Rolls-royce Deutschland Ltd & Co. Kg

Christoph Klaus

Jonas Schwengler

Konstantinos Emmanouil

Maik Gude

Sebastian Spitzer

Reyya Nitin Rao

The invention relates to a component of a gas turbine engine which has a fiber-composite material having a multiplicity of rovings, wherein at least one roving of the fiber-composite material along the spatial extent thereof has a variable cross section, at least two rovings have in each case a dissimilar cross section and/or the at least one roving follows a variable direction and the at least one roving is deposited by means of tailored fiber placement. The invention also relates to a method of a component.

Part of a gas turbine engine and method for the manufacturing the part

A reduction gearbox which has: an input, which can be coupled to an input shaft, which has an input speed; an output, which rotates at an output speed that is lower than the input speed; and at least one statically arranged component. It is envisaged that an electric generator is integrated into the reduction gearbox, said generator comprising a rotor and a stator, wherein the rotor of the electric generator is coupled to the output of the reduction gearbox, and the stator of the electric generator is coupled to a statically arranged component of the reduction gearbox.

Reduction gearbox

An intermediate-casing structure for a compressor in a gas turbine engine, in particular an aircraft engine, having a plurality of components including at least one static blade row for deflecting at least one airflow entering the intermediate-casing structure, and at least one ring, on which the blade rows are radially arranged, characterized in that at least one first component of the intermediate-casing structure is formed from composite material, in particular fiber-composite material, or exhibits composite material, and at least one second component of the intermediate-casing structure is formed from metal or exhibits metal. Furthermore, the invention relates to a gas turbine device.

Intermediate casing for a compressor in a gas turbine engine and a gas turbine engine

A jet engine with a chamber which is delimited by a housing and inside of which a rotatable appliance that can be impinged by hydraulic fluid is arranged, wherein hydraulic fluid and air introduced through the housing into the chamber can be discharged from the chamber. In the area through which air and hydraulic fluid can be discharged from the chamber, the housing is embodied with a separating appliance in the area of which air and hydraulic fluid can be separated from each other, and/or a deflector appliance, by means of which air, hydraulic fluid and/or an air-oil mixture in the chamber can be guided in the direction of the area in a targeted manner, is provided upstream of the area of the housing.

Jet engine with a chamber

A gas turbine engine comprising a gearbox, the gearbox comprising a sun gear, an annulus gear, a plurality of planet gears and a carrier, each planet gear being rotatably mounted in the carrier by at least one bearing, the sun gear meshing with the planet gears and the planet gears meshing with the annulus gear, the sun gear, the planet gears and the annulus gear comprising gear teeth, the annulus gear having a length in the axial direction and an axially forward end and an axially rearward end and wherein the annulus gear is resiliently mounted to a supporting structure at both its axially forward and axially rearward ends.

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Teltow, Germany

Christoph Klaus