A power takeoff and gearbox system of a multi-spool gas turbine engine includes a low rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, and a high rotor towershaft operably connected to and driven by a second spool of the gas turbine engine. The high rotor towershaft and the low rotor towershaft are concentric and extend to a common gearbox housing.

A core engine includes a first tierod and a compressor rotor assembly including a plurality of compressor rotor disks arranged in a face to face orientation and spaced along the first tierod. The core engine includes a second tierod and a turbine rotor assembly including a plurality of turbine rotor disks arranged in a face to face orientation and spaced along the second tierod. The compressor rotor assembly is aft of the turbine rotor assembly.

A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.

A turbine engine that includes an engine casing including a fluid supply plenum, a mating surface, and a nozzle supply passage and a cavity flow passage that both extend between the fluid supply plenum and the mating surface. The turbine engine further includes a turbine nozzle assembly including a mating band. The mating band includes an inlet scoop in flow communication with the nozzle supply passage. An interface is defined between the mating band and a first portion of the mating surface, and a band cavity is defined between the mating band and a second portion of the mating surface. The cavity flow passage couples the fluid supply plenum in flow communication with the band cavity.

The Modular turbo compressor shaft (4) comprise a tubular bearing portion (5) having a first axial end portion and a second axial end portion; an impeller portion (6) arranged at the first axial end portion of the tubular bearing portion (5); and a driving portion (7) arranged at the second axial end portion of the tubular bearing portion (5). The tubular bearing portion (5) is made of a hard material, and the impeller portion (6) and/or the driving portion (7) are made of relatively soft material compared to the hard material of the tubular bearing portion (5). The impeller portion (6) and/or the driving portion (7) are at least partially extending into the tubular bearing portion (5) and are firmly connected to the tubular bearing portion (5). The tubular bearing portion (5), the impeller portion (6) and the driving portion (7) are configured such that radial deformations, occurring during assembly of the impeller portion (6) and/or the driving portion (7) to the tubular bearing portion (5), are substantially limited to the driving portion (7) and/or the impeller portion (6).

The invention relates to a plain bearing device having a primary sliding surface between a first pair of concentrically arranged structural elements, wherein, in a normal operating state, a relative rotational movement between the structural elements along the primary sliding surface is possible, characterized by at least one secondary sliding surface between a second pair of concentrically arranged structural elements, wherein a coupling means, in the normal operating state, prevents a relative rotational movement between the second pair of structural elements, and wherein, if a predeterminable event occurs, the coupling means is automatically releasable, such that a relative rotational movement between the second pair of structural elements along the at least one secondary sliding surface is made possible. The invention furthermore relates to a method for operating a plain bearing device, and to a gas turbine engine.

In accordance with one aspect of the disclosure, a stream diverter for a gas turbine engine is disclosed. The stream diverter may include a first air duct, a second air duct, a third air duct, and a door operatively associated with the second and third air ducts of the gas turbine engine. The door may have at least an open position allowing air from the second air duct to flow into the third air duct and a closed position preventing air from flowing between the ducts.

An auxiliary gearbox has a low speed input shaft driving a first plurality of accessories. A high speed input shaft drives a second plurality of accessories. The first plurality of accessories rotating about a first set of rotational axes, which are parallel to each other and perpendicular to a first plane. The second plurality of accessories rotating about a second set of rotational axes, which are parallel to each other and perpendicular to a second plane. The first and second planes extending in opposed directions away from a drive input axis of the high speed input shaft and the low speed input shaft. The low speed input shaft drives a variable speed transmission. A gas turbine engine is also disclosed.

A gas turbine includes a compressor rotor having a plurality of compressor rotor disks installed therein; a turbine rotor having a plurality of turbine rotor disks installed therein; a connection part connecting the compressor rotor and the turbine rotor to each other; a tie rod extended through the central axes of the plurality of compressor rotor disks and the central axes of the plurality of turbine rotor disks; and a clamping member forced onto the tie rod in the an axial direction of the tie rod so as to be rotated with the tie rod, and relatively rotated with respect to the an inner circumferential surface of the connection part, thereby damping vibration and shock.

A gas turbine engine system and method of operating gas turbine engines are provided. The gas turbine engine assembly includes a gas turbine engine includes a power shaft configured to rotate about an axis of rotation. The gas turbine engine assembly also includes a first fan and a second fan coupled to the power shaft coaxially with the gas turbine engine. The gas turbine engine assembly also includes a first fan duct configured to direct a first stream of air to the first fan. The gas turbine engine assembly also includes a second fan duct configured to direct a second stream of air to the second fan. The gas turbine engine assembly also includes an exhaust duct configured to direct a stream of exhaust gases of the gas turbine engine in a direction of the axis of rotation.