Component Comprising an Adhesive Structure for a Turbomachine, Method for Producing a Component with an Adhesive Structure for a Turbomachine and Turbomachine Comprising a Component with an Adhesive Structure

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This patent discloses a thermally and mechanically robust component for turbomachines, such as aircraft engines. The core innovation is a multi-layered element that features a specially structured adhesive (bond) layer—engineered with unique peak or trough geometries—between a metallic base and a ceramic top layer. This adhesive structure improves thermal barrier performance and attachment strength. The bond layer is formed using laser ablation techniques, creating undercut-free geometries tailored for strong ceramic adhesion and improved thermal fatigue performance.

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• Aircraft engine parts, such as combustion chamber walls, turbine blades, stator vanes, or protective liners, where high temperatures and mechanical loads are expected.
• Stationary gas and steam turbine components operating in high-temperature environments.
• High-temperature liners or barriers in energy generation systems (e.g., power plants) that require durable thermal insulation and protection.
• Advanced turbine design for aerospace and industrial applications, optimizing lifespan and maintenance needs.

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• Improved bonding strength between ceramic thermal barrier coatings and the underlying metal substrate, reducing the risk of coating delamination or spalling.
• Enhanced thermal and mechanical stability of turbomachine components, allowing them to operate reliably at higher temperatures and mechanical stresses.
• More efficient and economical manufacturing process using laser ablation for precise surface structuring.
• Customization of adhesive structures (lines, dots, grids, honeycomb, waves) for application-specific stress and thermal profiles.
• Greater protection against oxidation and thermal degradation, extending component life and reducing maintenance costs.
• Facilitates the design of complex, high-performance turbomachine parts for increasingly demanding aerospace and energy applications.

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Patent Abstract

A construction element, particularly adapted and configured for use in a turbo engine, in particular an aircraft engine, wherein a bond coat having a bond structure and thereabove a ceramic coat are disposed on a base. The lateral faces of the bond structure in the cross section are configured so as to be free of undercuts, wherein peak structures and/or trough structures are present, and the peak of the cross section of a peak structure has a mean peak angle (α) of less than or equal to 90°, most particularly less than 45°, and/or the trough structure has a valley angle in the range 90°≤β