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Match Document Document Title
8167531 Method and apparatus for supporting rotor assemblies during unbalances  
A method and apparatus for reducing dynamic loading of a gas turbine engine is provided. The gas turbine engine includes a rotor shaft assembly including a rotor shaft, a bearing assembly, a...
8166746 Rotor containment element with frangible connections  
A containment system for containing fragments of a burst rotor including first and second means for frangibly connecting a containment element to first and second walls, the first and second means...
8137053 Assembly having first and second members distinguishable by respective first and second compositions each including one or more isotopes of a same element  
An assembly includes a first member and a second member, the first member including a first material composition and the second member including a second material composition. The first and second...
8127525 System for dissipating energy in the event of a turbine shaft breaking in a gas turbine engine  
A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The...
8128339 Bearing support structure and gas turbine  
To provide a bearing support structure and a gas turbine that prevent damage of device induced by a rotor shaft when the rotor shaft is unbalanced, the bearing support structure and the gas turbine...
8087873 Secondary blade portion containment device  
A device that deploys during a blade portion failure that encompasses the engine casing is provided to prevent damage caused by the failure. A blade containment device such as a flexible interwoven...
8087874 Retention structures and exit guide vane assemblies  
A retention structure includes a center body including an outer surface, an enclosed end, an open end, and a contact section, the outer surface adapted to define a first portion of a flowpath, and...
8061966 Composite containment casings  
Composite containment casing including a body having an interior, an abradable system integrally joined to the interior of the body of the containment casing wherein the abradable system comprises,...
8061967 Panel for supporting abradable material in a turbomachine  
A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure...
8061965 Ring structure of metal construction having a run-in lining  
A ring structure with a metal design for a moving blade of axially flowed through compressor and turbine stages, particularly in gas turbine engines is provided. The ring structure includes a...
8057171 Fan assembly  
A fan assembly for a gas turbine, the assembly comprising: a fan surrounded by a fan casing; a resilient, radially flexible containment material wrapped around the outside of the fan casing for...
8057160 Device for limiting turbine overspeed in a turbomachine  
A device (40) for limiting overspeed in a turbomachine in the event of breakage of the turbine shaft (24), comprising means (38, 44) of propelling a pin (42) into the path of the blades (22), these...
8055413 Method for compensating hydraulic pressure of automatic transmission  
Faster shifting operation and reduced shift shock in response to a braking operation during a lift-foot-up shifting may be achieved when an automatic transmission is controlled by a method for...
8046915 Methods for making composite containment casings  
Method for making a composite containment casing having an integrated abradable system involving providing a mandrel having a pocket, positioning a sandwich structure into the pocket, applying at...
8047764 Blade containment structure  
The fan duct of a ducted fan gas turbine engine has a fan case lined with a honeycomb structure that acts to absorb the energy of a separated part of a blade. A layer of composite material lining...
8029231 Fan track liner assembly  
A fan track liner within a rotor blade assembly for a gas turbine engine comprises a radially inner casing liner member and a radially outer casing liner member adjacent to the radially inner...
8021102 Composite fan containment case and methods of fabricating the same  
A method of fabricating a fan containment case for a gas turbine engine is provided. The method includes forming a core layer material, wrapping the core layer material about a cylindrically-shaped...
8016543 Composite case armor for jet engine fan case containment  
A gas turbine fan blade containment assembly includes a fan case having an inner surface surrounding a jet engine fan and an outer surface. Mounted on the inner surface and across a blade...
7959405 Blade containment structure  
The fan duct of a ducted fan gas turbine engine has a fan case (20) lined with a honeycomb structure (22) that acts to absorb the energy of a separated part of a blade (16). A layer of composite...
7914256 Articles made from composite materials having toughened and untoughened regions  
Articles having a body including a composite material having at least one toughened region and at least one untoughened region, the toughened region containing a toughening agent selected from the...
7914251 Liner panel  
A liner panel for a fan casing of a gas turbine engine includes a honeycomb layer, a septum layer and an abradable layer. The fan casing is provided with a containment system in case of fan blade...
7874136 Rotor containment element with frangible connections  
A containment system for containing fragments of a burst rotor including first and second means for frangibly connecting a containment element to first and second walls, the first and second means...
7866939 Liner for a gas turbine engine casing  
A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the...
7850416 Turboengine and method for adjusting the stator and rotor of a turboengine  
A turbo-machine (1), including a stator (2), internally coated with a running-in layer (6), a rotor (4) within the stator (2), wherein the turbo-machine (1) supplementally includes a device for...
7811053 Fan rotor design for coincidence avoidance  
A fan rotor capable of avoiding coincidence will include a fan hub comprising one or more slots each designed to receive a fan blade; and one or more fan blades disposed within the slots. One or...
