that couples the low-pressure shaft (6) to the fan shaft (7); and - a maximum of ...  
WO/2017/158294A1
The invention relates to a turbofan engine (1) comprising: a turbine shaft (10); a fan shaft (20); and a reduction mechanism (12) coupling the turbine shaft (10) and the fan shaft (20), said turbofan engine (1) having a bypass ratio grea...  
WO/2017/160375A3
A thruster operable in a chemical mode or in an electrospray mode using the same liquid monopropellant for operation in both modes is described having a multiplicity of a microthrusters made of a catalytic material having a bore therethr...  
WO/2017/158857A1
A jet engine is provided with an inlet 11 for taking in air, and a combustor 12 that has a fuel injection port 30a for injecting fuel. The combustor 12 uses the air to combust the fuel injected from the fuel injection port 30a. Between t...  
WO/2017/160375A2
A thruster operable in a chemical mode or in an electrospray mode using the same liquid monopropellant for operation in both modes is described having a multiplicity of a microthrusters made of a catalytic material having a bore therethr...  
WO/2017/153610A1
The invention relates to a ducted propeller (100) comprising a housing (102) with an inlet opening (104) and an outlet opening (106), at least one propeller (108) which is mounted in the housing (102) in a rotatable manner about a rotati...  
WO/2017/153677A1
The invention relates to a rocket engine having more secure and better controlled solar ignition, said rocket engine comprising an axisymmetrical propulsion chamber (12) having a neck (12c) where the diameter of said propulsion chamber (...  
WO/2017/151188A1
A method of producing a propellant material element (12), such as an electrically-operated propellant material, includes extruding a propellant material (16) through a heated nozzle (20). The nozzle may be heated to a temperature that is...  
WO/2017/151189A1
A device may include an electrically-operated propellant or energetic gas-generating material, additively manufactured together with electrodes for producing a reaction in the material. The device may also include a casing that is additi...  
WO/2017/142590A1
A hybrid rocket motor (10) includes a solid fuel element (12), and an oxidizer tank (14) containing an oxidizer (16). The solid fuel element adjoins and at least partially defines a combustion chamber (20) in which the solid fuel and the...  

Matches 1 - 50 out of 9,168