A propeller engine (1) which is configured for providing thrust for an aircraft (100), in particular an aircraft (100) having vertical takeoff and landing capability, comprises a bearing structure (30); a propeller rotor (5) beared by the bearing structure (30), wherein the propeller rotor (5) includes multiple blades (51) and, upstream of the blades (51), a nose cone (50) which are attached to rotate with the propeller rotor (5), at least one electromotor (2) configured for driving the propeller rotor (5); and an air-cooling system (7) for at least one subsystem of the propeller engine (1) including at least one inlet opening (70) for receiving an intake stream of cooling air through the propeller rotor (5), wherein the air-cooling system (7) includes least one vortex chamber (71, 71a, 71b, 71c, 71d, 71e) connected to the propeller rotor (5), wherein the vortex chamber (71, 71a, 71b, 71c, 71d, 71e) is configured to receive the cooling air from the inlet opening (70) before the cooling air is provided to the at least one subsystem and/or wherein the at least one subsystem includes an electromotor subsystem (20) including a fluid barrier (21) separating a closed cooling circuit (8) containing electromotor electronics, in particular control electronics (21) and/or electromagnets, from the cooling air of the air-cooling system (7).
PROPELLER ENGINE AND AIRCRAFT
PROPELLERTRIEBWERK UND LUFTFAHRZEUG
MOTEUR À HÉLICE ET AÉRONEF
2024-11-27
Patent
Electronic Resource
English