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A method of swing on a swing is disclosed, in which a user positioned on a standard swing suspended by two chains from a substantially horizontal tree branch induces side to side motion by pulling alternately on one chain and then the other.
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| Number | Title | Issue Date |
| 8186934 | Casing assembly Provision of panels within casings can cause problems where retaining bolts require apertures in the casings, which in turn may reduce the structural strength of that casing. By providing a ring within the casing and appropriate retainer elements secured to that rin... | 05/29/2012 |
| 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 material compositions each include one or more isotopes of the same e... | 03/20/2012 |
| 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 includes: a casing (7) formed in a cylindrical shape; a beari... | 03/06/2012 |
| 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 structure or a net encompasses the engine casing and the blade failu... | 01/03/2012 |
| 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 the contact section extending radially outwardly from a centerline an... | 01/03/2012 |
| 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 carrying a layer of abradable material, the laminated structure compris... | 11/22/2011 |
| 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 circular ring-shaped outer wall, a circular ring-shaped inner wall, which ... | 11/22/2011 |
| 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, a sandwich structure including a first facesheet and a second facesh... | 11/22/2011 |
| 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 propelling means being controlled... | 11/15/2011 |
| 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 casing liner member. A septum is interposed between the radially inner and... | 10/04/2011 |
| 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 take-up spool, and transferring the core layer material to a cylindr... | 09/20/2011 |
| 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 containing region of the fan case is a load spreader layer for initially recei... | 09/13/2011 |
| 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 material (24) lining honeycomb structure ( | 06/14/2011 |
| 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 failure. In use, ice may be released from a fan blade in a first direc... | 03/29/2011 |
| 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 fan blade containment assembly ( | 01/11/2011 |
| 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 on one surface of the blade is dissipated through the foam and transmi... | 09/14/2010 |
| 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 of destruction of the ice strike sheathing ring due to e... | 08/24/2010 |
| 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 (11), especially a low pressure turbine, is positioned downst... | 08/24/2010 |
| 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 one hollow tubular member (66) is ... | 08/03/2010 |
| 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 of a the fluid inlet port to an end point on a side of a fluid discha... | 07/06/2010 |
| 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 filament-wound radially disposed layers. The bands of tows are interleaved as a ... | 05/11/2010 |
| 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 pins that fit within slots formed between the platform and airfoil. The... | 03/30/2010 |
| 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 between turbine blade disks and the surrounding ring seal without ca... | 03/30/2010 |
| 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 be bent to define the spacing between the outer face of the arm a... | 07/21/2009 |
| 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 stage-1 seal (340) comprises... | 05/05/2009 |
| 7524161 | Gas turbine engine blade containment assembly A gas turbine engine rotor blade containment assembly (38) comprises a generally cylindrical, or frustoconical, metal casing (40). The metal casing (40) has at least one arched portion (62,64,66) and each arched portion (62,64,66) ... | 04/28/2009 |
| 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 includes a plurality of resiliently compressive springs extending transvers... | 04/07/2009 |
| 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 between the disks of the rotor, and means for shearing the moving blades of... | 02/03/2009 |
| 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 (26). The compressor rotor carries a pluralit... | 11/11/2008 |
| 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 root portion below each blade. A damaged blade can be removed from t... | 11/11/2008 |
| 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 structure (36) is made up of a number of ... | 11/04/2008 |
| 7416380 | Pressure relief arrangement for a pump A pressure relief arrangement for a pump (10) which includes a pump housing assembly with a pumping chamber (25) therein, the pump housing assembly including a section (41) mounted for movement between a normal operating position and a venting p... | 08/26/2008 |
| 7407367 | Variable area diffuser A diffuser includes multiple vanes rotatable about pivot pins between multiple positions. A mounting plate supports a backing plate. The vanes are arranged between the backing plate and the shroud. The pivot pins are in a slip fit relationship with the backing plate... | 08/05/2008 |
| 7402022 | Rotor blade containment assembly for a gas turbine engine A gas turbine engine rotor blade containment assembly (38) comprising a generally cylindrical, or frustoconical, casing (40). The casing (40) having at least one member (54) and the member (54) has a first portion (53) exten... | 07/22/2008 |
| 7390161 | Composite containment case for turbine engines A composite fan casing for a gas turbine engine includes, in an exemplary embodiment, a core having a plurality of core layers of reinforcing fiber bonded together with a thermosetting polymeric resin. Each core layer includes a plurality of braided reinforcing fibe... | 06/24/2008 |
| 7367774 | System for protecting a main shaft of an engine having a fusible bearing A turbomachine comprising at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the shaft, one of the bearings being capable of giving way when an unbalance occurs in the rotary assembly, at lea... | 05/06/2008 |
| 7364402 | Turbine module for a gas turbine engine A turbine module for a gas turbine engine includes at least one turbine disk and a disk-shaped component mounted on the turbine disk upstream relative to the gas flow. The module can be assembled to the compressor of the engine, wherein the component is preassembled... | 04/29/2008 |
| 7360986 | System for blocking a main shaft of an engine having a fusible bearing A turbomachine including at least a first rotary assembly with a first shaft, a stator, and bearings secured to the stator and suitable for supporting the first shaft, one of the bearings being capable of giving way when an unbalance occurs in the first rotary assem... | 04/22/2008 |
| 7340882 | Turbomachine with means for axial retention of the rotor The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support el... | 03/11/2008 |
| 7341423 | Molecular pump and connecting device A flange of a molecular pump is connected to a vacuum vessel by first bolts that extend through elongate holes in the flange and are bolted to the vacuum vessel. One or more buffering members are attached to the flange by the first bolts that extend through first op... | 03/11/2008 |
