A propulsion system (20) for an aircraft (1000) includes an engine assembly (22) and a turbocompressor (24). The engine assembly (22) includes an engine (30) and an interburner (34). The engine (30) includes an engine output shaft (38). The engine (30) is configured to drive rotation of a propulsor (1002) with the engine output shaft (38). The interburner (34) is configured to mix and burn an exhaust gas from the engine (30) with fuel to form a combustion gas. The turbocompressor (24) includes a turbine (60) and a compressor (58). The turbine (60) and the compressor (58) form a rotational assembly (70). The rotational assembly (70) includes a shaft (72), a bladed turbine rotor (76) of the turbine (60), and a bladed compressor rotor (74) of the compressor (58). The turbine (60) is connected in fluid communication with the interburner (34) to receive the combustion gas. The compressor (58) is connected in fluid communication with the engine (30) to direct a compressed air to the engine (30). The rotational assembly (70) is mechanically independent of the engine output shaft (38).
AIRCRAFT PROPULSION SYSTEM
FLUGZEUGANTRIEBSSYSTEM
SYSTÈME DE PROPULSION D'AÉRONEF
13.08.2025
Patent
Elektronische Ressource
Englisch