Abstract: The epicyclic gear stage has a carrier body receiving the planet gears via corresponding planet bearings, a first bearing plane where a first axial end of the planet bearings are received by the carrier body, a second bearing plane where a second axial end of the planet bearings are received by the carrier body, a torque transfer body made integral to the carrier body externally to the sun gear, at a balanced torque transfer plane located between the first bearing plane and the second bearing plane, and extending away therefrom to a shaft coupler, for transferring torque between the carrier body and a shaft, and an oil network extending within the carrier, the oil network having an inlet in the torque transfer body, extending within the torque transfer body and into the carrier body, and extending within the carrier body and into the planet bearings.

Abstract: An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.

Abstract: An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.

Abstract: The epicyclic gear stage has a carrier body receiving the planet gears via corresponding planet bearings, a first bearing plane where a first axial end of the planet bearings are received by the carrier body, a second bearing plane where a second axial end of the planet bearings are received by the carrier body, a torque transfer body made integral to the carrier body externally to the sun gear, at a balanced torque transfer plane located between the first bearing plane and the second bearing plane, and extending away therefrom to a shaft coupler, for transferring torque between the carrier body and a shaft, and an oil network extending within the carrier, the oil network having an inlet in the torque transfer body, extending within the torque transfer body and into the carrier body, and extending within the carrier body and into the planet bearings.

Abstract: A heat exchanger defines an annulus divided by a plurality of radial plates extending longitudinal along the annulus, into a plurality of channels. A first group of the channels form an oil passage and a second group of channels form a fuel passage. The channels in the respective first and second groups are circumferentially alternately positioned one to another, and heat transfer from the oil passage to the fuel passage takes place through the radial plates.

Abstract: A gas turbine engine has a fuel system including an apparatus. The apparatus includes a housing containing at least a fuel filter assembly and a bypass valve assembly within the housing. The bypass valve assembly selectively opens or closes a bypass passage which bypasses a filtering unit of the fuel filter assembly. In accordance with one aspect, respective first and second fuel flows are introduced into the housing to be merged and mixed therein prior to entering the fuel filter assembly or the bypass valve assembly. In accordance with another aspect, an ice accretion device is provided within the housing to allow ice formation and accumulation thereon as a result of a transient icing occurrence when the mixed fuel flows in the housing pass through the ice accretion device to enter the fuel filter assembly.

Abstract: An air supply system is configured to provide cooling air with reduced heat pickup to a turbine rotor of a gas turbine engine. The system comprises a first cooling passage extending between a hollow airfoil and an internal pipe extending through the airfoil. The airfoil extends through a hot gas path. A second cooling passage extends through the internal pipe. The coolant flowing through the second cooling passage is thermally isolated from the airfoil hot surface by the flow of coolant flowing through the first cooling passage. The first and second cooling passages have a common output flow to a rotor cavity of the turbine rotor where coolant flows from the first and second cooling passages combine according to a predetermined ratio.

Abstract: A heat exchanger defines an annulus divided by a plurality of radial plates extending longitudinal along the annulus, into a plurality of channels. A first group of the channels form an oil passage and a second group of channels form a fuel passage. The channels in the respective first and second groups are circumferentially alternately positioned one to another, and heat transfer from the oil passage to the fuel passage takes place through the radial plates.

Abstract: An integrated mixer/TEC having structural features that may be individually used or combined to achieve a robust and durable design.

Abstract: A gas turbine engine has a fuel system including an apparatus. The apparatus includes a housing containing at least a fuel filter assembly and a bypass valve assembly within the housing. The bypass valve assembly selectively opens or closes s bypass passage which bypasses a filtering unit of the fuel filter assembly. In accordance with one aspect, respective first and second fuel flows are Introduced into the housing to be merged and mixed therein prior to entering the fuel filter assembly or the bypass valve assembly, in accordance with another aspect, an ice accretion device is provided within the housing to allow ice formation and accumulation thereon as a result of a transient icing occurrence when the mixed fuel flows in the housing pass through the ice accretion device to enter the fuel filter assembly.