Abstract: Nickel based super alloy, which includes at least, (in wt %): Iron (Fe) 1.5%-6.5% especially 3.5%-5.5%; Chrome (Cr) 12.0%-14.0%; Molybdenum (Mo) 1.0%-2.0%; Wolfram (W) 2.0%-5.0%; Aluminum (Al) 5.2%-5.8%; Tantalum (Ta) 5.0%-7.0%; Hafnium (Hf) 1.2%-1.8%; Silicon (Si) 0.005%-0.4%; Carbon (C) 0.005%-0.1%; Nickel (Ni), optionally Cobalt (Co) 0.0%-5.0%; especially at least 1.0 wt % Cobalt (CO); Boron (B) >0.0%-0.02%; especially maximum 0.005%; Zirconium (Zr) >0.0%-0.05%; especially maximum 0.01% 0-0.05%; reactive element(s), especially Yttrium (Y), Cerium (Ce), Dysprosium (Dy), and/or Lanthanum (La).

Abstract: A nickel-based alloy for additive manufacturing, method and product wherein due to a specific selection of elements and adaptations, an improved alloy for casting and for additive manufacturing is provided.

Abstract: A nickel based superalloy, including: Chromium (Cr) 12.0%-14.0%, Molybdenum (Mo) 1.5%-3.0%, Tungsten (W) 2.5%-4.5%, Aluminum (Al) 4.0%-5.0%, Titanium (Ti) 1.8%-2.8%, Niobium (Nb) 1.5%-3.5%, Hafnium (Hf) 0.8%-1.8%, Carbon (C) 0.03%-0.13%, Boron (B) 0.005%-0.025%, Silicon (Si) 0.005%-0.05%, and optionally: Cobalt (Co) 0.0%-10.0%, Tantalum (Ta) 0.0%-3.0%, Zirconium (Zr) 0.0%-0.03%, especially remainder Nickel.

Abstract: A nickel base super alloy or blade alloy having Ni as a main constituent and the following elements or portions in wt %: Fe: 2 to 8, Al: 6.1 to 6.8, Cr: 12.5 to 15, W: 1.5 to 4.5, Ta: 2.5 to 5.5, Hf: 1.2 to 2, C: 0.03 to 0.13, B: 0.005 to 0.02, Zr: 0.005 to 0.02, and Si: 0.005 to 0.02.

Abstract: A nickel-based superalloy without titanium and a corresponding powder. A process for producing a component, wherein the alloy or the powder is used, in particular for a process for additive manufacture, especially selective laser sintering or selective laser melting. A component having an alloy or produced from the powder or produced by the process.

Abstract: A nickel-base alloy for high-temperature applications, preferably for gas turbines, and a process. A selective choice of alloy elements permits the provision of an alloy which can be used to produce components devoid of cracking.

Abstract: A nickel based superalloy, including: Chromium (Cr) 12.0%-14.0%, Molybdenum (Mo) 1.5%-3.0%, Tungsten (W) 2.5%-4.5%, Aluminum (Al) 4.0%-5.0%, Titanium (Ti) 1.8%-2.8%, Niobium (Nb) 1.5%-3.5%, Hafnium (Hf) 0.8%-1.8%, Carbon (C) 0.03%-0.13%, Boron (B) 0.005%-0.025%, Silicon (Si) 0.005%-0.05%, and optionally: Cobalt (Co) 0.0%-10.0%, Tantalum (Ta) 0.0%-3.0%, Zirconium (Zr) 0.0%-0.03%, especially remainder Nickel.

Abstract: A nickel base super alloy or blade alloy having Ni as a main constituent and the following elements or portions in wt %: Fe: 2 to 8, Al: 6.1 to 6.8, Cr: 12.5 to 15, W: 1.5 to 4.5, Ta: 2.5 to 5.5, Hf: 1.2 to 2, C: 0.03 to 0.13, B: 0.005 to 0.02, Zr: 0.005 to 0.02, and Si: 0.005 to 0.02.

Abstract: A nickel-based superalloy without titanium and a corresponding powder. A process for producing a component, wherein the alloy or the powder is used, in particular for a process for additive manufacture, especially selective laser sintering or selective laser melting. A component having an alloy or produced from the powder or produced by the process.

Abstract: A combustion chamber of a combustor for a gas turbine is provided. A combustion chamber includes a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising a radial inner wall portion and a radial outer wall portion, a first section comprising an opening for the installation of a burner, and a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment.

Abstract: A nickel alloy includes a proportion by weight of Cr of 12.3% to 13.7%, a proportion by weight of Al of 4.3% to 4.7% and a proportion by weight of Co of 4% to 6%. The components are preferably Cr, Mo, Re and/or W, Al, Ti, Ta, Hf, Si, reactive elements including actinides and lanthanides, C, optionally the components Zr and/or B. The proportions by weight are selected such that both a desired high creep resistance and also a desired high hot corrosion resistance are achieved. A turbine blade is made of the nickel alloy.

Abstract: A combustion chamber of a combustor for a gas turbine is provided. A combustion chamber includes a plurality of segments arranged annularly about an axis of the combustion chamber, each segment comprising a radial inner wall portion and a radial outer wall portion, a first section comprising an opening for the installation of a burner, and a second section at which at least one airfoil extends between the radial inner wall portion and radial outer wall portion of the segment.