7806364 Containment system for a gas turbine engine  
A containment system for a gas turbine engine comprises a force absorbing arrangement for absorbing the force exerted thereon by an ejected portion of a failed component of the engine. The force...
7798285 Acoustic barrel for aircraft engine nacelle including crack and delamination stoppers  
An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an...
7794197 Aerofoil blades with improved impact resistance  
An aerofoil blade for a gas turbine engine, the blade having a metallic core defining a number of cavities that contain a foamed material. The cavities are shaped such that the force of an impact...
7780400 Device for detecting a fracture in the shaft of a gas turbine, and gas turbine  
An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine...
7780401 Ice strike sheathing ring for the fan casing of an aircraft gas turbine  
An ice strike sheathing ring (4) including several fiber compound layers for the fan casing of an aircraft gas turbine features breaking points (7) at a certain regular distance, so that, in case...
7780410 Method and apparatus for gas turbine engines  
A method of assembling a gas turbine engine includes providing at least one blade assembly. The method also includes forming at least one blade tip fuse within at least a portion of the at least...
7766603 Rotor blade containment assembly for a gas turbine engine  
A fan blade containment assembly (38) for a turbofan gas turbine engine (10) comprises a cylindrical, or frustoconical, casing (40) arranged to surround an arrangement of fan blades (26). At least...
7758301 Arrangement for detection of a shaft break in a gas turbine as well as gas turbine  
A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a...
7748948 Vortex-flow blower device  
A vortex-flow blower device includes an impeller having a plurality of fins, a blower housing that has a vortex flow chamber for accommodating the impeller and extends from a start point on a side...
7726286 Housing for a supercharger assembly  
A housing for a supercharger assembly is provided having an inner wall at least partially defining a rotor cavity. A layer is formed from a sacrificial polymeric material and is provided on at...
7713021 Fan containment casings and methods of manufacture  
A fan containment casing includes a core comprising a number of tows. The core has a central region and two end regions. The tows are grouped into a number of bands and form a number of...
7686570 Abradable coating system  
This invention relates to an abradable coating system for use in axial turbine engines. When coated onto a turbine ring seal segment the coating system may allow formation of an individualized seal...
7686571 Bladed rotor with shear pin attachment  
A stator vane assembly for a gas turbine engine, the stator vane including an airfoil portion formed from a single crystal material and two platforms attached to the ends of the airfoil by shear...
7604199 Aerofoil containment structure  
A stage of fan aerofoils (10) lies within a fan cowl (12). The fan duct (16) is defined in part by a hard casing (14) that in turn surrounds aerofoils (10). Hard casing (14) includes wedge members...
7565796 Turbofan case and method of making  
A casing for a gas turbine includes a construction providing improved structural efficiency. Improved load paths and means for transmitting loads in the engine case are disclosed.
7563069 Clip  
A clip used to attach an acoustic panel to a fan casing of a gas turbine engine is “U” shaped. One arm of the clip is provided with a spacing portion cut into the material of the arm and which may...
7527469 Transition-to-turbine seal apparatus and kit for transition/turbine junction of a gas turbine engine  
One embodiment of a transition-to-turbine seal (300) comprises a transition exit seal (302) adapted for fixed attachment to an exit rail (350) of a transition (109), and a stage-1 seal (340). The...
7517184 Low deflection fan case cotainment fabric  
A turbine engine fan casing for containing a separated blade fragment comprising a support case having an axially extending impact zone, a substantially structurally continuous penetrable covering...
7513103 Gas turbine engine assembly and methods of assembling same  
A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an...
7513734 Gas turbine engine blade containment system and a laminate material  
A gas turbine engine blade containment system that includes a laminate material including first and second layers. The first layer is an inner layer within the second layer. The second layer...
7484924 Device for limiting turbine overspeed in a turbomachine  
Device for limiting turbine overspeed in a turbomachine, the turbine comprising a rotor formed of disks mounted on a turbine shaft and carrying moving blades, stages of fixed blades disposed...
7448845 Gas turbine engine  
A turbofan gas turbine engine (10) comprises a fan rotor and a compressor rotor (62). The fan rotor (24) carries a plurality of circumferentially spaced radially outwardly extending fan blades...
7448844 Blisk having partially cut blade attachment  
An integrally bladed rotor disk, commonly referred to as an IBR or a blisk, includes partial cuts in the rotor disk extending from the rotor disk surface and along side the blades to form a partial...
7448808 Arrangement of bearing supports for the rotating shaft of an aircraft engine and an aircraft engine fitted with such an arrangement  
An arrangement of bearing supports for a rotating shaft mounted on bearings connected to an engine stator structure by bearing supports of which at least one is made up of N>1 elements effectively...
7445421 Fan duct blade containment assembly  
The fan cowl (12) of a ducted fan gas turbine engine (10) has a downstream portion including an inner casing (30) that surrounds a honeycomb structure (36) in abutting engagement. Honeycomb...
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