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Matches 701 - 750 out of 9,921

Document Document Title
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...  
WO/2015/111253A1
[Problem] A thruster having a main body using a ceramic base composite material, that suppresses contamination caused by leaked gas leaking from micro-cracks formed in the main body. [Solution] Provided is a thruster comprising: a main b...  
WO/2015/112231A2
A gas turbine engine comprises a fan rotor configured to be driven by a fan drive turbine through a first shaft and a gear reduction. The fan rotor is configured to deliver air into a bypass duct as bypass air and to deliver core air flo...  
WO/2015/088606A3
A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an ...  
WO/2015/110770A1
Hydraulic control of a thrust reverser for a nacelle of a turbojet, comprising a hydraulic machine (30) fed by a pressure source (2), which powers the actuators (36) controlling the stroke movement of the reverser, characterised in that ...  
WO/2015/112554A1
A divergent flap includes a hinge joint to connect the divergent flap to a convergent flap, a plow structure, a first wall, a second wall, and two side walls. The plow structure is at a plow end of the flap opposite the hinge joint. The ...  
WO/2015/108709A1
A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine a...  
WO/2015/069335A3
An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the subs...  
WO/2015/104474A1
The present invention relates to an epicyclic reduction device (70) for rotating a first set of blades of a turbomachine, comprising a sun gear (74) centred on a longitudinal axis (12) of the turbomachine and connected to a rotor (76) of...  
WO/2015/069350A3
A gas turbine engine assembly has a pylon with a first side and a second side. A first rail is mounted to the first side and a second rail is mounted to the second side. The assembly also has a thrust reverser with a first door assembly ...  
WO/2015/069358A3
A gas turbine engine includes a core engine including a central engine axis and a nacelle surrounding the core engine. At least a portion of the nacelle is axially movable relative to the core engine between open and fully closed positio...  
WO/2015/104477A1
The invention relates to the field of propulsion systems, in particular to expander-type rocket engines, in which at least one propulsion chamber (40) is supplied with at least one first propellant by a first pump (33) coupled with a fir...  
WO/2015/104475A1
The invention pertains to a method for monitoring an aircraft engine retractable doors thrust reverser, the thrust reverser being a reverser having hydraulic actuators and being provided with contactors (3a, 4a, 5a, 3B, 4b, 5b, Sa, Sb) a...  
WO/2015/101758A1
A thrust reverser of a turbofan engine nacelle, comprising movable covers (4) that retract relative to a fixed front structure (10) to expose openings radially towards the outside, and rotary gratings (12) linked to the front structure b...  
WO/2015/096000A1
An aircraft with aturbofan engine assembly having at least one compressor, a nacelle surrounding the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine, a thrust reverser having at least one mov...  
WO/2015/069361A3
A disclosed fan drive gear system includes a sun gear rotatable about an axis of rotation, a plurality of intermediate gears rotatable about an intermediate gear rotation axis in meshing engagement with the sun gear and a ring gear circu...  
WO/2015/099552A1
The invention relates to pulse (pulsating) hydro-jet propulsion devices operating in a pulse detonation mode, and can be used as a power system for surface vessels and underwater vessels and for vehicles having various purposes. Propo...  
WO/2015/094607A1
A disclosed gas turbine engine includes a fan section including a hub supporting a plurality of fan blades rotatable about an axis, and a bearing assembly supporting rotation of the hub about the axis. A compressor section is in fluid co...  
WO/2014/123595A8
A thrust reverser system and operation suitable for high-bypass turbofan engines. The thrust reverser system includes a cascade system adapted to be translated with a translating cowl in an aft direction of an engine to expose a circumfe...  
WO/2015/093201A1
 A fan case is provided with: a cylindrical case main body (10) comprising a composite material; a linking ring (20) made of Al, the linking ring (20) being fittably secured to the rear end of the case main body (10) and being provided...  
WO/2015/041801A3
A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a m...  
WO/2013/147967A3
A variable area fan nozzle for a gas turbine engine includes a radially outer wall and a radially inner wall. At least one of the radially outer wall and the radially inner wall includes a wall thickness distribution that has local thick...  
WO/2015/088606A2
A reverse-core turbofan engine including a propulsor section including a fan and a fan-tip turbine configured to deliver air to a core duct, including a first portion, disposed aft of the propulsor section, and direct air aft, toward an ...  
WO/2013/102113A3
Embodiments of the present invention include unique gas turbine engines. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects,...  
WO/2015/088593A1
An edge seal for preventing airflow through a space between a fan platform and an adjacent airfoil in a gas turbine engine may include a bonding segment being bondable to the fan platform. A sealing flap converges with the bonding segmen...  
WO/2015/088833A1
A system for varying the fan pressure ratio of a gas turbine engine is provided. The system may comprise a stator having a variable area component. The variable area component may be configured to adjust the inlet area on the main fan by...  
WO/2015/084452A2
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/2015/084451A1
A method of forming a ceramic matrix composite component is provided. The method includes applying a first amount of adhesive across a surface of a release film, providing a first ceramic foam panel including a plurality of channels form...  
WO/2015/082330A1
An aircraft engine (10) comprising a gas turbine (13) and a sound generation device (14) for actively reducing the operating noise generated by the gas turbine (13) is characterized in that the sound generation device (14) comprises at l...  
WO/2015/080785A2
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/2015/079100A1
A heat exchanger according to the invention comprises a heat exchanging ele- ment (101) comprising heat transferring walls for preventing first fluid and second fluid from mixing with each other and for transferring heat from the first f...  
WO/2015/080787A2
A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. Th...  

Matches 701 - 750 out of 9,921