PROPULSION SYSTEM FOR AN AIRCRAFT

• Main Authors: GANSLER, Michael Thomas, HON, Robert Charles
• Format: Patent
• Language: English; French; German
• Published: 24.04.2024
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; AIRCRAFT; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; COSMONAUTICS; ENGINE PLANTS IN GENERAL; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; PARACHUTES; PERFORMING OPERATIONS; STEAM ENGINES; TRANSPORTING; WEAPONS

A hybrid-electric propulsion system (50) for an aircraft (10) includes a propulsor (104) and a turbomachine (102). The turbomachine (102) includes a high pressure turbine (116) drivingly coupled to a high pressure compressor (112) through a high pressure spool (122). The hybrid electric propulsion system (50) further includes an electrical system including a first electric machine, a second electric machine, and an electric energy storage unit (55) electrically connectable to the first and second electric machines. The first electric machine is coupled to the high pressure spool (122) of the turbomachine (102) and the second electric machine is coupled to the propulsor (104) for driving the propulsor (104) to provide a propulsive benefit for the aircraft (10). The hybrid electric propulsion system (50) also includes a controller configured to provide electrical power from an electric power source to the first electric machine to drive the first electric machine to start, or assist with starting, the turbomachine (102).