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

摘要

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:; $$ \frac{{\alpha }_2\left(T_2\right)}{{\alpha }_1\left(T_1\right)}=x\frac{T_1-T_0}{T_2-T_0},$$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.