Micro-mixing cluster nozzle structure of micro turbojet combustion chamber for changing aviation kerosene into hydrogen with variable flow channel and method

The micro-mixing nozzle structure with variable flow channel design solves the problems of backfire and thermoacoustic instability in micro turbojet combustion chambers, achieves efficient premixing of hydrogen and air, reduces NOx emissions and improves combustion efficiency, and is suitable for drones, cruise missiles and distributed energy systems.

CN122447728APending Publication Date: 2026-07-24HARBIN INST OF TECH
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Patent Information

Application Number
CN202610887555.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2026-06-18
Publication Date
2026-07-24

AI Technical Summary

Technical Problem

Existing micro-turbojet combustion chambers are prone to backfire, spontaneous combustion, and thermoacoustic instability, especially in hydrogen fuel applications, and traditional flow channel structures are not suitable for hydrogen fuel micro-hybridization.

Method used

The micro-mixing cluster nozzle structure of the aviation kerosene-to-hydrogen micro-turbojet combustor, which adopts a variable flow channel design, includes multiple micro-mixing units, an outer air guide ring, and an air distribution shroud. The premixing of hydrogen and air is achieved through the hydrogen distribution network and the air micro-mixing unit channels. The micro-pore array is optimized by combining metal 3D printing technology to ensure that hydrogen and air are fully mixed in front of the combustor.

Benefits of technology

It effectively suppresses the risk of backfire, reduces NOx emissions, and improves combustion efficiency and safety, while requiring no major modifications to the main engine structure, facilitating rapid upgrades.

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Abstract

The invention relates to the technical field of aviation power, in particular to a variable-runner micro-mixing cluster nozzle structure and method for an aviation kerosene-to-hydrogen micro turbojet combustion chamber. The nozzle structure comprises a plurality of micro-mixing units, an air outer flow guide ring and an air flow dividing cover, and each micro-mixing unit comprises a hydrogen supply channel, a hydrogen distribution pipe network, a hydrogen collection containing cavity, an air micro-mixing unit channel, a hydrogen-air premixing section and a premixed gas outlet; the hydrogen supply channel is used for supplying sufficient hydrogen to the micro-mixing unit, an inlet of the hydrogen collection containing cavity is communicated with an outlet of the hydrogen supply channel, and an inlet of the hydrogen distribution pipe network is communicated with an outlet of the hydrogen collection containing cavity; the hydrogen distribution pipe network is provided with a plurality of inlet channels and opposite outlet channels with the number twice that of the inlet channels. The nozzle structure can effectively improve the adaptability of the fuel of the micro turbojet engine from aviation kerosene to hydrogen, restrain tempering and reduce the carbon emission of the engine.
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