Abstract: A nickel base gamma prime strengthened superalloy with a unique blend of adequate hot corrosion resistance, high oxidation resistance, high coating compatibility, adequate phase stability, adequate creep resistance and low density is disclosed. The composition includes: Up to 20 wt % Co, between 12 and 14 wt % Cr, between 1 and 2 wt % Mo, between 1.4 and 2.8 wt % W, between 5.1 and 5.9 wt % Al, between 1.1 and 1.6 wt % Ti, between 3 and 7 wt % Ta, between 0.01 and 0.3 wt % of C+Zr+B, between 0.05 and 1 wt % Hf, between 0.05 and 1 wt % Si, and between 0.01 and 0.2 wt % of the sum of rare earths such as Sc, Y, the actinides and the lanthanides. The composition is intended for use in hot components such as gas turbine blades, and the hot components are preferably produced by clean casting.

Abstract: An inlet guide vane arrangement for a gas turbine is provided. The arrangement includes a plurality of guide vane duct elements, the guide vane duct elements include a suction side wall and a pressure side wall, both walls facing each other, and are designed to be adjoinable to another of the guide vane duct elements, such that the pressure side wall of one guide vane duct element cooperates with the suction side wall of the adjacent guide vane duct element thereby forming a guide vane. The guide vane duct element includes features to accept a key element adapted to be arranged between the pressure side wall and the adjacent suction side wall, when two guide vane duct elements are adjoining to one another, and to attach together both adjoining guide vane duct elements.

Abstract: A nickel-base y/y? superalloy with a blend of at most moderate cost, high oxidation resistance, high hot corrosion resistance, moderate strengthening, adequate allow stability and comparatively good weldability is provided. The alloy includes up to 20 wt % of the sum of Co and Fe, between 17 and 21 wt % Cr, between 0.5 and 3 wt % of the sum of Mo and W, at most 2 wt % Mo, between 4.8 and 6 wt % Al, between 1.5 and 5 wt % Ta, between 0.01 and 0.2 wt % of the sum of C and B, between 0.01 and 0.2 wt % Zr between 0.05 and 1.5 wt % Hf, between 0.05 and 1.0 wtz % Si, and between 0.01 and 0.5 wt % of the sum of rare earths such as Sc, Y, the actinides and the lanthanides, such that at least two of these rare earths are present in the alloy, and no more than 0.3 wt % of any of these rare earths.

Abstract: A nickel base gamma prime strengthened superalloy with a unique blend of adequate hot corrosion resistance, high oxidation resistance, high coating compatibility, adequate phase stability, adequate creep resistance and low density is disclosed. The composition comprises: Up to 20 wt % Co, between 12 and 14 wt % Cr, between 1 and 2 wt % Mo, between 1.4 and 2.8 wt % W, between 5.1 and 5.9 wt % Al, between 1.1 and 1.6 wt % Ti, between 3 and 7 wt % Ta, between 0.01 and 0.3 wt % of C+Zr+B, between 0.05 and 1 wt % Hf, between 0.05 and 1 wt % Si, and between 0.01 and 0.2 wt % of the sum of rare earths such as Sc, Y, the actinides and the lanthanides. The composition is intended for use in hot components such as gas turbine blades, and said components are preferably produced by clean casting.

Abstract: A nickel base alloy is provided which includes the following components by weight: Co: 2.75 to 3.25% Cr: 11.5 to 12.5% Mo: 2.75 to 3.25% Al: 3.75 to 4.25% Ti: 4.1 to 4.9% Ta: 1.75 to 2.25% C: 0.006 to 0.04% B: ?0.01% Zr: ?0.01% Hf: ?1.25% Nb: ?1.25% balance Ni.

Abstract: A nickel base gamma prime strengthened superalloy with a unique blend of high hot corrosion resistance, high oxidation resistance, high coating compatibility, good weldability, high phase stability and at least moderate creep resistance is disclosed. The composite includes: Up to 20 wt % Co, between 17 and 21 wt % Cr, between 2 and 5 wt % of Mo+W+Re, at most 2 wt % Mo, between 4 and 4.7 wt % AL, between 3 and 7 wt % Ta, 0.01 and 0.2 wt % Ta, between 0.01 and 0.3 wt % of C+Zr+B between 0.05 and 1 wt % Hf, between 0.05 and 1 wt % Si, and between 0.01 and 0.2 wt % of the sum of rare earths such as SC, Y, the actinides and the lanthanides. The composition is intended for use as base alloy for moderately stressed hot components and as filler alloy for cladding and weld repair in moderately stressed parts of hot components.

Abstract: A nickel base alloy is provided which includes the following components by weight: Co: 2.75 to 3.25% Cr: 11.5 to 12.5% Mo: 2.75 to 3.25% Al: 3.75 to 4.25% Ti: 4.1 to 4.9% Ta: 1.75 to 2.25% C: 0.006 to 0.04% B: ?0.01% Zr: ?0.01% Hf: ?1.25% Nb: ?1.25% balance Ni.

Abstract: A nickel-base superalloy is provided which includes in a weight percentage:: Co+Fe+Mn 0-20, Al 4-6, Cr >12-20, Ta >7.5-15, Ti 0-<0.45, V 0-1, Nb 0-<0.28, Mo 0-2.5, Mo+W+Re+Rh 2-8, Ru+Os+Ir+Pt+Pd 0-4, Hf 0-1.5, C+B+Zr 0-0.5, Ca+Mg+Cu 0-0.5, Y+La+Sc+Ce+Actinides+Lanthanides 0-0.5 Si 0-0.5 Ni balance and unavoidable impurities. Also provided are a conventional cast component, a directionally solidified component and a single crystal component which include the superalloy.