A turbine engine that includes a stationary assembly, and a rotor assembly configured to rotate relative to the stationary assembly. The rotor assembly includes a plurality of unitary turbine and fan blades. Each unitary turbine and fan blade includes a single turbine airfoil, a single fan airfoil positioned radially outward from the single turbine airfoil, and a midspan shroud segment defined between the single turbine airfoil and the single fan airfoil.

According to an aspect, a system for a gas turbine engine includes a reduction gear train operable to drive rotation of a starter gear train that interfaces to an accessory gearbox of the gas turbine engine. The reduction gear train includes a starter interface gear that engages the starter gear train, a core-turning clutch operably connected to the starter interface gear, and a plurality of stacked planetary gear systems operably connected to the core-turning clutch and a core-turning input. The system also includes a mounting pad including an interface to couple a core-turning motor to the core-turning input of the reduction gear train.

The invention relates to a modular nozzle ring for a turbine stage of a continuous flow machine. The modular nozzle ring has a carrier system having an an adjustment ring, and a blade module having a blade leaf. The blade module is detachably connected to the carrier system. Furthermore, an adjustment angle of the blade leaf by the carrier system, in particular by the adjustment ring spaced apart from a flow channel, is specified, which adjustment angle is unchangeable during operation. The blade module is designed to be detachably pressed to a turbine housing part on the flow side, in particular by the adjustment ring. The invention furthermore relates to a blade module for a modular nozzle ring of a turbine stage and the use of a carrier system for a modular nozzle ring.

An engine inlet cover and a method for covering an engine inlet are provided. A method for covering an engine inlet includes providing a collapsible cover comprising a connection pin defining an axis; a frame including interconnected arms; and a web. Further, the method includes storing the collapsible cover in a stowed configuration in which the arms are aligned. Also, the method includes rotating the arms from the stowed configuration to an operating configuration in which the arms are radially spaced about the axis, enclosing the frame in the operating configuration with the web to define an interior volume, and placing the cover over the engine inlet.

A method includes joining a fuel plurality of injection components to a fuel manifold, wherein for each fuel injection component in the plurality of fuel injection components, a metallic joint is formed joining and sealing the fuel injection component to the manifold. A system includes a fuel manifold. A plurality of fuel injection components are connected in fluid communication with the fuel manifold with metallic joints sealing between each of the plurality of fuel injection components and the fuel manifold to prevent leakage from between the manifold and the plurality of fuel injection components.

A nozzle module includes a nozzle body having a blade shape in a cross section and extending in a radial direction, and a platform member integrally connected to each end portion of the nozzle body in the radial direction. The platform member includes a first portion formed on a first side in an axial direction in which a central axis extends, and having a pair of first side surfaces extending in the axial direction, when viewed in the radial direction, and a second portion formed to extend to a second side in the axial direction with respect to the first portion, and having a second side surface extending obliquely with respect to the first side surface, when viewed in the radial direction.

A gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides a spline for engaging the bearing package.

A method of disassembling a rotor module of a gas turbine engine. The gas turbine engine having a rotor output shaft. The rotor module having a centre-bolt, a sleeve, at least one rotor stage, at least one stator stage, a casing and an axis. The method having the steps: attaching a fixture to the at least one rotor stage, attaching the fixture to the casing, detaching the centre-bolt from the at least one rotor stage, detaching the sleeve from the output shaft, attaching the fixture to the sleeve, and removing the rotor module and fixture from the rotor output shaft. There is also presented a method of assembling the rotor module to the gas turbine engine and the apparatus used for disassembly and assembly.

A shroud segment including a forward radial wall, an aft radial wall and at least one interlocking subcomponent. The forward radial wall, an aft radial wall and the at least one interlocking subcomponent are each formed of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The shroud segment further including an interlocking mechanical joint joining each of the forward radial wall and the aft radial wall to the at least one interlocking subcomponent. Methods are also provided for joining the forward radial wall and the aft radial wall to the at least one interlocking subcomponent using an interlocking mechanical joint.

A rotary machine is provided. The rotary machine includes a rotor disk including a plurality of slots, a plurality of blades mounted on an outer circumferential surface of the rotor disk, each of the blades having a root part inserted into an associated one of the slots, and a retainer restraining axial movement of the plurality of blades, wherein the retainer includes an inner fixing member inserted into a bottom of the slot, an outer fixing member inserted into a lower surface of the root part to abut against the inner fixing member, and a spacer inserted between the outer fixing member and the bottom of the slot to prevent the outer fixing member from being separated.