Abstract: An assembly of a shaft and a rotor disk comprises a shaft configured to rotate at a first angular speed S1 about a shaft rotational axis. A bladed rotor includes a disk adapted to support blades, the disk having a rotor rotational axis, the disk being integrally and monolithically formed with at least one rotor gear, the rotor gear being concentric with the disk about the rotor rotational axis. A gear train includes a shaft gear fixed to the shaft, the gear train having at least one gear meshed with the rotor gear for imparting a rotation to the bladed rotor at angular speed S2, wherein the angular speed S1?the angular speed S2.

Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.

Abstract: A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet. The winglets therefore provide a wide trailing edge thereof to aerodynamically manage boundary layers and micro-shocks of a working fluid.

Abstract: 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.

Abstract: A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet. The winglets therefore provide a wide trailing edge thereof to aerodynamically manage boundary layers and micro-shocks of a working fluid.

Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.

Abstract: 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.

Abstract: A method of protecting a blade of a gas turbine engine by applying a nanocrystalline metal coating to a portion of the blade root is disclosed, which includes preparing at least a portion of a dovetail of the blade root for coating; and then applying a nanocrystalline metal coating to said portion.

Abstract: There is described a portable data transmission unit comprising a communications link for electrical connection to an aircraft engine to be maintained; an application coupled to a processor and configured for capturing in real time performance data indicative of a performance of the aircraft engine and making the performance data available for analysis upon landing of the aircraft, retrieving maintenance data related to the aircraft engine and performing maintenance operations on the aircraft engine; a user interface to display the maintenance data and receive input data, the maintenance operations performed on the aircraft engine directly through the data transmission unit using the input data and the maintenance data; a microphone to convert sound waves into an electric current; a speaker to convert analog audio signals into air vibrations to make audible sound; and a transceiver to transmit and receive in real time voice and data signals wirelessly across a network.

Abstract: There is described a portable data transmission unit comprising a communications link for electrical connection to an aircraft engine to be maintained; an application coupled to a processor and configured for capturing in real time performance data indicative of a performance of the aircraft engine and making the performance data available for analysis upon landing of the aircraft, retrieving maintenance data related to the aircraft engine and performing maintenance operations on the aircraft engine; a user interface to display the maintenance data and receive input data, the maintenance operations performed on the aircraft engine directly through the data transmission unit using the input data and the maintenance data; a microphone to convert sound waves into an electric current; a speaker to convert analog audio signals into air vibrations to make audible sound; and a transceiver to transmit and receive in real time voice and data signals wirelessly across a network.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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