Mtu Aero Engines Gmbh

Mtu Aero Engines Ag

Miu Aero Engines Gmbh

Erich Steinhardt

Werner Humhauser

Wilfried Smarsly

Thomas Uihlein

Reinhold Meier

André Werner

Manfred Feldmann

Hermann Klingels

Rudolf Stanka

Norbert Huebner

Hans-Peter Hackenberg

Karl Maar

Stefan Hagen Weber

Jochen Gier

Helmut Eibl

Klaus Peter Rued

Eckart Heinrich

Claus Riegler

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element () with which the blade element is arranged in a receptacle () of the turbomachine. in the region of the fastening element, the blade element has a core region () and an envelope region () which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

Ductile compensation layer for brittle components

A turbofan aircraft engine having a primary duct (C), including a combustion chamber (BK), a first turbine (HT) disposed downstream of the combustion chamber, a compressor (HC) disposed upstream of the combustion chamber and coupled (W) to the first turbine, and a second turbine (L) disposed downstream of the first turbine and coupled (W) via a speed reduction mechanism (G) to a fan (F) for feeding a secondary duct (B) of the turbofan aircraft engine. A square of a ratio of a maximum blade diameter (D) of the fan to a maximum blade diameter (D) of the second turbine is at least 3.5, in particular at least 4.

Turbofan aircraft engine

Disclosed is a blade element of a turbomachine, in particular of a gas turbine, which comprises a fastening element () with which the blade element is arranged in a receptacle () of the turbomachine. In the region of the fastening element, the blade element has a core region () and an envelope region () which at least partially envelops the core region. The core region is formed from a blade base material which is more brittle than the envelope material of the envelope region, and the envelope region is formed by a coating. The envelope material is a blade base material which has been modified to achieve a higher ductility or is a pseudoelastic or superelastic material.

A method for manufacturing an integrally bladed rotor (), in particular for a gas turbine, including the following method steps: preparing a rotor base member () having at least one first weld surface () and one blade () having a second weld surface (); positioning the rotor base member () and the blade () in such a way that a join zone () is formed between the first and second weld surface (); and filling the join zone () with metal powder () and the laser welding or electron beam welding of the metal powder (). An integrally bladed rotor () has a join zone () between the rotor base member () and blades (), the join zone () being filled with welded metal powder ().

Method for the production of an integrally bladed rotor, and rotor

The invention relates to a method for producing a blade tip plating () on a blade () for a turbomachine, in particular on a high-pressure rotating compressor blade for a gas turbine, comprising the following steps: &#x2014;producing a particle composite material () having embedded hard material particles (); &#x2014;placing the panicle composite material () on a solder () applied to the blade tip (); and&#x2014;healing the solder ().

Method for producing a blade plating on a blade for a turbomachine

A method is for manufacturing and/or repairing components, e.g., blades and blade segments, for gas turbines, e.g., for aircraft engines, by laser-powder build-up welding. Laser-powder build-up welding is performed using at least one substructure, the material build-up by a powder material occurring in the process of laser-powder build-up welding such that the or every substructure is at least in sections enclosed by the built-up powder material.

Method for manufacturing and/or repairing components for gas turbines

A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.

Method for producing gas turbine components

A static gas turbine component, especially for an aircraft engine, is formed at least partially region-wise of metal foam. An abradable shroud lining of metal foam and a carrier allow a radial through-flow of gas.

Gas turbine component

A lightweight, composite structural element for turbo engines, includes a thin metallic shell and a metallic core structure, of which a large proportion of the volume is empty space, the shell and the core structure being rigidly connected to each other. The core structure has a spatial, felt-like and/or mesh-like construction and is made of one or more wires, strips, shavings, or comparable elements. The core structure is sintered together, and sintered to the shell.

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Munich, Germany

Erich Steinhardt