Hydrogen-ammonia mixed fuel turbine through-flow matching method and device

By adjusting the turbine blade installation angle to match the flow requirements of the hydrogen-ammonia mixed fuel, the problem of supercritical flow in gas turbine blades was solved, and efficient and stable operation of the gas turbine was achieved.

CN122242337APending Publication Date: 2026-06-19SHANGHAI JIAOTONG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
SHANGHAI JIAOTONG UNIV
Filing Date
2026-03-05
Publication Date
2026-06-19

AI Technical Summary

⚠Technical Problem

When existing gas turbines use hydrogen-ammonia mixed fuels, turbine blades are prone to supercritical flow and insufficient flow capacity, resulting in decreased efficiency and unstable output power.

⚗Method used

By calculating the outlet velocity and airflow angle changes of each stage of turbine blades, the blade installation angle is adjusted to match the flow path, ensuring that the turbine blades achieve flow path matching with small angle changes, suppressing supercritical phenomena and maintaining the unit's output power and efficiency.

🎯Benefits of technology

Without changing the compressor's operating point, it effectively reduces the gas velocity inside the turbine, suppresses supercritical phenomena, and maintains stable output power and efficiency of the gas turbine.

✦ Generated by Eureka AI based on patent content.

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Abstract

This invention relates to a flow matching method and apparatus for a hydrogen-ammonia mixed-fuel gas turbine in the field of gas turbine technology. Based on gas turbine model simulation, the thermodynamic parameters of each stage of turbine blades are obtained, the outlet flow area of ​​each stage of turbine blades is calculated, and the increase in outlet flow area is converted into a change in the corresponding blade outlet airflow angle. Based on this, combined with changes in gas velocity and blade installation angle adjustments, the adjusted blade inlet velocity triangle is obtained, and then the change in the inlet airflow angle of the next stage blade is calculated. Taking into account both the changes in the inlet and outlet airflow angles of each stage of blades, the adjustment value of the installation angle for each stage of turbine blades is determined. This invention achieves flow matching of the turbine section of a gas turbine without changing the compressor structural parameters, only adjusting the turbine blade installation angle. The adjusted gas turbine unit still maintains a work capacity comparable to the original unit, demonstrating good engineering applicability.
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