Abstract: A rotor (10) for a turbomachine, comprising at least one first, preferably disk-like rotor section (12), which is exposed to high operating temperatures and consists of a particularly creep-resistant material, in particular a nickel-based alloy, and at least one second, preferably disk-like rotor section (11), which is exposed to lower operating temperatures and consists of a less creep-resistant material, in particular steel, the first and second rotor sections (11, 12) being joined to one another by welding. In a rotor of this type, a crack-free welded joint is achieved by the fact that, to join the two rotor sections (11, 12), a transition region (13) is arranged between the two rotor sections (11, 12), which transition region is produced by powder metallurgy, is welded to one of the two rotor sections (11, 12) at least on one side, and on this side has the same composition as the rotor section to which it is welded.

Abstract: In a method for welding together two parts (12, 13), especially of a turbomachine, which are exposed to different temperatures, of which the first part (12) consists of a steel and the second part (13) consists of a nickel-base alloy which contains elements which are unfavorable for welding to steel, such as for example Nb, a crack-free welded joint is achieved by the fact that first of all an intermediate layer (18), in which the amount of unfavorable elements is progressively reduced from the inside outward, is applied to the joining surface (17) which is provided for the welding, and that then the second part (13), which has been provided with the intermediate layer (18), is welded to the first part (12).

Abstract: The invention relates to a high-temperature alloy for a mechanically highly stressed component of a thermal machine based on doped TiAl and a method to improve a mechanical property of the alloy. The alloy has the following composition (in atomic %): 44.5 to <46 Al, 1-4 W, 0.1-1.5 Si, 0.0001-4 B, and the rest Ti and contaminations due to the manufacturing process. The alloy is characterized by improved heat resistance and ductility at high temperatures, and at the same time good oxidation and corrosion resistance.

Abstract: The invention relates to a high-temperature alloy for a mechanically highly stressed component of a thermal machine based on doped TiAl and a method to improve a mechanical property of the alloy. The alloy has the following composition (in atomic %): 44.5 to <46 Al, 1-4 W, 0.1-1.5 Si, 0.0001-4 B, and the rest Ti and contaminations due to the manufacturing process. The alloy is characterized by improved heat resistance and ductility at high temperatures, and at the same time good oxidation and corrosion resistance.

Abstract: In a blade possessing a blade body and a blade foot consisting of an alloy based on a doped gamma-titanium aluminide, at least part of the surface layer of the blade has a finely-grained structure, and the core has a coarsely-grained structure. The ductility of the finely-grained surface layer is higher than that of the coarsely-grained core. In a method for producing the blade, the surface is deformed after casting and hot-isostatic pressing of the blade. The deformed surface layer undergoes recrystallization annealing.

Abstract: In a heat shield (1), in particular for combustion chambers and for thermal fluid flow machines, the heat shield consists of a feltlike material (3) composed of compressed and sintered intermetallic fibers. Advantageously, the intermetallic fibers consist of an iron based or nickel based intermetallic phase.

Abstract: In a method for welding together two parts (12, 13), especially of a turbomachine, which are exposed to different temperatures, of which the first part (12) consists of a steel and the second part (13) consists of a nickel-base alloy which contains elements which are unfavorable for welding to steel, such as for example Nb, a crack-free welded joint is achieved by the fact that first of all an intermediate layer (18), in which the amount of unfavorable elements is progressively reduced from the inside outward, is applied to the joining surface (17) which is provided for the welding, and that then the second part (13), which has been provided with the intermediate layer (18), is welded to the first part (12).

Abstract: A rotor (10) for a turbomachine, comprising at least one first, preferably disk-like rotor section (12), which is exposed to high operating temperatures and consists of a particularly creep-resistant material, in particular a nickel-based alloy, and at least one second, preferably disk-like rotor section (11), which is exposed to lower operating temperatures and consists of a less creep-resistant material, in particular steel, the first and second rotor sections (11, 12) being joined to one another by welding.

