Abstract: The disclosure provides a powerplant for an aircraft comprising: at least two gas turbine engines, and at least one closed-cycle arrangement for recuperating heat from the at least two gas turbine engines and supplying power to at least one power-demanding system, wherein the closed-cycle arrangement comprises: a closed circuit channeling a working fluid subjected to a thermodynamic cycle; at least one pre-cooler configured to transfer heat from the working fluid to a heat sink; the heat sink in thermal communication with the pre-cooler, the heat sink being a fuel tank and/or an airframe surface; at least one pumping element configured to move the working fluid through the closed circuit; at least two primary heat exchangers, each one configured to transfer heat from a respective gas turbine engine to the working fluid; at least one expanding element configured to drive a gearbox and an output shaft by the expansion of the working fluid; wherein the output shaft driven by the expanding element is connected to

Abstract: A bladed rotor wheel of an aero turbine stage includes a portion of a rotor blade with a shank portion and a bottom surface; a portion of a forged rotor disk with a rim portion and an outer surface; and a joining structure provided by an additive manufacturing process configured for integrally merging the portion of a rotor blade with the portion of a forged rotor disk. An aero turbine can include such bladed rotor wheel, and an aircraft can include such aero turbine.

Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

Abstract: The disclosure provides a powerplant for an aircraft comprising: at least two gas turbine engines, and at least one closed-cycle arrangement for recuperating heat from the at least two gas turbine engines and supplying power to at least one power-demanding system, wherein the closed-cycle arrangement comprises: a closed circuit channeling a working fluid subjected to a thermodynamic cycle; at least one pre-cooler configured to transfer heat from the working fluid to a heat sink; the heat sink in thermal communication with the pre-cooler, the heat sink being a fuel tank and/or an airframe surface; at least one pumping element configured to move the working fluid through the closed circuit; at least two primary heat exchangers, each one configured to transfer heat from a respective gas turbine engine to the working fluid; at least one expanding element configured to drive a gearbox and an output shaft by the expansion of the working fluid; wherein the output shaft driven by the expanding element is connected to

Abstract: A bladed rotor wheel of an aero turbine stage includes a portion of a rotor blade with a shank portion and a bottom surface; a portion of a forged rotor disk with a rim portion and an outer surface; and a joining structure provided by an additive manufacturing process configured for integrally merging the portion of a rotor blade with the portion of a forged rotor disk. An aero turbine can include such bladed rotor wheel, and an aircraft can include such aero turbine.

Abstract: A method of determining a life defining quantity of a production component manufactured by an additive manufacturing process. The method includes the step of defining a plurality of components to be manufactured by an additive manufacturing technique. The plurality of components has a first test piece and a first production component. The method further includes manufacturing the components in the same manufacturing batch using an additive manufacturing process and with nominally the same material composition and build parameters. A characteristic mechanical property of the first test piece is then determined. The method further includes determining a value of a life defining quantity of the first production component as a function of the first test piece characteristic mechanical property. The first production component and first test piece are then provided with indicators which associate the first production component with the determined life defining quantity.

Abstract: The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

Abstract: An annular combustion chamber wall arrangement includes an annular wall and a plurality of tiles and each tile is secured to and is spaced from a further annular wall. The first surface of each tile faces the annular wall and the second surface of each tile faces away from the annular wall. Each tile has a plurality of pedestals extending away from the first surface towards the annular wall and/or a plurality of effusion cooling apertures extending through the tile from the first surface to the second surface. At least one of the tiles has the pedestals and/or the effusion cooling apertures arranged in a predetermined pattern which provides the tile with a more uniform stiffness in all directions to reduce the possibility of cracking of the tile. In one predetermined pattern the pedestals are arranged in a Fermat's (parabolic) spiral with the pedestals arranged with Fibonacci number ordering.

Abstract: A method of determining a life defining quantity of a production component manufactured by an additive manufacturing process. The method includes the step of defining a plurality of components to be manufactured by an additive manufacturing technique. The plurality of components has a first test piece and a first production component. The method further includes manufacturing the components in the same manufacturing batch using an additive manufacturing process and with nominally the same material composition and build parameters. A characteristic mechanical property of the first test piece is then determined. The method further includes determining a value of a life defining quantity of the first production component as a function of the first test piece characteristic mechanical property. The first production component and first test piece are then provided with indicators which associate the first production component with the determined life defining quantity.

Abstract: A method for manufacturing a number of gas turbine components includes selecting material for manufacturing a number of components, making at least one coupon of the material for testing of material properties, determining at least one required material property, a target value of the property and an acceptable deviation from the target value, testing the at least one determined material property of the coupon, associating each component, which is made of the selected particular material, with the at least one material property of the coupon, comparing the testing result of the property with the required material property, and rejecting components, the associated at least one property of which do not fulfil the acceptable deviation of the required value of the material property.

Abstract: The remaining serviceable life of a critical rotating component of a gas turbine engine can be predicted using a remote detection component. The remote detection component is inspected to determine whether a crack has formed at a dedicated crack-initiation feature. If a crack has formed, a known correlation between the remote detection component and the critical rotating component is used to estimate the remaining serviceable life of the critical rotating component. Because the detection component is remote from the critical component, there is no risk of failure of the critical component.

Abstract: An annular combustion chamber wall arrangement includes an annular wall and a plurality of tiles and each tile is secured to and is spaced from a further annular wall. The first surface of each tile faces the annular wall and the second surface of each tile faces away from the annular wall. Each tile has a plurality of pedestals extending away from the first surface towards the annular wall and/or a plurality of effusion cooling apertures extending through the tile from the first surface to the second surface. At least one of the tiles has the pedestals and/or the effusion cooling apertures arranged in a predetermined pattern which provides the tile with a more uniform stiffness in all directions to reduce the possibility of cracking of the tile. In one predetermined pattern the pedestals are arranged in a Fermat's (parabolic) spiral with the pedestals arranged with Fibonacci number ordering.

Abstract: The remaining serviceable life of a critical rotating component of a gas turbine engine can be predicted using a remote detection component. The remote detection component is inspected to determine whether a crack has formed at a dedicated crack-initiation feature. If a crack has formed, a known correlation between the remote detection component and the critical rotating component is used to estimate the remaining serviceable life of the critical rotating component. Because the detection component is remote from the critical component, there is no risk of failure of the critical component.

Abstract: The remaining serviceable life of a component of a gas turbine engine can be predicted by monitoring one or more topographical features of the component which are arranged so as to cause a non-hazardous crack to be initiated at one or more of the topographical features during the course of operation of the gas turbine engine.