| Patent application number | Description | Published |
|---|
| 20080240917 | 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. | 10-02-2008 |
| 20090136348 | VIBRATION DAMPING OF A STATIC PART USING A RETAINING RING - A retaining ring is mounted in frictional engagement with a static gas turbine engine part, such as a compressor shroud, in order to provide frictional damping. | 05-28-2009 |
| 20100209251 | FAN BLADE PLATFORM - A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub. | 08-19-2010 |
| 20120082541 | GAS TURBINE ENGINE CASING - An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine. | 04-05-2012 |
| 20120082551 | GAS TURBINE BLADE AND METHOD OF PROTECTING SAME - An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed. | 04-05-2012 |
| 20120082553 | METAL ENCAPSULATED STATOR VANE - A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating. | 04-05-2012 |
| 20120082556 | NANOCRYSTALLINE METAL COATED COMPOSITE AIRFOIL - An airfoil for a gas turbine engine comprising a root, a tip, and leading and trailing edges extending between the root and the tip. The airfoil has a non-metallic core which is composed of a composite material, and a metallic coating disposed on at least a portion of the composite core, such as along the leading edge of the airfoil for example. The metallic coating is composed of a nanocrystalline metal, and forms an outer surface of the portion of the airfoil onto which the coating is applied. | 04-05-2012 |
| 20120082559 | AIRFOIL BLADE - A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core. | 04-05-2012 |
| 20120082783 | METHOD OF APPLYING A NANOCRYSTALLINE COATING TO A GAS TURBINE ENGINE COMPONENT - A method of applying a nanocrystalline coating to a gas turbine engine component is described. The method comprises the steps of applying an intermediate bond coat to at least a portion of the component, and then applying the nanocrystalline coating to at least the portion of the component overtop of the intermediate bond coat. The component may include, for example, a blade of which a dovetail portion of the blade root is protected by applying the intermediate bond coat and the nanocrystalline coating thereto. | 04-05-2012 |
| 20120134777 | ENGINE CASE WITH WASH SYSTEM - A gas turbine engine includes a structure defining a circumferential passage in fluid communication with an internal passage in at least one strut radially extending into the engine, circumferential passage also in fluid communication with a plurality or nozzles or jets to provide a wash manifold integrated with the engine casing structure. One or more nozzles are provided in the manifold for directing a washing fluid injected into the duct. | 05-31-2012 |
| 20120216506 | GAS TURBINE ENGINE RECUPERATOR WITH FLOATING CONNECTION - A gas turbine engine recuperator including a plurality of independent arcuate segments, each segment having an inlet connection member designed to sealingly engage a plenum in fluid flow communication with the compressor discharge, and an outlet connection member designed to sealingly engage a plenum containing the combustor. One of the inlet and outlet connection members is a rigid member forming a rigid connection to the respective plenum, and the other of the inlet and outlet connection members includes a flexible member and forms a floating connection to the respective plenum, the floating connection allowing relative movement between the segment and a remainder of the gas turbine engine. | 08-30-2012 |
| 20120216543 | DIFFUSING GAS TURBINE ENGINE RECUPERATOR - A gas turbine engine recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust inlet having a smaller cross-sectional area than that of the exhaust outlet, and a cross sectional area of each exhaust passage progressively increasing from the exhaust inlet to the exhaust outlet such as to diffuse the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and provide fluid flow communication between an air inlet and an air outlet designed to sealingly engage respective plenums of the gas turbine engine. | 08-30-2012 |
| 20120216544 | SWIRL REDUCING GAS TURBINE ENGINE RECUPERATOR - A gas turbine engine recuperator recuperator including exhaust passages providing fluid flow communication between an exhaust inlet and an exhaust outlet, the exhaust inlet being oriented to receive exhaust flow from a turbine of the engine and the exhaust outlet being oriented to deliver the exhaust flow to atmosphere, the exhaust passages having an arcuate profile in a plane perpendicular to a central axis of the recuperator to reduce a swirl of the exhaust flow. Air passages are in heat exchange relationship with the exhaust passages and providing fluid flow communication between an air inlet and an air outlet, design to sealingly respective plenum of the gas turbine engine. | 08-30-2012 |
| 20120251313 | APPARATUS AND METHOD FOR GAS TURBINE ENGINE VANE RETENTION - A vane assembly of a gas turbine engine has a plurality of vanes extending radially and inwardly from an annular casing. An outer end of each vane radially and outwardly projects from the casing and is received in one of apertures defined in an elastomeric ring which is placed around the casing. A strap of a non-metallic material is placed in a pre-tensioned condition around the elastomeric ring to compress the elastomeric ring and to radially retain the outer end of each vane. | 10-04-2012 |
| 20120308362 | DUAL INPUT DRIVE AGB FOR GAS TURBINE ENGINES - A mechanical drive system of an aircraft gas turbine engine includes a tower shaft operatively connected to first and second shafts in an accessory drive gearbox. The first shaft rotates at a rotational speed lower than the rotational speed of the tower shaft and the second shaft rotates at a rotational speed equal to or higher than the rotational speed of the tower shaft. | 12-06-2012 |
| 20130014513 | CONNECTION FOR GENERATOR IN A GAS TURBINE ENGINEAANM Barnett; BarryAACI MarkhamAACO CAAAGP Barnett; Barry Markham CAAANM Alecu; DanielAACI TorontoAACO CAAAGP Alecu; Daniel Toronto CAAANM Eleftheriou; AndreasAACI WoodbridgeAACO CAAAGP Eleftheriou; Andreas Woodbridge CA - A gas turbine engine having an electric generator includes a transmission shaft extending along a longitudinal axis of the engine and drivingly interconnecting a turbine shaft of the engine and a rotor shaft of the electric generator. The transmission shaft is engaged by splined mating connections with the turbine shaft and the rotor shaft. The transmission shaft has a shear neck defining a reduced radial wall thickness with respect to a remainder of the transmission shaft such as to provide a weakened region of the transmission shaft. An annular support structure, concentric with and surrounding the transmission shaft, is axially located between the shear neck and a forward end of the transmission shaft engaged to the turbine shaft, and includes a bearing operable to rotationally support the transmission shaft. | 01-17-2013 |
| 20130058778 | FABRICATED INTERMEDIATE CASE WITH ENGINE MOUNTS - A fabricated engine case has a plurality of circumferentially spaced struts radially extending between an outer case and an inner case. A mount apparatus is affixed to the outer case of the engine case. The mount apparatus is a mount base radially spaced apart from a circumferential skin of the outer case and a load bearing member extending radially inwardly to connect the mount base to an outer end of one of the struts. | 03-07-2013 |
