Method for the manufacture of a component for high thermal loads, a component producible by this method and an aircraft engine provided with the component
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 α1 of the first metallic material and of a linear expansion coefficient α2 of the second metallic material is as: α 2 ⁡ ( T 2 ) α 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.
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