Reflux combustion chamber head structure and an aeroengine

By using a floating snap-fit ​​connection between the flame tube and the guide plate in the head structure of the recirculation combustion chamber, and setting the vortex generator and fuel nozzle coaxially, the problem of uneven fuel distribution caused by misalignment of the fuel nozzle centerline is solved, the flow field distribution in the combustion chamber is improved, and the machining accuracy and service life of the flame tube are increased.

CN121854899BActive Publication Date: 2026-06-05AECC HUNAN AVIATION POWERPLANT RES INST
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
AECC HUNAN AVIATION POWERPLANT RES INST
Filing Date
2026-03-18
Publication Date
2026-06-05

AI Technical Summary

Technical Problem

In the existing recirculation combustion chamber head structure, the center lines of the fuel nozzle and the flame tube are not aligned when hot, resulting in uneven fuel distribution, which affects the temperature distribution and flow field stability at the combustion chamber outlet. At the same time, the welded structure causes deformation of the flame tube and shortens its service life.

Method used

The flame tube and the guide plate assembly are connected by a floating snap-fit. The vortex generator and fuel nozzle are set coaxially with the flame tube. The thermal expansion difference is coordinated by the elastic connection to avoid deformation and stress concentration caused by welding.

Benefits of technology

Ensure that the fuel nozzle is aligned with the centerline of the vortex generator and the flame tube in all operating conditions, improve the flow field distribution, increase combustion efficiency and structural reliability, and extend the service life of the flame tube.

✦ Generated by Eureka AI based on patent content.

Smart Images

  • Figure CN121854899B_ABST
    Figure CN121854899B_ABST
Patent Text Reader

Abstract

The application discloses a backflow combustion chamber head structure and an aero-engine. The structure comprises a flame tube mechanism and a pneumatic atomization mechanism arranged between a casing and the flame tube mechanism. The flame tube mechanism comprises a flame tube assembly arranged in the casing and a guide vane assembly axially penetrating into the flame tube assembly and floatingly connected with the flame tube assembly. The pneumatic atomization mechanism comprises a vortex generator assembly coaxially arranged with the flame tube assembly and an oil nozzle assembly. The vortex generator assembly is inserted into the guide vane assembly and fixed with the flame tube assembly. The spray end of the oil nozzle assembly is fixed with the vortex generator assembly, and the mounting end of the oil nozzle assembly is used for floatingly connecting with the casing. The flame tube assembly, the vortex generator assembly and the oil nozzle assembly are fixed as a whole, so that relative displacement between the three assemblies in the axial and radial directions can be effectively prevented. In various working conditions of the aero-engine, the center line of the oil nozzle assembly and the flame tube assembly can be ensured to be aligned, and uniform distribution of fuel oil can be ensured.
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