Abstract: An iron aluminide coating consists essentially of: 5-35% by weight aluminum 15-25% by weight chromium 0.5-10% by weight molybdenum, tungsten, tantalum and niobium 0-0.3% by weight zirconium 0-1% by weight boron 0-1% by weight yttrium the remainder being iron and also impurities and additaments arising from its production.

Abstract: An iron aluminide coating as a bonding layer between a thermally stressed element of a thermal turbomachine and a heat insulation coat consists essentially of:  5-35 % by weight aluminum 15-25 % by weight chromium 0.5-10  % by weight molybdenum, tungsten, tantalum and/or niobium   0-0.3 % by weight zirconium 0-1 % by weight boron 0-1 % by weight yttrium the remainder being iron and incidental impurities arising from production thereof.

Abstract: An iron aluminide coating consists essentially of: 1 5-35% by weight aluminum 15-25% by weight chromium 0.5-10% by weight molybdenum, tungsten, tantalum and niobium 0-0.

Abstract: An iron-nickel superalloy of the type IN 706 has an addition of 0.02 to 0.3 percent by weight of boron and/or 0.05 to 1.5 percent by weight of hafnium. By means of this addition, a virtual doubling of the ductility is achieved as compared with an addition-free iron-nickel superalloy of the type IN 706, while the hot strength is reduced only slightly. The alloy is particularly suitable as a material for rotors of large gas turbines. It has a sufficiently high hot strength. When locally acting temperature gradients arise unwanted stresses can occur to only a slight extent because of the high ductility of the alloy.

Abstract: A process for the production of a body of material stable at high temperatures. In this process, the body of material is formed by solution annealing and subsequent precipitation hardening of a hot work-hardened starting body composed of an iron-nickel superalloy of the type IN 706 provided in a furnace. The body of material is distinguished by a particularly high ductility in combination with high hot strength if the solution-annealed starting body is cooled from the annealing temperature envisaged for the solution annealing to the temperature envisaged for the precipitation hardening at a cooling rate of between 0.5.degree. and 20.degree. C./min.

Abstract: An alloy based on a silicide containing at least chromium and molybdenum contains the following constituents in atomic percent: chromium 41-55, molybdenum 13-35 and silicon 25-35, or chromium 35-55, molybdenum 13-35, silicon 13-35, yttrium 0.001-0.3, and/or tungsten 0.001-10. This alloy is distinguished by a high oxidation resistance and still has a mechanical strength at temperatures of over 1000.degree. C. which favors its use as structural material in gas turbines.

Abstract: The component comprises a body (5) composed of an alloy based on a .gamma.-titanium aluminide, a steel body (2) and a connecting piece (4) composed of a nickel-base alloy. The .gamma.-titanium aluminide body (5) and the steel body (2) are rigidly joined together by means of the connecting piece (4). The joint between the .gamma.-titanium aluminide body (5) and the connecting piece (4) is produced by friction welding. The nickel-base alloy has a nickel content of less than 65 percent by weight. This achieves the result that the friction-welding joint of the .gamma.-titanium aluminide body (5) to the connecting piece (4) can be produced at comparatively low temperatures. During the friction welding, the risk of crack formations in the embrittlement-prone .gamma.-titanium aluminide body (5) is therefore appreciably reduced.

Abstract: The alloy is based on doped iron aluminide Fe.sub.3 Al. It contains the following alloying constituents in atomic percent:______________________________________ 24 28 aluminum, 0.1 2 niobium, tantalum and/or tungsten, 0.1 10 chromium, 0.1 2 silicon, 0.1 5 boron, 0.01 2 titanium, ______________________________________the remainder being iron. The alloy is notable for a high oxidation resistance and corrosion resistance even at temperatures above 700.degree. C. and is preferably used in components which are exposed to oxidizing and corrosive actions at high temperatures and low mechanical stress.

