Efficient thermal protection hybrid thermodynamic cycle combined engine and control method thereof

By combining a rotating detonation engine and a turbine engine, and utilizing the design of mode switching and afterburner guide valves, the mode conversion difficulties and thermal protection problems of existing combined engines when crossing the thrust gap are solved, achieving an efficient thermal protection effect with a simple structure and high stability.

CN120720122AActive Publication Date: 2025-09-30TAIHANG LABORATORY
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Patent Information

Application Number
CN202511221322.3
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-08-29
Publication Date
2025-09-30
Estimated Expiration
2045-08-29

AI Technical Summary

Technical Problem

Existing turbine-ramjet, turbine-ramjet-rocket and turbine-precooling combination engines have problems such as difficulty in modal conversion, high structural complexity and complex control laws when crossing the thrust gap, making it difficult to achieve efficient thermal protection.

Method used

A combination of a rotating detonation engine and a turbine engine is used, and mode switching is achieved through an inlet regulating valve and an adjustable tail nozzle. Combined with the afterburner combustion chamber guide valve, the combustible mixture ejected from the rotating detonation engine is guided to the afterburner combustion chamber of the turbine engine for detonation combustion, and the cooling device of the afterburner combustion chamber is used for thermal protection.

Benefits of technology

It effectively connects the working upper limit of the turbine engine, bridges the thrust gap, has low structural design complexity, high system stability, and realizes efficient thermal protection to prevent the outer casing from being damaged by high temperature.

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Abstract

The invention relates to the technical field of aero-engines, and discloses an efficient thermal protection hybrid thermodynamic cycle combined engine and a control method thereof.The combined engine composed of an external rotary detonation engine and an internal turbine engine is adopted, and modal switching of the combined engine is achieved through an inlet adjusting valve and an adjustable exhaust nozzle; the working upper limit of a turbine engine can be effectively joined, power relay can be completed, so that a thrust gap is spanned, the structural design complexity is relatively low, the system stability is relatively high, and in a stress application rotating detonation mode, the reliability is high. Combustible mixtures sprayed by the rotary detonation engine are guided into the afterburner of the turbine engine through the afterburner diverter valve for detonation combustion, an original cooling device of the afterburner is used for thermal protection, and an outer casing is prevented from being damaged due to high temperature.
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