Mtu Aero Engines Ag

Daniel Theurich

Hans-Peter Hackenberg

Michael Junge

Martin Pernleitner

Manfred Dopfer

Wilfried Schuette

Alexander Halcoussis

Axel Stettner

Hannes Wolf

Martin Becker

Knut Werner

Wolfgang Horn

Wilfried Schütte

The disclosure is directed to a method comprising the steps: carrying out multiple measurements on a mechanical object, the measurements each differing by one or more parameters influencing the measurement; determining a spectrogram on the basis of the measurement data of the measurements and depending on a predefined parameter of the mechanical object; determining one or more excitations of the mechanical object; reproducing the excitations in the spectrogram.

Method, device, and graphical user interface for analysing a mechanical object

A rotor assembly may be used in a gas turbine. The rotor assembly includes rotor segments arranged in succession in an axial direction and interconnected in the axial direction by a tie-rod, and a rotor segment disposed forwardly in the axial direction having a first contact surface and a rotor segment disposed rearwardly in the axial direction having a second contact surface. The first and second contact surfaces are at least partially in contact with each other, are substantially annular in shape, and extend in a radial direction and in a circumferential direction. The first contact surface and/or the second contact surface extend at least partially obliquely relative to the radial direction. An angle is formed between the first contact surface and the second contact surface when viewed in a sectional plane defined by the axial direction and the radial direction.

Rotor arrangement for a gas turbine with inclined axial contact surfaces formed on rotor segments, gas turbine and aircraft gas turbine

A blade () for a turbomachine is provided. The blade () includes an airfoil () having at least one thickening () on a pressure side () of the airfoil (). The thickening () has a region (B) of constant thickness (D). A turbomachine, a compressor and a turbine having stator vanes and/or rotor blades including at least one such blade () is also provided.

Blade for a turbomachine

The invention relates to a blade for a turbomachine, comprising a blade element with a suction side and a pressure side, which extend between a leading edge and a trailing edge of the blade element, as well as a blade root for connection of the blade at a main rotor body, wherein the blade comprises a crack-affecting device, which, in the radial direction, has an altered cross-sectional geometry in comparison to an aerodynamically optimized blade profile. The invention further relates to a rotor for a turbomachine having at least one such blade, a turbomachine having at least one such blade, and/or with such a rotor as well as a method for producing a blade.

Blade and rotor for a turbomachine and turbomachine

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Stockdorf, Germany

Daniel Theurich