Air vehicle dual-flow turbine engine assembly equipped with angle-of-attack control air discharge fins
By adjusting the angle of attack control of the exhaust fins, the problem of backflow interference in the secondary flow path of ultra-high bypass ratio turbine engines was solved, and effective exhaust airflow introduction was achieved under different configurations, improving the quality of the reverse thrust airflow and the reverse thrust level.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SAFRAN AIRCRAFT ENGINES SAS
- Filing Date
- 2021-11-02
- Publication Date
- 2026-07-21
AI Technical Summary
In ultra-high bypass ratio turbine engines, the reverse thrust airflow in the secondary flow path is interfered with by the reverse flow of the exhaust airflow at the outlet of the low-pressure compressor, resulting in insufficient reverse thrust level, and the traditional design cannot install a thrust reversal system.
By adjusting the angle of attack of the exhaust fins, it is ensured that the exhaust airflow can be axially and concurrently introduced into the secondary flow path in both the normal propulsion and thrust reversal configurations of the turbine engine. Movable exhaust fins and control devices are used to adjust the direction of the fins according to the configuration.
It enables the effective introduction of exhaust airflow under different configurations, ensuring the quality of reverse thrust airflow and reverse thrust level, and adapting to various operational requirements of turbine engines.
Smart Images
Figure CN116438370B_ABST