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Patent Searching and Data


Matches 501 - 550 out of 9,637

Document Document Title
WO/2015/166179A1
The invention relates to an aircraft turbine engine (1) comprising a fan (15) as well as a reduction gear (20) including a plurality of rotary elements (52, 58) and driving the fan, the turbine engine also including a gearbox (32) as wel...  
WO/2015/130384A3
The present disclosure relates generally to a system for fan nacelle inlet flow control in a gas turbine engine, the nacelle comprising a nacelle inlet cowl including an inlet lip disposed at a leading edge of the nacelle inlet cowl, an ...  
WO/2015/166187A1
The invention relates to a modular assembly for a turbine engine, comprising an annular bearing support (26) including means for connecting to a first anti-friction bearing (24) designed to be mounted around a first shaft (16) of the tur...  
WO/2015/166921A1
The present invention improves the durability of an afterburner (25) and yet suppresses a reduction in the engine efficiency of an aircraft engine (1). A ring-shaped cooling channel (35) through which cooling air (CA) flows is formed bet...  
WO/2014/133911A3
Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed rela...  
WO/2015/159944A1
A vapor jet system which includes: a container which accommodates a sublimable solid and is equipped with a vapor discharge port for discharging vapor generated by sublimation of the sublimable solid; a member which is equipped with an o...  
WO/2015/116283A3
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pres...  
WO/2015/156872A2
An aircraft jet propulsion system may comprise a thermoelectric cooler array coupled to a portion thereof, wherein the TEC array converts electrical energy to heat energy to create a temperature gradient and cools a turbine case using th...  
WO/2015/155733A1
A combustor (2) for a liquid propellent motor (1) has an elongated hollow tubular casing (4) having an inner wall (12) delimiting a combustion chamber (8) for the liquid propellent and an outlet nozzle (11) for the combustion products, a...  
WO/2015/155432A1
The present invention relates to a door-type thrust reverser device (21) for a turbojet engine nacelle, comprising: - a fixed structure (31), and - a mobile structure (33) mobile with respect to said fixed structure, comprising at least ...  
WO/2015/155434A1
The invention relates to a thrust reverser of a turbofan pod, comprising movable cowlings (4) that retract relative to stationary front structure (2) to reveal stationary or movable thrust reverser cascades, as well as a secondary variab...  
WO/2015/150707A1
The invention relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a transverse pivot in order to partially close off the ...  
WO/2015/150706A1
The method according to the invention includes: a step (E10) of obtaining a measurement of the monitored parameter carried out by a sensor and corresponding to an operating point of the engine, said operating point being defined by at le...  
WO/2015/151621A1
This jet engine is provided with an inlet that takes in air, a combustor (12) that combusts a fuel using air, and a fuel control unit (37) that controls the supply of fuel. The combustor (12) is provided with a fuel supply unit (22) that...  
WO/2015/151062A1
A solid propellant rocket motor (1) has a tubular casing (3) accommodating a mass (5) of solid propellant material and at least one opening (10) for the space in the casing (3) to communicate with the outside closed by a closing head (11...  
WO/2015/151620A1
This jet engine is provided with an inlet and a combustor. The inlet (11) takes in air. The combustor combusts a fuel using air. The combustor is provided with an injector (20). The injector (20) has an opening portion (31) for injecting...  
WO/2015/150653A1
Bypass turbojet engine nacelle thrust reverser comprising mobile cowls (4) which retract with respect to a fixed forward structure (2) in order to uncover thrust reversal cascades or vanes, and a variable secondary nozzle (6) connected t...  
WO/2015/146357A1
A combustor (7) of this jet engine comprises: a fuel injector (62); an igniter (61) for igniting a gas mixture of air and a fuel; and a flame-holding part (66, 66'). The igniter (61) is arranged within the flame-holding part (66, 66'). A...  
WO/2015/145041A1
The invention relates to a method for detecting a failure of a first turbine engine, referred to as faulty engine (4), of a twin-engine helicopter and for operating a second turbine engine, referred to as sound engine (5), each engine (4...  
WO/2015/146375A1
This jet engine comprises: an inlet (11) that takes in air; and a combustor (12) that combusts a fuel by using said air. The combustor (12) includes an injector (20), a plurality of flame holders (21, 22), and a disappearing part (31). T...  
WO/2015/146376A1
This jet engine comprises an inlet and a combustor. The inlet takes in air. The combustor combusts a fuel by using said air. The combustor (12) includes an injector (20) that is provided with a plurality of openings (31a, 31b) for inject...  
WO/2015/145056A1
The invention relates to a thrust reversal device (12) for an aircraft turbojet engine pod including at least one movable cover (22) and a thrust reversal flap (26) that extends from a head (28) to a leg (30). Said device is characterize...  
WO/2015/146356A1
This jet engine comprises: an inlet (6) that takes in air; and a combustor (7) that combusts a fuel by using said air. The combustor (7) includes a fuel injector (62), and an igniter (61) for igniting a gas mixture of said air and said f...  
WO/2015/140450A1
The invention relates to a locking device (12) for a thrust reverser (14) with door (16) equipping a turbo jet engine nacelle (10), characterized in that the device (12) comprises a first fitting (28) secured to the door (16) and a secon...  
WO/2015/142395A2
The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.  
WO/2015/142394A1
