Abstract: Embodiments of the invention relate to processes for the production of a creep-resistant material. One of the processes provides the following: provision of a metal powder; provision of metallic or ceramic nanoparticles; mixing of the metal powder with the nanoparticles, where during the mixing procedure the particles of the metal powder and the nanoparticles neither change their size nor change their shape; and consolidation of the mixture of metal powder and of nanoparticles to form a material with a polycrystalline metal structure, where the individual grains which have resulted from the consolidation and which are part of the polycrystalline metal structure have been produced from the particles of the metal powder and are separated from one another by grain boundaries, and where the arrangement has the nanoparticles at the grain boundaries.

Abstract: A method for manufacturing a part includes metal injection molding of metal powder mixed with a binder to produce individual components of the part as separately molded green compact sections which are then debindered to form brown compact sections. At least one of the brown compact sections is subjected to a pre-sintering process to undergo a first shrinkage. The pre-sintered brown compact section and a further brown compact section are joined together to form a multi-part brown compact which is subsequently subjected to a main sintering process, where the pre-sintered brown compact section undergoes less shrinkage than the further brown compact section to draw together and firmly connect the pre-sintered brown compact section and the further brown compact section.

Abstract: A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient ?1 of the first metallic material and of a linear expansion coefficient ?2 of the second metallic material is as: ? 2 ? ( T 2 ) ? 1 ? ( T 1 ) = x ? ? T 1 - T 0 ? ? T 2 - T 0 ? , where x=0.5 to 1; T1=mean operating temperature on a hot side; T0=reference temperature; T2=mean operating temperature on a cold side.

Abstract: A component, especially contrived and designed for being used in a turbomachine, includes a high-temperature coating being arranged above a base of the component. The base has at least one structural element for connecting it to the high-temperature coating, with the cross-section of the at least one structural element having at least three different widths, i.e. a base width at the lower end of the at least one structural element, a center width above it, and a tip width above that, where on average the center width is greater than or equal to the base width, but less than four times the base width, in particular less than or equal to three times the base width.

Abstract: A method for manufacturing thermally stressed engine components having a geometrically complex structure includes metal injection molding metal powder mixed with a binder to form green compacts of individual parts, which are debindered to form brown compact sections which are joined together to form a multi-part brown compact which are sintered in the assembled state. The brown compact sections have differing shrinkage properties in the sintering process, depending on the metal powder used, with a greater shrinking first brown compact section being automatically pressed against a second brown compact section during sintering. Connecting elements having positively engaging projections and recesses are provided at joining surfaces of the brown compact sections and have differing shrinkage such that during sintering of the assembled brown compact, the brown compact section with projections undergoes a greater shrinkage than the brown compact section with recesses.

Abstract: For near net shape manufacturing of a high-temperature resistant component of complex design a high melting-point part of an intermetallic phase provided as a metal powder is mixed with a binder, and from the feedstock such formed a green compact substantially matching the final contour is produced by metal injection moulding, into the pores of said compact that remain after removal of the binder the low melting-point part of the intermetallic phase is infiltrated. The brown compact thereby created is mechanically processed, if required, and subjected to a specific heat treatment depending on the metallic phases used in order to create the intermetallic phase. This permits engine components consisting of intermetallic phases and having a geometrically complex structure to be manufactured cost-efficiently.

Abstract: For near net shape manufacturing of high-temperature resistant engine components of geometrically complex design consisting of an intermetallic phase, a low melting-point metallic phase in the molten state or in a temperature range near the molten state is mixed with a high melting-point metallic phase provided as a metal powder, and the mixture is mechanically treated under the effect of kneading and shear forces, thereby heating it up and reducing its viscosity. In a subsequent injection moulding process the engine component substantially matching the final contour is formed and mechanically finish-machined, if required, and afterwards subjected to a heat treatment for creating an intermetallic phase.

Abstract: The present invention relates to a method for manufacturing thermally stressed engine components having a geometrically complex structure by metal injection moulding of metal powder mixed with a binder, by which method individual parts of the engine component are produced as separately moulded green compact sections and then as debindered brown compact sections which are joined together to form a two-part or multi-part brown compact and sintered in the assembled state, with the brown compact sections having differing shrinkage properties in the sintering process, depending on the type and size of the metal powder used, with at least one more heavily shrinking first brown compact section being automatically pressed against at least one second brown compact section during sintering of the assembled brown compact.

Abstract: A method for manufacturing a thermally deformable component for high thermal loads, includes: providing a first area of the component with a first metallic material by a generative laser process, or making the first area of the first metallic material; providing a second area of the component with a second metallic material by a generative laser process, or making the second area of the second metallic material; where at least one of the metallic materials is deposited by the generative laser process, and a ratio of a linear expansion coefficient ?1 of the first metallic material and of a linear expansion coefficient ?2 of the second metallic material is as: ? 2 ? ( T 2 ) ? 1 ? ( T 1 ) = x ? ? T 1 - T 0 ? ? T 2 - T 0 ? , where x=0.5 to 1; T1=mean operating temperature on a hot side; T0=reference temperature; T2=mean operating temperature on a cold side.

