Method for producing gas turbine components
A method for producing gas turbine components, in particular blades, blade sections or rotors with integral blades for a jet engine is provided. The method comprises at least the following steps: preparation of at least one metallic powder and at least one expanding agent; mixing of the metallic powder or each metallic powder with the expanding agent or each expanding agent; compression of the resultant mixture to form at least one semi-finished product; expansion of the semi-finished product or each semi-finished product by heating to achieve a defined degree of expansion; termination of the expansion process by cooling, once the defined degree of expansion has been reached.
1. A method for manufacturing gas turbine components, comprising:
providing at least one metal powder and at least one foaming agent;
mixing the at least one metal powder with the at least one foaming agent,
compacting the resulting mixture to form at least one precursor; and
foaming the at least one precursor by heating the at least one precursor in a mold until a defined degree of foaming is reached;
cooling the at least one precursor when the defined degree of foaming is reached to terminate the foaming, the cooled at least one precursor being at least one gas turbine component having a closed and supporting exterior wall.
2. The method as recited in claim 1 , wherein at least one supporting and/or function-relevant component made of a non-foamable material is at least partially surrounded by foam or partially embedded in foam during the foaming step.
3. The method as recited in claim 2 , wherein the at least one precursor to be foamed and the component to be partially surrounded by foam or partially embedded in foam are made of the same material.
4. The method as recited in claim 2 , wherein the at least one precursor to be foamed and the component to be partially surrounded by foam or partially embedded in foam are made of different materials.
5. The method as recited in claim 2 , wherein the at least one gas turbine component is a blade, and wherein when the at least one precursor is foamed in the mold, a blade root made of a non-foamable material is partially surrounded by foam or partially embedded in foam during the foaming step.
6. The method as recited in claim 2 , wherein the at least one gas turbine component includes a blade, and wherein the at least one precursor is foamed in a mold with at least one integrated flow channel, at least one component forming the flow channel being surrounded by foam during the foaming process.
7. The method as recited in claim 1 , wherein the at least one metal powder is selected from the group consisting of an aluminum-based alloy, a titanium-based alloy, a nickel-based alloy, an intermetallic alloy and combination thereof.
8. The method as recited in claim 1 , wherein the at least one foaming agent comprises titanium hydride.
9. The method as recited in claim 1 , wherein the compacting step comprises compacting by extrusion or axial pressing.
10. The method as recited in claim 1 , wherein the at least one metal powder includes a plurality of metal powders, each of the plurality of metal powders having different melting points.
11. The method as recited in claim 1 , wherein the at least one metal powder includes a plurality of metal powders, each of the plurality of metal powders having different powder granularities.
12. The method as recited in claim 1 , wherein said mixing comprises mixing the at least one metal powder with the at least one foaming agent and with a material selected from the group consisting of ceramic particles, ceramic fibers and combinations thereof.
13. The method as recited in claim 1 , wherein the at least one gas turbine component includes a plurality of individual blades or blade segments formed from a corresponding plurality of precursors, and wherein the method further comprises
fixedly joining the plurality of individual blades or blade segments with a forged or cast rotor carrier via soldering or welding.
14. The method as recited in claim 1 , further comprising, subsequent to the cooling step, coating a surface of the at least one gas turbine component.