Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

G4t Gmbh

Mtu Motoren-und Turbinen-union Munchen Gmbh

Mtu Motoren-und Turbinen-union Muenchen, Gmbh

Boehler Schmiedetechnik Gmbh & Co Kg

Montanuniversitaet Leoben

Gfe Metalle Unf Materialien Gmbh

Gfe Metalle Und Materialien Gmbh

Wilfried Smarsly

Martin Schloffer

Helmut Clemens

André Werner

Manfred Renkel

Erwin Bayer

Erich Steinhardt

Markus Fried

Axel Rossmann

Joachim Bamberg

Bertram Kopperger

Natividad Lopez Lavernia

Manfred A Daeubler

Andreas Otto

Thomas Goehler

Katrin Friedberger

Volker Guether

Sascha Kremmer

Gerhard Sauthoff

Raimund Lackermeier

Harald Chladil

Joerg Esslinger

Svea Mayer

Marc Haltrich

Al&eacute;xander Sagel

Wolfgang Track

Thomas Klein

Emanuel Schwaighofer

Described is a TiAl alloy which, besides titanium, comprises 42 to 48 at. % aluminum, 3 to 5 at. % niobium, 0.05 to 1 at. % molybdenum, 0.2 to 2.2 at. % silicon, 0.2 to 0.4 at. % carbon, 0.05 to 0.2 at. % boron, and optionally tungsten, zirconium and hafnium, as well as unavoidable impurities, and at room temperature has a microstructure which comprises globular colonies of lamellae of &#x3b1;-TiAl and &#x3b3;-TiAl, as well as silicide precipitates, and essentially no &#x3b2; phase. A method for producing a component made of this alloy is also described.

High temperature resistant TiAl alloy, production method therefor and component made therefrom

The invention relates to a blade for use in a turbine of an aircraft engine. The blade is made of (a) a Mo-based alloy strengthened by intermetallic silicides or (b) a Ni-based single crystal superalloy. An aircraft engine and in particular, a turbofan aircraft engine including a corresponding turbine blade is also disclosed.

Turbine blade and aircraft engine comprising same

Disclosed is a process for producing a component from a TiAl alloy by layer-by-layer deposition of powder on a substrate and/or an already produced semifinished product. The component has a proportion of x at % of aluminum which is in the range from about 34 to about 47 at % of aluminum, the powder having a proportion of x+1 at % to x+6 at % of aluminum. Also disclosed is a component formed from a TiAl alloy which has been produced by a corresponding process.

Additive manufacturing of high-temperature components from TiAl

Disclosed is a method for producing a blade for a turbomachine, in particular for an aero engine. The method comprises providing at least one blade airfoil with a first platform region and at least one blade root with a second platform region and joining the blade airfoil and the blade root at the respective platform regions by a friction welding method at a common joint region of the platform regions, the blade airfoil and the blade root being made of materials which are different from each other. Also disclosed is a blade which is and/or can be obtained by such a method.

Method for producing a blade for a turbomachine

The present invention relates to a TiAl alloy for use at high temperatures which has aluminum and titanium as main constituents. The TiAl alloy has an aluminum content of greater than or equal to 50 at. % and a matrix of &#x3b3;-TiAl and at least one phase of Al and Ti incorporated in the &#x3b3;-TiAl matrix which is different from &#x3b3;-TiAl, as well as depositions of oxides and/or carbides and/or silicides. In addition, the invention relates to a method for producing the alloy and to the use of the alloy for components of turbo-machines, in particular aircraft engines.

Al-rich high-temperature TiAl alloy

The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises

Method for producing a component from a composite material comprising a metal matrix and incorporated intermetallic phases

An apparatus and a process for producing forged components composed of TiAl alloys, wherein a melt of a TiAl alloy is provided and is cast by horizontal centrifugal casting so as to produce at least one semifinished TiAl cast part and the semifinished TiAl cast part is converted by forging into a forged TiAl part.

Process and apparatus for producing forged TiAl components

A component for a turbomachine having at least one region made of an intermetallic material which is formed from an intermetallic compound or comprises an intermetallic phase as the largest constituent. The intermetallic material is compacted and/or modified in microstructure by microplasticization at least partially at a surface or interface in a region close to the surface or interface.

TiAl blade with surface modification

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

The invention relates to a method for producing a component from a TiAl alloy, wherein the component is shaped by forging, in particular isothermal forging, and is subsequently subjected to at least one heat treatment, wherein in the first heat treatment the temperature is between 1100 and 1200&#xb0; C. and is maintained for 6 to 10 hours and then the component is cooled.

Method for producing forged components from a TiAl alloy and component produced thereby

The present invention relates to a process for producing a component, in particular a component for a turbomachine, composed of a TiAl alloy, which comprises the following:

Production process for TiAl components

Disclosed is a TiAl alloy for high-temperature applications which comprises not more than 43 at. % of Al, from 3 at. % to 8 at. % of Nb, from 0.2 at. % to 3 at. % of Mo and/or Mn, from 0.05 at. % to 0.5 at. % of B, from 0.1 at. % to 0.5 at. % of C, from 0.1 at. % to 0.5 at. % of Si and Ti as balance. Also disclosed is a process for producing a component made of this TiAl alloy and the use of corresponding TiAl alloys in components of flow machines at operating temperatures up to 850&#xb0; C.

Creep-resistant TiA1 alloy

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 running-in coating for a compressor housing is disclosed. The running-in coating has at least two layers where a first layer is dimensionally stable and at least one additional layer has run-in capability.

Apparatus and method for coating a compressor housing

A material for a gas turbine component, to be specific a titanium-aluminum-based alloy material, including at least titanium and aluminum. The material has a) in the range of room temperature, the &#x3b2;/B2-Ti phase, the &#x3b1;-TiAl phase and the &#x3b3;-TiAl phase with a proportion of the &#x3b2;/B2-Ti phase of at most 5% by volume, and b) in the range of the eutectoid temperature, the &#x3b2;/B2-Ti phase, the &#x3b1;-TiAl phase and the &#x3b3;-TiAl phase, with a proportion of the &#x3b2;/B2-Ti phase of at least 10% by volume.

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Munich, Germany

Wilfried Smarsly