Hybrid-electric propulsion system for multi-engine aircraft

摘要

The invention relates to a hybrid-electric propulsion system 10 for multi-engine aircraft 20. It comprises at least a first and a second hybrid-electric propulsion unit 31, 32, each of which has an internal combustion engine 41, 42, a motor-generator unit 71, 72 and a transmission 51, 52 for transmitting drive power to a propeller 61, 62. In a primary operating mode, the propellers 61, 62 receive the drive power predominantly or entirely from the internal combustion engines 41, 42 coupled to the respective transmission 51, 52. In a secondary operating mode, the first or the second internal combustion engine 41, 42 transmits drive power via the first or second gear 51, 52 to the first or second propeller 61, 62 and the first or second motor-generator unit 71, 72, whose generated electrical power is transmitted via the transmission device 80 the second or first motor-generator unit 72, 71, which in turn is driven via the second or first gearbox 5 2, 51 transmits drive power to the second or first propeller 62, 61 and the second or first internal combustion engine 42, 41 is switched off or does not transmit any drive power. The following advantages result:1. Optimization of the operating range of the thermal machines and a reduction of the specific fuel consumption2. Weight-optimized design compared to high-capacity, battery-based hybrid concepts3. Significant reduction in the operating times of the individual thermal machines in alternating use compared to the aircraft operating hours.4. Increased operational safety for the safety-relevant failure of a thermal machine and the avoidance of asymmetric thrust.