Patent application number | Description | Published |
20090132111 | REAL-TIME AIRCRAFT MAINTENANCE TERMINAL - There is described a method for maintenance of an aircraft component, the method comprising: connecting electrically to the aircraft component via a maintenance terminal; retrieving maintenance data relating to the aircraft component using the maintenance terminal; performing maintenance operations on the aircraft component by entering data via a user interface on the maintenance terminal; and communicating in real time with a remote operator by transmitting and receiving at least one of voice signals and data signals wirelessly across a network via the maintenance terminal while performing the maintenance operations | 05-21-2009 |
20100101065 | Diffuser Case Removal Apparatus and Method - A method and apparatus is provided for removing a centrifugal compressor diffuser case from a turbofan gas turbine engine case which may be used while the engine is installed on an aircraft or when the engine has been removed from the aircraft. The tool includes movable gripping members at least one force member for exerting a pushing action on the engine structure on which the diffuser case is mounted the method includes gripping a peripheral portion of the diffuser case and applying an axial pushing force on the case relative to the engine case to thereby overcome an interference fit between the diffuser case and the engine case. | 04-29-2010 |
20100327588 | GAS TURBINE WITH MAGNETIC SHAFT FORMING PART OF A GENERATOR/MOTOR ASSEMBLY - A gas turbine engine including a first shaft being one of a main shaft concentrically mounted to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom, the first shaft having a reduced diameter portion located within the gas turbine engine, an electrical assembly having a rotor comprising permanent magnets retained on an outer surface of the reduced diameter portion and a stator comprising a magnetic field circuit disposed adjacent an outer periphery of the rotor, and an electrical connection between the magnetic field circuit and at least one of a power source and an electrically drivable accessory. | 12-30-2010 |
20100327589 | GAS TURBINE WITH WIRED SHAFT FORMING PART OF A GENERATOR/MOTOR ASSEMBLY - A gas turbine engine including an electrical assembly operable as at least one of an electric motor and a generator, with an electromagnetic rotor formed in part by a portion of one of a main shaft concentrically and drivingly connected to at least one turbine rotor and a tower shaft directly driven by the main shaft and extending generally radially therefrom. | 12-30-2010 |
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 |
20120304651 | INTEGRATED FUEL NOZZLE AND IGNITION ASSEMBLY FOR GAS TURBINE ENGINES - There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage. | 12-06-2012 |
20130224008 | NANO-METAL COATED VANE COMPONENT FOR GAS TURBINE ENGINES AND METHOD OF MANUFACTURING SAME - A method of manufacturing a vane component of a gas turbine engine is described, and includes forming a core of the vane component using a rapid manufacturing process, and applying a coating of nanocrystalline metal onto the core, the nanocrystalline metal fully encapsulating the core and defining an outer structural surface of the vane component. | 08-29-2013 |
20130255277 | GAS TURBINE ENGINE NOSE CONE - A nose cone for a turbofan gas turbine engine includes a central tip, an outer perimeter and a substantially conical outer wall extending therebetween which encloses a cavity therewithin. The outer wall includes an inner substrate layer facing the cavity and an outer layer which overlies and at least partially encloses the inner substrate layer. The outer layer is composed entirely of a nanocrystalline metal forming an outer surface of the nose cone. | 10-03-2013 |
20130276285 | DIFFUSER CASE REMOVAL APPARATUS AND METHOD - A method and apparatus is provided for removing a centrifugal compressor diffuser case from a turbofan gas turbine engine case which may be used while the engine is installed on an aircraft or when the engine has been removed from the aircraft. The tool includes movable gripping members at least one force member for exerting a pushing action on the engine structure on which the diffuser case is mounted the method includes gripping a peripheral portion of the diffuser case and applying an axial pushing force on the case relative to the engine case to thereby overcome an interference fit between the diffuser case and the engine case. | 10-24-2013 |
20140150550 | METHOD AND SYSTEM FOR INTEGRATING GAS TURBINE TRIM BALANCING SYSTEM INTO ELECTRONIC ENGINE CONTROLS - Methods and systems for determining a rebalancing strategy for trim balancing one or more rotational components of a gas turbine. One or more noise, acoustics or vibrational signals may be received at a control device of an aircraft comprising the gas turbine engine while the aircraft is in operation. The one or more noise, acoustics or vibrational signals may be used for determining a rebalancing strategy for one or more unbalanced rotational components. | 06-05-2014 |
20140238038 | GAS TURBINE VARIABLE FOCUS LASER IGNITION - A laser ignition system for a gas turbine engine includes a combustion chamber. The system comprises a laser source for generating a continuous laser beam during an ignition process of the combustion chamber; and a dynamic laser focus apparatus positioned outside of the combustion chamber and focusing the laser beam into a continuously varying focal point to generate a laser kernel moving within a spray of air/fuel mixture injected into the combustion chamber. | 08-28-2014 |
20150017324 | METHOD OF APPLYING A NANOCRYSTALLINE COATING TO A GAS TURBINE ENGINE COMPONENT - A method of applying a nanocrystalline metal coating to a titanium or titanium alloy blade of a gas turbine engine is described. The method includes selecting an intermediate bond coat from the group consisting of nickel, nickel alloy, P, B, Tl and combinations thereof, and applying the intermediate bond coat to at least a portion of the blade. A nanocrystalline metal coating having an average grain size of between 10 nm and 500 nm is then applied to the portion of the blade overtop of the intermediate bond coat. | 01-15-2015 |