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: 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.

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 whichEl=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: A process for producing a workpiece from an alloy containing dopant and based on titanium aluminide. The process is intended to produce a workpiece of high oxidation and corrosion resistance, good high-temperature strength and adequate ductility. The process steps include melting the alloy, casting the melt to produce a cast body, cooling the cast body to room temperature and removing its casting skin and its scale layer. The descaled cast body is subjected to high-temperature isostatic pressing at a temperature between 1200.degree. and 1300.degree. C. and a pressure between 100 and 150 MPa, and cooling the isostatically pressed cast body. The cooled cast body is heated to temperatures of 1050.degree. to 1200.degree. C., deformed isothermally one or more times at this temperature for the purpose of molding and structure improvement, and cooled to room temperature. The deformed cast body is machined to produce a workpiece by material removal.

Abstract: Oxidation- and corrosion-resistant alloy for components for a medium temperature range based on doped iron aluminide Fe.sub.3 Al having the following composition:Al=24-28 at.-%Nb=0.1-2 at.-%Cr=0.1-10 at.-%B=0.1-1 at.-%Si=0.1-2 at.-%Fe=remainder.At 550.degree. C. high temperature yield points of 500 to more than 650 MPa are obtained.

Abstract: Current-transmitting components for conducting current between adjacent, planar, stacked high-temperature fuel cells containing solid electrolyte (1) comprising a carrier (7; 10) which determines the geometrical shape and is composed of an oxide-dispersion-hardened nickel or nickel/chromium alloy containing up to 2% by weight of ThO.sub.2 as dispersoid, an electrically conductive Cr.sub.2 O.sub.3 layer (8) and a noble-metal surface layer (9; 12) supported on the latter at the contact/touching faces. Variants having continuous (13; 14) or porous (9; 12) noble-metal surface layer composed of Au, a Pt metal or alloys. Separating plate (4) composed of an oxide-dispersion-hardened nickel/chromium alloy with nickel plating (5) on the fuel side and noble-metal plating (6) on the oxygen side.

Abstract: An oxidation- and corrosion-resistant high-temperature alloy of high toughness at room temperature for directional solidification, based on an intermetallic compound of the nickel aluminide type and having the following composition:Al=10-20 atom %Si=0.5-8 atom %Nb=2-10 atom %B=0.1-2 atom %Ni=remainder,the total of Al, Si, Nb and B amounting at most to a value of 25 atom %. The alloy contains at least 90% by volume of the intermetallic phases Ni.sub.3 Al, Ni.sub.3 Si and Ni.sub.3 Nb.

Abstract: A precipitation-hardenable nickel-base superalloy with improved mechanical properties in the temperature range from 600.degree. to 750.degree. C. which has the following composition:Cr=12-15 percent by weightCo=3-4.5 percent by weightW=1-3.5 percent by weightTa=4-5.5 percent by weightAl=3-4.3 percent by weightTi=4-5 percent by weightHf=0-2.5 percent by weightB=0-0.02 percent by weightZr=0.01-0.06 percent by weightC=0.05-0.

Abstract: A process for increasing the oxidation resistance and corrosion resistance of a component made of a dispersion strengthened superalloy by means of a surface treatment, the object of which in every case is to produce or retain a fine-grained surface zone (5) while the core zone (4) of the component in all circumstances is forced to form coarse grains during the final recrystallization annealing in the temperature range between the recrystallization temperature and the solidus temperature. A fine-grained surface zone (5) is produced by cold-working the surface zone (3, 5) by shot-peening, surface milling or pressing or by heating the surface zone (7) to a temperature about 100.degree. to 140.degree. C. below the recrystallization temperature by means of a laser (9) or an arc (10) while the core zone is kept at less than 900.degree. C., or by application of a 10 to 50 .mu.

Abstract: A workpiece produced from a corrosion- and oxidation-resistant Ni/Al/Si/B alloy, which possesses simultaneously good high-temperature strength and high ductility, is produced by casting an alloy containingAl=12 to 23 atom-%,Si=1 to 12 atom-%,B=0.1 to 2 atom-%, withAl+Si+B being=24 atom-%, andNi=remainderinto a cast ingot, heat treating at 1,100.degree. C./60 h in argon and subsequent isothermal forging between 1,050.degree. and 1,150.degree. C. until a deformation of .epsilon.=1.6 is reached at a deformation rate of .epsilon.=6.times.10.sup.-5 s.sup.-1, where ##EQU1## with h.sub.o =original height of the workpiece,h.sub.f =height of the workpiece after deformation.

Abstract: Method for applying a corrosion-protection layer to the base body (1) of a gas turbine blade by embedding particles (3) of SiC in a metallic matrix by means of powder, paste or electrolytic/electrophoretic methods and compacting, welding or fusing and bonding the matrix-forming material to the base body (1) by means of hot-pressing, hot isostatic pressing or laser beam, electron beam or electric arc. Protective layers are formed which do not flake off and with high silicon content which is at least partially contained in the embedded, partly modified SiC particles (6) as a reservoir for the operation.