Mtu Aero Engines Ag

Thomas Goehler

Robert Singer

Ralf Rettig

Ernst Affeldt

Thomas Hess

Wilfried Smarsly

Markus Fried

Steffen Neumeier

Mathias Goeken

Ernst Fleischmann

Uwe Glatzel

Rainer Voelkl

Michael Weiss

Tobias Maiwald-Immer

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

The invention relates to a nickel-based alloy having a microstructure with a matrix of &#x3b3;-phase and precipitates of &#x3b3;'-phase. The &#x3b3;&#x2032;-phase comprises a percentage by volume of from 50 vol % to 80 vol % in the temperature range of from 1000&#xb0; C. to 1100&#xb0; C. The nickel-based alloy comprises 8 to 13 at % aluminum, 3 to 14 at % cobalt, 4 to 12 at % chromium, 0.6 to 8 at % molybdenum, 0 to 6 at % rhenium, 0.5 to 4 at % tantalum, 0.5 to 4 at % titanium, 0.3 to 3.5 at % tungsten, 0 to 4 at % germanium, 0 to 0.6 at % hafnium, 0 to 4 at % ruthenium, balance nickel and unavoidable impurities. The concentrations of molybdenum and tungsten are selected such that the percentage X of molybdenum and tungsten in the &#x3b3;-phase, X=0.84 C+C, is greater than 5.5 at % at a temperature of from 1000&#xb0; C. to 1100&#xb0; C., Cand Cbeing the concentrations of molybdenum and tungsten in at %.

Nickel-based alloy with optimized matrix properties

A nickel-base superalloy is disclosed. The superally includes aluminum, cobalt, chromium, molybdenum, tantalum, titanium and tungsten, in addition to nickel, as alloy constituents, wherein rhenium can additionally be contained and the rhenium content is less than or equal to 2 wt. % and wherein the titanium content is greater than or equal to 1.5 wt. %. Further disclosed is a component made of the nickel-base superalloy.

Rhenium-free or rhenium-reduced nickel-base superalloy

The present invention relates to a method for the generative production of components, particularly of single-crystalline or directionally-solidified components, particularly for the production of components for turbomachines, in which the component is constructed in layers on a substrate or a previously produced part of the component (), wherein a construction in layers takes place by melting of powder material in layers with a high-energy beam () and solidification of the powder melt () takes place, wherein the high-energy beam has a beam cross section () in the area of its impingement on the powder material that is altered in comparison to a circular or other symmetrical cross section and/or the beam energy is distributed non-uniformly, in particular asymmetrically or eccentrically, over the beam section.

Irradiation in generative fabrication

Growing community of inventors

Dachau, Germany

Thomas Goehler