A hybrid structure comprises a metallic built-up sandwich structure, and a monolithic superplastic formed and diffusion bonded structure joined to the built-up sandwich structure.  
WO/2015/143362A1
In one embodiment, a power generation system includes a pulse detonation engine including a combustion chamber, a linear power generator including a working chamber, and a nozzle positioned between the combustion chamber and the working ...  
WO/2015/138033A1
An inlet manifold for a multi-tube pulse detonation engine includes a vaneless diffuser disposed in a first zone to collect an air discharged from a compressor; a vaned diffuser including a plurality of guide vanes disposed in a second z...  
WO/2015/134081A2
The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator...  
WO/2015/133639A1
A blade for a propeller constituting an aircraft engine that constitutes a reaction engine or composite reaction engine configured such that, in order to produce a sustained output at the theoretical rotational speed of an axial compress...  
WO/2015/130386A2
The present disclosure relates generally to turbomachinery in which a rotating component is disposed adjacent a counter-rotating component in order to achieve a relative rotational velocity that is higher than would be achieved with a ro...  
WO/2015/128563A1
The invention relates to a forward fan rotor (16) with a hub (18) of axis of rotation (X) and a cone (22) mounted on the hub (18) of the fan (16), the cone (22) comprising an air bleed orifice (34) which opens into an air duct (32) of wh...  
WO/2015/130382A2
A fan assembly for a gas turbine engine is disclosed. The fan assembly may include a rotor, a plurality of airfoils extending radially from the rotor, and a platform surrounding the rotor and including a surface that defines a flow path ...  
WO/2015/130384A2
The present disclosure relates generally to a system for fan nacelle inlet flow control gas turbine engine.  
WO/2015/125766A1
A thrust vectoring device (101) equipped with: a shroud (102) having an opening; a nozzle (104) for spraying gas through the opening in the shroud (102), and provided in the interior of the shroud (102); a rotational drive shaft (S140) p...  
WO/2015/124879A1
The present invention relates to (solid) propellant loads with a mechanically reinforced liners/propellant connection as well as a method for the preparation of said loads. Said loads comprise: - a propellant block, containing energy loa...  
WO/2015/126489A2
An exhaust section for an aircraft gas turbine engine includes an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine having a fan section, a compressor section, a combustion section, a turbine section, an...  
WO/2015/122862A1
Oxygen (1) and fuel (3) are mixed (5) and sent to the combustion chamber (8). At certain periods, ignition is made. The generated gas pressure goes through the space of the funnel shaped structure (11), hits the head (13) section of the ...  
WO2015084452A3
The present disclosure relates generally to a variable area turbine vane row assembly. In an embodiment, the variable area turbine vane row assembly includes rotatable vanes that are circumferentially biased and/or axially biased with re...  
WO/2015/119740A1
A thrust reverser cascade having a frame and a body. The body comprises multiple layers formed by an additive manufacturing process where at least one of the layers is coupled to the frame.  
WO/2015/119698A2
A gas turbine engine comprises a first turbine rotor positioned upstream of a second intermediate turbine rotor and a third turbine rotor positioned downstream of the first and second turbine rotors. A fan rotor and three compressor roto...  
WO/2015/116283A2
A gas turbine engine comprises a fan for delivering air into a bypass duct as bypass flow, into a core housing as core flow, with the core housing containing an upstream compressor rotor and a downstream compressor rotor. An overall pres...  
WO/2015/080785A3
A cascade set for creating sufficient drag to slow an aircraft is disclosed. The cascade set includes one or more supporting vanes. A plurality of turning vanes are connected to the supporting vanes, and the turning vanes include forward...  
WO/2015/116494A1
A mid-turbine frame (MTF") for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ("HPT") and a low pressure turbine ("LPT"), the duct comprising a plurality of segments that together form an oute...  
WO/2015/076900A3
A fan rotor, for an aircraft engine, including at least one blade root attachment lug, each blade root attachment lug including an attachment lug surface, wherein at least one cavity is disposed on each attachment lug surface.  
WO/2015/114241A1
The invention relates to a nacelle (1) for an aeroplane turbojet, comprising a frustoconical radially outer annular wall (13) from which a pylon (9) extends radially outwards, the pylon (9) being used to attach the nacelle (1) to a stati...  
WO/2015/053848A3
A platform for a gas turbine engine has an outer surface and an inner surface. The inner surface is provided with a mount location for mounting the platform to a rotor. The platform extends from a leading edge to a trailing edge, and bet...  
WO/2015/052474A3
A rotational machine such as a turbo compressor has a fluid recovery system for recovering leaked working fluid such as gaseous helium in a helium circuit which has leaked past a shaft seal, a purifier being provided for removing contami...  
WO/2015/110741A1
An aircraft turbo engine having non-ducted propellers provided with a gas generator and a receiver comprising a propulsion assembly carrying at least one propeller, comprising a first housing (27), a second housing (40) and a third housi...  
WO/2015/076882A3
A turbine engine fan case (48) comprises a composite body member (300) circumscribing an axis (500) and having an annular mounting portion (310, 410), a segmented polymer member (320, 330, 420, 440) along the annular mounting portion, an...  

Matches 501 - 550 out of 9,637