Abstract: The iron-aluminum alloy comprises the following constituents in atom percent:______________________________________ 12-18 aluminum 0.1-10 chromium 0.1-2 niobium 0.1-2 silicon 0.1-5 boron 0.01-2 titanium 100-500 ppm carbon 50-200 ppm zirconium remainder iron. ______________________________________This alloy is distinguished by high thermal-shock resistance and, at temperatures of 800.degree. C., still has comparatively good mechanical properties. The alloy can be used advantageously in components such as, for example, casings of gas turbines, which, with comparatively low mechanical loading, are subject to frequent thermal cycling.

Abstract: The high temperature alloy is intended for machine components subjected to high mechanical and thermal stress. It is essentially based on doped TiAl and has the following composition:______________________________________ Ti.sub.x El.sub.y Me.sub.z Al.sub.1 -(x + y + z), in which El = B, Ge or Si and Me = Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Ta, V, W, Y, and/or Zr and: 0.46 .ltoreq.x .ltoreq.0.54, 0.001 .ltoreq.y .ltoreq.0.015 for El = Ge and Me = Cr, Hf, Mn, Mo, Nb, Ta, V and/or W, 0.001 .ltoreq.y .ltoreq.0.015 for El = Si and Me = Hf, Mn, Mo, Ta, V and/or W, 0 .ltoreq.y .ltoreq.0.01 for El = B and Me = Co, Ge, Pd, Y and/or Zr, 0 .ltoreq.y .ltoreq.0.02 for El = Ge and Me = Co, Ge, Pd, Y and/or Zr, 0.0001 .ltoreq.y .ltoreq.0.01 for El = B and Me = Cr, Mn, Nb and/or W, 0.01 .ltoreq.z .ltoreq.0.04 if Me = an individual element, 0.01 .ltoreq.z .ltoreq.0.08 if Me = two or more individual elements and 0.46 .ltoreq.(x + y +z) .ltoreq.0.54.

Abstract: The turbine blade contains a casting having a blade leaf (1), blade foot (2) and, if appropriate, blade cover strip (3) and composed of an alloy based on a dopant-containing gamma-titanium aluminide.This turbine blade is to be distinguished by a long lifetime, when used in a turbine operated at medium and high temperatures, and, at the same time, be capable of being produced in a simple way suitable for mass production. This is achieved in that, at least in parts of the blade leaf (1), the alloy is in the form of a material of coarse-grained structure and with a texture resulting in high tensile and creep strength and, at least in parts of the blade foot (2) and/or of the blade cover strip (3), provided if appropriate, is in the form of a material of fine-grained structure and with a ductility increased in relation to the material contained in the blade leaf (1).

Abstract: The high temperature alloy is intended for machine components subjected to high mechanical and thermal stress. It is essentially based on doped TiAl and has the following composition:Ti.sub.x El.sub.y Me.sub.z Al.sub.1-(x+y+z),in which El=B, Ge or Si and Me=Co, Cr, Ge, Hf, Mn, Mo, Nb, Pd, Ta, V, W, Y, and/or Zr and:______________________________________ 0.46 .ltoreq.x .ltoreq.0.54, 0.001 .ltoreq.y .ltoreq.0.015 for El = Ge and Me = Cr, Hf, Mn, Mo, Nb, Ta, V and/or W, 0.001 .ltoreq.y .ltoreq.0.015 for El = Si and Me = Hf, Mn, Mo, Ta, V and/or W, 0 .ltoreq.y .ltoreq.0.01 for El = B and Me = Co, Ge, Pd, Y and/or Zr, 0 .ltoreq.y .ltoreq.0.02 for El = Ge and Me = Co, Ge, Pd, Y and/or Zr, 0.0001 .ltoreq.y .ltoreq.0.01 for El = B and Me = Cr, Mn, Nb and/or W, 0.01 .ltoreq.z .ltoreq.0.04 if Me = an individual element, 0.01 .ltoreq.z .ltoreq.0.08 if Me = two or more individual elements and 0.46 .ltoreq.(x + y + z) .ltoreq.0.54.