Mtu Aero Engines Ag

Mtu Aero Engines Gmbh

Boehler Schmiedetechnik Gmbh & Co Kg

Montanuniversitaet Leoben

Gfe Metalle Unf Materialien Gmbh

Gfe Metalle Und Materialien Gmbh

Montanuniversitat Leoben

Böhler Schmiedetechnik Gmbh & Co Kg

Helmut Clemens

Wilfried Smarsly

Martin Schloffer

Andreas Otto

Wilfried Wallgram

Volker Guether

Sascha Kremmer

Svea Mayer

Harald Chladil

Emanuel Schwaighofer

Thomas Klein

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 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

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

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.

Material for a gas turbine component, method for producing a gas turbine component and gas turbine component

A method for producing a component of a titanium-aluminum base alloy comprising hot isostatically pressing the alloy to form a blank, subjecting the blank to a hot forming by a rapid solid-blank deformation, followed by a cooling of the component to form a deformation microstructure with high recrystallization energy potential, thereafter subjecting the component to a heat treatment in the range of the eutectoid temperature (T) of the alloy, followed by cooling in air, to form a homogeneous, fine globular microstructure composed of phases GAMMA, BETA, ALPHAand having an ordered atomic structure at room temperature. This abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.

Method for producing a component and components of a titanium-aluminum base alloy

Growing community of inventors

Leoben, Austria

Helmut Clemens