A three-duct variable-ratio multi-mode aero-engine

By designing a three-duct variable-ratio multi-mode aero-engine, utilizing a mode selection valve and an internal axial series dual-combustion chamber structure, the problem of reduced power output of aero-engines during high-speed flight was solved, achieving wide-speed-range flight and efficient thrust output, while reducing manufacturing complexity and cost.

CN121363472BActive Publication Date: 2026-05-26NANCHANG HANGKONG UNIVERSITY
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
NANCHANG HANGKONG UNIVERSITY
Filing Date
2025-12-10
Publication Date
2026-05-26

AI Technical Summary

Technical Problem

Existing aero engines experience a sharp decrease in power output due to increased intake air temperature and reduced flow capacity during high-speed flight, making it impossible to achieve wide-range flight and higher cruise speeds.

Method used

Design a three-duct variable pressure ratio multi-mode aero-engine. The opening and closing of the inner and outer bypass ducts are controlled by a mode selection valve to change the pressure ratio under different modes. The engine adopts an inner axial series dual combustion chamber structure and utilizes three combustion chamber operating modes to achieve switching between three-duct, dual-duct, and single-duct modes, and adjust the airflow distribution to adapt to flight requirements at different Mach numbers.

Benefits of technology

It achieves high efficiency and high thrust in the Mach 0-3 range, broadens the flight speed range, improves gas flow capability and thrust output, and reduces the complexity and cost of engine manufacturing.

✦ Generated by Eureka AI based on patent content.

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Abstract

This invention provides a three-duct variable pressure ratio multi-mode aero-engine, belonging to the field of aero-engine technology. It includes a front fan, a rear fan, and a tail nozzle. The front and rear fans are connected to the tail nozzle via an inner duct and a second outer duct. The inner duct includes a low-pressure compressor, a high-pressure compressor, a front combustion chamber, a high-pressure turbine, a rear combustion chamber, and a low-pressure turbine. The front fan, rear fan, low-pressure compressor, and low-pressure turbine are connected by a low-pressure rotor. This invention employs an inner duct axially tandem dual-combustion chamber structure, utilizing the dual combustion chambers to achieve three combustion chamber operating modes. A mode selection valve controls the duct mode switching and the airflow direction of the second outer duct, enabling switching between multi-duct and single-duct configurations and changing the pressure ratio under different modes. This ensures sufficient thrust and good fuel economy, and widens the flight speed range.
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