Nanostructured thermal protection coating for hydrogen fuel gas turbine and method for producing the same

By designing a gradient-decreasing three-layer nanostructure coating on hydrogen fuel cell gas turbines, the problem of insufficient corrosion resistance of existing coatings at high temperatures has been solved, achieving effective protection at higher temperatures, extending coating life, and making it suitable for various hydrogen fuel cell gas turbines.

CN118326307BActive Publication Date: 2026-07-14HARBIN INST OF TECH
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Patent Information

Application Number
CN202410452321.9
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2024-04-16
Publication Date
2026-07-14
Estimated Expiration
2044-04-16

AI Technical Summary

Technical Problem

Existing thermal protection coatings are insufficient to meet the operating requirements of hydrogen fuel cell gas turbines above 1200℃, and their high-temperature corrosion resistance is not ideal, leading to coating peeling and affecting unit operation.

Method used

A three-layer coating structure was designed, comprising a high-temperature alloy substrate, a bonding underlayer, a yttrium-stabilized zirconium oxide or zirconate intermediate layer, and a silicate top layer. The material of each layer decreases in a gradient. The coating is prepared by spraying technology, which improves the coating's resistance to water and oxygen corrosion and its thermal stress matching.

Benefits of technology

It effectively resists water and oxygen corrosion at high temperatures, extends the coating life, and is suitable for various hydrogen fuel gas turbines such as hydrogen fuel power generation gas turbines, hydrogen fuel marine gas turbines, and hydrogen fuel rocket engines.

✦ Generated by Eureka AI based on patent content.
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Abstract

The application discloses a nano-structure thermal protection coating for hydrogen fuel gas turbine and a preparation method thereof. The nano-structure thermal protection coating takes high-temperature alloy as a substrate, and sequentially deposits a bonding bottom layer, a yttrium stabilized zirconium oxide or zirconate intermediate layer and a silicate top layer on the surface of the substrate. The application starts from the design of the coating structure, and aims at the problems of low service temperature and poor water-oxygen corrosion resistance of the existing thermal protection coating for gas turbine. The water-oxygen corrosion resistance function of the silicate material is superimposed on the thermal protection coating for gas turbine, and the coating structure is optimized to form a new thermal protection coating structure resistant to high-temperature corrosion. The new thermal protection coating structure can not only meet more extreme service environments, but also resist water-oxygen corrosion at high temperature. The new thermal protection coating structure is suitable for hydrogen fuel power generation gas turbine, and is also suitable for hydrogen fuel or hydrogen mixed marine engines, hydrogen fuel rocket engines and other hydrogen fuel gas turbines.
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