Self-adaptive hybrid air suction system of aviation piston engine

By using an adaptive hybrid air intake system, which utilizes a nickel-titanium-based shape memory alloy guide ring and an adjustable air intake mechanism, the problem of low efficiency and slow response of traditional air intake systems under complex flight conditions is solved, and efficient air intake and power output of aero-piston engines under different operating conditions are achieved.

CN121382415APending Publication Date: 2026-01-23SHANGHAI LINGXIANG TECHNOLOGY CO LTD
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Patent Information

Application Number
CN202511517381.5
Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Filing Date
2025-10-23
Publication Date
2026-01-23

AI Technical Summary

Technical Problem

Traditional aircraft piston engines have mechanically fixed air intake duct shapes and guide vane angles, which cannot adapt to complex and ever-changing flight conditions, resulting in low efficiency and slow response.

Method used

An adaptive mixing intake system is adopted, which utilizes a nickel-titanium-based shape memory alloy guide ring and an adjustable intake mechanism. The intake angle and shape are adjusted by the phase change of the shape memory alloy spring. Combined with a vortex generator and a compressor unit, gas mixing and compression are achieved. The toroidal iron core transformer and linkage mechanism are combined to improve response speed and stability.

Benefits of technology

Improving intake efficiency under different flight conditions enhances the system's adaptability and response speed, ensures power output stability and combustion efficiency, improves fuel economy, and enhances structural stability and environmental adaptability.

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Abstract

The invention relates to the technical field of air intake systems of aero-engines, and discloses a self-adaptive hybrid air suction system of an aero-piston engine, which comprises an engine body for providing power for aviation flight, and is characterized in that an air suction unit for air intake is fixedly arranged at one end of an inner cavity of the engine body; the air suction unit comprises an air suction part used for air suction, a vortex generator used for improving air mixing and an air inlet adjusting mechanism used for adjusting the air inlet angle, the air inlet adjusting mechanism is fixedly connected with the air suction part through the vortex generator, and an air compression unit used for compressing air is fixedly arranged at one end of the air suction unit; the end, away from the air suction unit, of the air compression unit is fixedly connected with a combustion unit used for combusting compressed air, the end, away from the air compression unit, of the combustion unit is fixedly connected with an exhaust unit used for exhausting air to provide power, the air inlet mechanism can be adjusted to dynamically adapt to the flight working condition, the air inlet efficiency and stability are improved, and the response speed is increased; and the combustion efficiency is optimized.
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