Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Hernan Victor Arrieta

Hans-Peter Borufka

Frank Stiehler

Peter Wiedemann

Joachim Lorenz

Patrick Prokopczuk

Klemens Hain

Paul Storm

Eberhard Knodel

Rolf Kleinstueck

Rolf KLEINSTÜCK

An integrally bladed rotor disk () for a turbine, including rotor blades (), which are joined in a substance-to-substance bond to a disk element (), and a sealing device () for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side () of the rotor disk () through openings () on the rotor disk () to a low-pressure side () of the rotor disk ().

Integrally bladed rotor disk for a turbine

A shroud for the rotating blades of a turbo machine, particularly a gas turbine, in which shroud is arranged along the circumference of a row of several rotating blades disposed on a rotor and has at least one separation gap along its circumference. The separation gap is formed in zigzag shape and has at least three damping gaps that are distanced from one another and extend at an angle relative to an axis of rotation of the rotor, and adjacent to these, has connection gaps each connecting damping gaps or extending the latter in the direction of shroud edges, wherein, when the rotor rotates, the gap width of damping gaps is reduced until the gap walls forming the damping gaps come to rest against each other.

Shroud for rotating blades of a turbo machine, and turbo machine

A turbine vane of a gas turbine, especially a gas turbine aircraft engine, is disclosed. The turbine vane includes a vane base body with an outer surface forming a suction side and a pressure side, the outer surface of the vane base body being at least partially coated with a thermal barrier coating. The thermal barrier coating extends continuously or uninterruptedly at least largely over the suction side and largely over the pressure side of the surface of the vane base body, with the layer thickness of the thermal barrier coating being variable or adjustable.

Turbine vane of a gas turbine

An apparatus and method for attaching a rotor blade to a rotor, particularly for a gas turbine, is disclosed. The rotor blade has a blade vane and a blade root, such that the blade vane can be attached to or anchored in the rotor by the blade root. The blade root is configured asymmetrically, such that the front region of the blade root as seen in the direction of rotation of the rotor blade is provided with more anchoring teeth than a rear region of the blade root as seen in the direction of rotation of the rotor blade.

Apparatus and method for attaching a rotor blade to a rotor

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Rzeszow, Poland

Hernan Victor Arrieta