Multilayer Ceramic for Use in Gas Turbines

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This invention introduces a multilayer ceramic component designed for use in gas turbine combustion chambers. Unlike traditional metal-based parts, this component is constructed from several ceramic films or pre-ceramic papers layered according to specific requirements. The multilayer structure allows for tailored material properties at different locations (hot gas side, cold side, and core), resulting in improved performance under the extreme conditions found within turbines. The patent also describes methods for manufacturing such components and their integration into combustion chambers.

Use CasesContent extracted from patent full text and abstract with AI.

• Liners, shields, and structural parts within gas turbine combustion chambers for power plants or aircraft engines
• Replacement of traditional metallic combustion chamber parts with ceramic alternatives to improve longevity and performance
• Customization of ceramic components for other high-temperature or corrosive environments beyond gas turbines, such as industrial furnaces or chemical reactors
• Applications in advanced combustion systems (like can-type or annular combustion chambers) requiring enhanced thermal and mechanical robustness

BenefitsContent extracted from patent full text and abstract with AI.

• Significantly increased component longevity and resistance to thermal shock, erosion, and corrosion compared to metal parts
• Potential for higher overall efficiency in gas turbines due to reduced cooling air requirements and better heat insulation
• Cost reductions in manufacturing and maintenance arising from extended service life and lower degradation rates
• Greater design flexibility, as the multilayer structure can be precisely tailored to different temperature, mechanical, or chemical demands within a single component
• Improved operational availability for turbine operators due to reduced downtime and longer intervals between service or replacement of parts

Technical Classifications (CPCs)

Inventors & Applicants

Patent Abstract

The invention relates to a component for a combustion chamber of a gas turbine, which component has a multi-layer structure in the form of ceramic films and/or paper made of pre-ceramic material, the inner and outer structure of the component being matched to the dimensions and conditions in the gas turbine combustion chamber. The invention further relates to a gas turbine combustion chamber having the component and to a method for producing the component.