Method for producing a component for high thermal loads, a component that can be created using the method and an aircraft engine with the component

摘要

The method comprises providing a first area of a component (10) with a first metallic material by a generative laser process, where the first area is made of the first metallic material, providing a second area of the component with a second metallic material by a generative laser process, where the second area is made of the second metallic material, and depositing the first and/or second metallic materials by the generative laser process, where a ratio of the linear expansion coefficient of the first and second metallic materials is calculated by an equation as given in the specification. The method comprises providing a first area of a component (10) with a first metallic material by a generative laser process, where the first area is made of the first metallic material, providing a second area of the component with a second metallic material by a generative laser process, where the second area is made of the second metallic material, and depositing the first and/or second metallic materials by the generative laser process, where a ratio of the linear expansion coefficient of the first and second metallic materials is calculated by an equation as given in the specification. The generative laser process includes selective laser melting, laser cladding, selective laser sintering, and/or direct laser deposition. The first area and/or second area is formed as a cast part. The method further comprises building up a cooling element on the component by the selective laser sintering and/or selective laser melting, increasing a concentration of elements such as copper and/or aluminum with high thermal conductivity and high linear expansion coefficient in the metallic material of the second area, performing heat treatment such as hot isostatic pressing on the component, after application of metallic material to first and/or second areas, and forming a boundary surface or transition area that is present between the metallic materials or between the first area and the second area. An independent claim is included for a component of an aircraft engine.