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Patent Searching and Data


Matches 551 - 600 out of 9,633

Document Document Title
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...  
WO/2015/079154A1
The invention relates to a fan, in particular for a small turbine engine such as a jet engine, having a hub ratio corresponding to the ratio of the diameter of the inner limit of the air intake section (26) at the radially internal ends ...  
WO/2015/026417A3
A variable geometry convergent-divergent nozzle for a gas turbine engine includes a centerbody extending rearward along a longitudinal axis of the engine which has a maximum diameter section. An inner shroud surrounds the centerbody and ...  
WO/2015/076882A2
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/2015/075503A1
The invention relates to a plastic propelling nozzle to be used in rockets, characterised in that the nozzle is made from a plastic material with glass fibre injection, that has characteristic properties allowing the entire rocket igniti...  
WO/2015/076929A1
A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.  
WO/2015/075360A1
A device (20) for supplying propellant to at least one propulsive rocket engine chamber (19) of a propulsive assembly (21) comprises a main propellant reservoir (1, 2), a main supply pipe (3, 4) extending between the main reservoir (1, 2...  
WO/2015/075355A1
The invention relates to a turbofan engine comprising a fan (S) driven, via a fan shaft (3) supported by at least two first bearings (11, 12), by a turbine shaft (4) supported by at least one second bearing (10) comprising a stationary r...  
WO/2015/076900A2
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/2015/067872A1
The invention relates to the field of technical trials and specifically to a technical trial method for assessing at least one device operation parameter (X) across a series of operation increments, each one of which corresponds to a sta...  
WO/2015/069147A1
A power plant having a separate wing-root engine which comprises an outer cowling, a compressor, a combustion chamber and a turbine that drives the compressor, and having propulsion devices which are situated separately from the wing-roo...  
WO/2015/067400A1
The invention relates to a turbomachine comprising an inner housing which radially defines the flow channel of the turbomachine. A thermal barrier coating is arranged about the inner housing. Said thermal barrier coating of the inner hou...  
WO/2015/067869A1
The present invention relates to an assembly comprising: - a mobile frame (8) supporting at least one turbo jet engine nacelle thrust reverser cowl, - an actuator comprising actuating cylinders (2) applying a retraction or traction axial...  
WO/2015/067878A1
The invention relates to the field of testing methods, and specifically to a method for technical testing of a device, including at least one operational step corresponding to a stable value of at least one operational setting of the dev...  
WO/2015/067894A1
The invention relates to the field of rocket engines, and specifically to a propulsion assembly (10) including a first tank (11), for a first liquid propellant, a second tank (12), for a second liquid propellant, a pressurisation device ...  
WO/2015/065525A1
An oil tank mounting system for use on a structure of a turbine engine, includes three mounts with each mount configured to constrain the oil tank with a different number of degrees of freedom of movement. A first mount may have fix the ...  
WO/2015/065428A1
An engine assembly having a turbine engine, a nacelle surrounding the turbine engine and defining an annular bypass duct between the nacelle and the turbine engine and extending through the turbofan engine to define a generally forward-t...  
WO/2015/063343A1
A method and a device for power extraction by means of an axial fluid machine, in an annulus tube comprising at least a rotatable inner wall (308, 408, 501) and/or a rotatable outer wall (409, 502) over which a swirling fluid is flowing ...  
WO/2015/059395A1
An autogenous pressurisation device (50) for a main propellant reservoir (10, 30), comprises a pressurisation pipe (13, 33) connected to the main reservoir (10, 30) for injecting the propellant into said main reservoir, a pressurisation ...  
WO/2015/059234A1
The invention relates to an actuator device (8) for moving a movable cowl of a thrust reverser, including: an actuator (12) including a screw (14) and a nut (15) capable of engaging with the screw (14) such that a rotation of the screw r...  

Matches 551 - 600 out of 9,633