Olver, Nobleton
Bryan Olver, Nobleton CA
Patent application number | Description | Published |
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20100229555 | Fuel manifold with reduced losses - A fuel conveying member of a gas turbine engine fuel system conducting pressurized fluid flow is provided. The fuel conveying member comprises a body defining an L-shaped fuel flow passage therein, the L-shaped passage including an elbow. The elbow portion provides a substantially smooth fluid-dynamic transition between portions of the passage upstream and downstream thereof. | 09-16-2010 |
20100278642 | BYPASS LIP SEAL - A cooling apparatus for cooling a fluid in a bypass gas turbine engine comprises a heat exchanger disposed within a bypass duct and accommodated by a sub-passage defined by a flow divider affixed to an annular wall of the bypass duct. The sub-passage defines an open upstream end and an open downstream end to direct a portion of the bypass air flow to pass therethrough. A sealing assembly for the bypass duct is also provided. | 11-04-2010 |
20120186257 | GAS TURBINE INTERNAL MANIFOLD MOUNTING ARRANGEMENT - A mounting method and system for supporting and positioning an internal fuel manifold relative to a combustor in a fuel injection system for a gas turbine engine. The method includes positioning the fuel manifold within a gas generator casing, applying a heat shield around a radially extending fuel inlet connected to the fuel manifold, and using the heat shield to at least partially support the fuel manifold within the gas generator casing. | 07-26-2012 |
20130164126 | HYBRID METAL/COMPOSITE LINK ROD FOR TURBOFAN GAS TURBINE ENGINE - The link rod can have a core portion supported inside an annular bypass duct with a bypass air passage extending radially therebetween, the link rod comprising a hot end fitting, a cold end, and an elongated and hollow strut body of composite material and having an aerodynamic cross-sectional shape, the strut body being secured to the hot end fitting and extending between the hot end fitting and the cold end, the hot end fitting having a metal body housing a spherical bearing mountable to the core portion, and the cold end housing a spherical bearing mountable to the bypass duct wall. | 06-27-2013 |
Bryan W. Olver, Nobleton CA
Patent application number | Description | Published |
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20080271433 | LOW PROFILE BLEED AIR COOLER - A bleed air cooler assembly of a gas turbine engine comprises a cooler body defining a fluid passage therein and a connector detachably affixed with the cooler body installed in an annular bypass air passage. | 11-06-2008 |
20090321585 | NACELLE INLET LIP - A nacelle inlet lip has a simplified geometry. The nacelle inlet lip has a constant cross-section all along a circumference thereof and is wholly concentric relative to the engine centerline, thereby allowing for the use of simple and economical manufacturing processes. | 12-31-2009 |
20100287950 | SUPPORT LINKS WITH LOCKABLE ADJUSTMENT FEATURE - A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus. | 11-18-2010 |
20100290903 | TURBOFAN MOUNTING SYSTEM - A gas turbine engine has a rear mounting assembly incorporating a mounting apparatus attached to a bypass duct wall with a link device for transferring core portion related inertia-induced loads, from an MTF of the core portion in a short circuit across an annular bypass air passage to the bypass duct wall. | 11-18-2010 |
Bryan William Olver, Nobleton CA
Patent application number | Description | Published |
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20100096511 | PROTECTIVE SADDLE MOUNT FOR CABLE TIE - A method and apparatus for providing a mounting system for an elongated item such as a cable, tube or wire, or an assembly of multiple cables, tube and/or wires. The mounting system includes an apparatus for mounting to a supporting structure, and an apparatus for receiving the elongated item. Also included is an apparatus for receiving a tying member such as a cable tie. Also included is an apparatus for permitting the tying member to be cut to release the elongate item from the mount without damage to the elongate item. | 04-22-2010 |
20100105266 | COMPOSITE FIRE SHIELD - A fire-critical aircraft or other component within a fire-risk zone includes a protective fire shield directly exposed to the fire-risk zone and separating the fire-critical component therefrom. The fire shield has an entirely composite construction composed of fibre cloth impregnated with a sacrificial resin which has a melting point that is below that of the fibre cloth. When exposed to fire, the fibre cloth remains substantially intact for at least the minimum period of time while the sacrificial resin is allowed to be at least partially consumed by the fire, such that the protective fire shield is partially sacrificed. | 04-29-2010 |
20120060508 | GAS TURBINE ENGINE BREATHER EXHAUST OIL COLLECTOR - A gas turbine engine oil system has an air-oil separator for removing air from an air/oil mixture. A breather tube is connected to an exhaust of the air-oil separator for receiving hot air removed from the air/oil mixture in the air-oil separator. The gas turbine engine oil separator exhaust is directed in a cooled oil collector to cause the oil mist remaining in the air at the exit from the engine air-oil separator to condensate. The oil condensate is returned back into the engine oil system. | 03-15-2012 |