Abstract: A forging tool for precision forging of components of intermetallic or high-temperature stable phases with high yield stresses and shapeable at temperatures up to 1400° C. is made of graphite with a low-melting metal or a low-melting metal alloy infiltrated into its open-pored cavities, where metal carbides are created by heat treatment and form with the graphite a two-phase material hardened by subsequent quenching. The tool features high strength thanks to the yield stress increasing as the temperature increases at forging temperatures up to 1400° C., and is oxidation-resistant. It is electrically conductive, and has a low heat capacity, so that rapid inductive heating of the tool involving only low energy expenditure, short forging cycles and an inexpensive isothermic shaping process are possible. It has good lubrication properties, low wear and low manufacturing costs.

Abstract: A method provides fire protection for titanium components of an aircraft gas turbine. To enable the use of titanium components on aircraft gas turbines without the risk of titanium fire, a surface-near, nonflammable, intermetallic phase of titanium and at least one further metal, selected from the group of aluminum, nickel, vanadium and chromium, including combinations thereof, is produced in the surface of the component by a diffusion process.

Abstract: A method for the manufacture of highly loadable components by precision forging, e.g., of gas turbine compressor blades with different stress zones, initially provides for the production of a preform in a one-step forming operation, e.g., casting or sintering, with further deformable volume zones with a certain volume concentration in the highly loaded areas. The preform is subsequently finish-forged at a deformation rate which is limited by the respective volumes and is merely directed to the load and strength-specific recrystallization and structural requirements in the critical stress zones of the component.

Abstract: On an aircraft engine with a shroudless rotor wheel arranged in a flow duct, the flow duct includes a shroud segment (1) formed by a ceramic rubbing coating (3) which, while having good thermal conductivity, is highly-temperature resistant, attaches firmly to the metallic substrate (2) and is abradable by the tips of the rotor wheel to form a sealing gap as narrow as possible, this rubbing coating, owing to the lack of self-insulation, being coolable from a free side of the metallic substrate and, therefore, permitting for working gas temperatures occurring in high-pressure turbines and coating thicknesses sufficient for abrasion.

Abstract: For the production of an aluminum diffusion coating for oxidation protection of metallic components, components are masked in areas not to be coated, and unmasked areas are electrically-plated with aluminum in an aprotic solution at low temperature. Upon removal of the masking material, the components are heat-treated according to a certain high-temperature-time graph such that aluminum elements diffuse into the component alloy and alloy elements of the component diffuse into the aluminum coating. The method involves low manufacturing and material costs and guarantees a defined formation of the aluminum diffusion coating on the component portions to be protected.

Abstract: A method for the manufacture of highly loadable components by precision forging, e.g., of gas turbine compressor blades with different stress zones, initially provides for the production of a preform in a one-step forming operation, e.g., casting or sintering, with further deformable volume zones with a certain volume concentration in the highly loaded areas. The preform is subsequently finish-forged at a deformation rate which is limited by the respective volumes and is merely directed to the load and strength-specific recrystallization and structural requirements in the critical stress zones of the component.

Abstract: The invention relates to a method for producing components with a high load capacity from ?+? TiAl alloys, especially for producing components for aircraft engines or stationary gas turbines. According to this method, enclosed TiAl blanks of globular structure are preformed by isothermal primary forming in the ?+?? or ? phase area. The preforms are then shaped out into components with a predeterminable contour by means of at least one isothermal secondary forming process, with dynamic recrystallization in the ?+?? or ? phase area. The microstructure is adjusted by solution annealing the components in the ? phase area and then cooling them off rapidly.

Abstract: On an aircraft engine with a shroudless rotor wheel arranged in a flow duct, the flow duct comprises a shroud segment (1) formed by a ceramic rubbing coating (3) which, while having good thermal conductivity, is highly-temperature resistant, attaches firmly to the metallic substrate (2) and is abradable by the tips of the rotor wheel to form a sealing gap as narrow as possible, this rubbing coating, owing to the lack of self-insulation, being coolable from a free side of the metallic substrate and, therefore, permitting for working gas temperatures occurring in high-pressure turbines and coating thicknesses sufficient for abrasion.

Abstract: The invention relates to a method for producing components with a high load capacity from &agr;+&ggr; TiAl alloys, especially for producing components for aircraft engines or stationary gas turbines. According to this method, enclosed TiAl blanks of globular structure are preformed by isothermal primary forming in the &agr;+&ggr;− or &agr; phase area. The preforms are then shaped out into components with a predeterminable contour by means of at least one isothermal secondary forming process, with dynamic recrystallization in the &agr;+&ggr;− or &agr; phase area. The microstructure is adjusted by solution annealing the components in the &agr; phase area and then cooling them off rapidly.