Asea Brown Boveri Inc.

Abb Research Ltd.

Alstom

Christoph Tonnes

Maxim Konter

Joachim Rosler

Manfred Thumann

Michael Newnham

Hans-Peter Bossmann

Gundolf Meyer

Robert Baumann

Clemens Verpoort

Christoph Sommer

Peter Ernst

Peter David Holmes

Peter Jongenburger

A nickel base alloy comprising: (measured in % by weight): 11-16% Co; 12.2-15.5% Cr; 6.5-7.2% Al; 3.2-5.0% Re; 1.0-2.5% Si; 1.5-4.5% Ta; 0.2-2.0% Nb; 0.2-1.2% Hf; 0.2-1.2% Y; 0-1.5% Mg; 0-1.5% Zr; 0-0.5% La and La series elements; 0-0.15% C; 0-0.1% B; and a remainder including Ni and impurities. The alloy is particularly suited for coatings for gas turbine components such as gas turbine blades and vanes.

Nickel base alloy

A nickel-base superalloy, in particular for the fabrication of monocrystalline components, consisting essentially of (measured in wt %) 6.0-6.8% of Cr, 8.0-10.0% of Co, 0.5-0.7% of Mo, 6.2-6.6% of W, 2.7-3.2% of Re, 5.4-5.8% of Al, 0.5-0.9% of Ti, 7.2-7.8% of Ta, 0.15-0.3% of Hf. 0.02-0.04% of C, 40-100 ppM of B, the remainder being nickel with impurities. The ratio (Ta+1.5 Hf+0.5 Mo-0.5 Ti)/(W+1.2 Re) is greater than or equal to 0.7.

Nickel-base superalloy

A nickel-base superalloy, in particular for the fabrication of large monocrystalline components, essentially comprises (measured in wt %): 6.0-6.8% of Cr, 8.0-10.0% of Co, 0.5-0.7% of Mo, 6.2-6.6% of W, 2.7-3.2% of Re, 5.4-5.8% of Al, 0.6-1.2% of Ti, 6.3-7.0% of Ta, 0.15-0.3% of Hf, 0.02-0.04% of C, 40-100 ppm of B. 15-50 ppm of Mg, the remainder being nickel with impurities. Carbides of Ta, Ti, and Hf, and Mg, and/or Mg--O--S compounds are concentrated along small angle grain boundaries of the superalloy.

Monocrystalline nickel-base superalloy with Ti, Ta, and Hf carbides

The method serves to produce a material based on a doped intermetallic compound. In carrying out the method, at least two differently doped powders each based on the intermetallic compound are selected. One of the two powders predominantly has coarse-grained particles. On the other hand, another powder is formed from comparatively fine-grained particles composed of a material having a lower creep strength but a higher ductility than the material of the coarse-grained powder. The at least two powders are mixed with one another in a ratio serving to establish a desired mixed microstructure and then hot-compacted and heat-treated to form the material. Material produced by this method is suitable for components which are exposed to high mechanical loads at high temperatures, such as, in particular, gas-turbine blades or turbine wheels of turbo chargers.

Method of producing a material based on a doped intermetallic compound

A turbine blade including a blade and blade foot. The blade foot is formed by a ductile material and the blade comprises a material which is brittle compared to the ductile material but resistant to high temperature. The two materials are alloys of the same base compositions but differ as to presence and/or quantity of at least one doping element. The alloys can be hot-compacted with the formation of a transition zone joining the blade and blade root wherein fine crystallites of the blade root interpenetrate coarse crystallites of the blade. The two materials can comprise a gamma-titanium aluminide containing 0.5 to 8 atomic percent of a dopant. The turbine blade exhibits outstanding mechanical properties at high temperatures, good ductility at room temperature and a long service life.

High-temperature component, especially a turbine blade, and process for

A turbine blade including a blade foot and a blade. The blade foot is formed by a ductile material and the blade comprises a material which is brittle compared to the ductile material but resistant to high temperature. The two materials are alloys of different chemical compositions and are hot-compacted with the formation of a boundary layer joining the blade foot and blade to produce a bimetallic composite material. The blade foot predominantly comprises a titanium-base alloy and the blade comprises a gamma-titanium aluminide containing 0.5 to 8 atomic percent of a dopant. The turbine blade exhibits outstanding mechanical properties at high temperatures, good ductility at room temperature and a long service life.

Component, in particular turbine blade which can be exposed to high

A process for the powder-metallurgical production of a workpiece by filling a binder-free and solvent-free, dry metal powder or ceramic powder into a mold, precompacting the powder by tapping and presintering it for 1/2 hour to 1 hour at 0.65 to 0.85 times the absolute melting temperature without significant shrinkage, adjacent powder particles being joined merely at their contact points by necking to give a skeletal formed body. The formed body is taken out of the mold and finish-sintered at at least 0.9 times the absolute melting temperature for at least 1 hour without additional support by a mold. Advantageously, the sintered body is additionally hot-isostatically pressed containerless in order to reach at least 98% of the theoretical density.

Process for the powder-metallurgical production of a workpiece

The process serves for producing a carbon-containing sintered compact from steel powder. In this process, the steel powder is heated to sintering temperature in an atmosphere containing, at least for a time, carbon monoxide, is kept at sintering temperature over a predetermined period of time and the sintered compact formed thereby is subsequently cooled. In this process, the carbon content of the sintered compact to be produced is to be set to a predetermined value in a way which is simple and suitable for mass production. This is achieved by the partial pressure of the carbon monoxide in the atmosphere being changed selectively during the execution of the production process, and by this change being controlled in such a way that the carbon content of the sintered compact is set to the predetermined value after execution of the production process.

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Birmenstorf, Switzerland

Christoph Tonnes