Abstract: The present invention relates to a method for producing a component of a turbomachine from a metal alloy as well as a correspondingly produced component, wherein the method includes defining at least one first component region that will have a first property profile, and at least one second component region that will have a second property profile which is different from the first property profile; providing at least one powder of the metal alloy or several different powders of constituents of the metal alloy; additive manufacture of the component from the at least one powder, wherein the powder is melted for cohesive joining of the powder particles to each other and to a substrate or to an already produced part of the component.

Abstract: The present invention relates to a method for producing a component of a turbomachine from a metal alloy as well as a correspondingly produced component, wherein the method includes defining at least one first component region that will have a first property profile, and at least one second component region that will have a second property profile which is different from the first property profile; providing at least one powder of the metal alloy or several different powders of constituents of the metal alloy; additive manufacture of the component from the at least one powder, wherein the powder is melted for cohesive joining of the powder particles to each other and to a substrate or to an already produced part of the component.

Abstract: The invention relates to a blade for use in a turbine of an aircraft engine. The blade is made of (a) a Mo-based alloy strengthened by intermetallic silicides or (b) a Ni-based single crystal superalloy. An aircraft engine and in particular, a turbofan aircraft engine including a corresponding turbine blade is also disclosed.

Abstract: The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises providing powders of at least one member of the group which comprises pure chemical elements, alloys, chemical compounds and material composites, the powder corresponding overall to the chemical composition which the composite material to be produced is intended to have, each individual powder being different to the chemical composition of the composite material to be produced, compacting the powders, bonding the powders to one another to form a unit and thermoplastically shaping the unit.

Abstract: The invention relates to method of making a molybdenum alloy which has a high titanium content and further comprises silicon and/or boron. The method comprises subjecting to pressureless sintering or sintering under pressure in an inert gas atmosphere a mixture of one or more powders (i) of an alloy of Mo and Ti and, optionally, one or more additional metals X and/or (i?) powders of Mo and of TiN, and (ii) one or more powders comprising one or more powders of silicides of Mo and/or Ti and/or (iii) one or more powders of nitrides which comprise Si3N4 powder and/or BN powder.

Abstract: Disclosed is a method for improving the high-temperature stability of a component, in particular a blade of a turbomachine, formed at least partially from a molybdenum alloy that, besides molybdenum, silicon, boron and titanium, comprises iron and/or yttrium. The method comprises depositing a diffusion barrier layer formed from technically pure molybdenum or tungsten or being an alloy based on molybdenum and/or tungsten at least on an outer surface, which comprises the molybdenum alloy, of the component, and depositing silicon on the diffusion barrier layer to form molybdenum silicides and/or tungsten silicides.

Abstract: The invention relates to a blade for use in a turbine of an aircraft engine. The blade is made of (a) a Mo-based alloy strengthened by intermetallic silicides or (b) a Ni-based single crystal superalloy. An aircraft engine and in particular, a turbofan aircraft engine including a corresponding turbine blade is also disclosed.

Abstract: The present invention relates to a method for producing a component of a composite material comprising a metal matrix and incorporated intermetallic phases, which method comprises providing powders of at least one member of the group which comprises pure chemical elements, alloys, chemical compounds and material composites, the powder corresponding overall to the chemical composition which the composite material to be produced is intended to have, each individual powder being different to the chemical composition of the composite material to be produced, compacting the powders, bonding the powders to one another to form a unit and thermoplastically shaping the unit.

Abstract: The present invention relates to a blade for a turbomachine, in particular for an aircraft engine, which comprises a blade root (2) for arranging the blade (1) in the turbomachine and a main blade part (3) for interaction with a fluid flowing through the turbomachine, the blade root and the main blade part being formed from different materials and the main blade part being formed from a metal-intermetallic composite material. The metal matrix, in which intermetallic phases are incorporated for forming the metal-intermetallic composite material, is formed by a molybdenum alloy. The invention also relates to a corresponding method for producing such a blade.

Abstract: The present invention relates to a quaternary or multinary molybdenum alloy for the production of structural components, in particular of vanes of a turbomachine having the main constituents molybdenum, silicon, boron and titanium, which, as minor alloying elements, additionally comprises at least one of iron and yttrium.