AIRCRAFT PROPULSION ARCHITECTURE INTEGRATING AN ENERGY RECOVERY SYSTEM

摘要

In an aircraft provided with a main rotor, a rear rotor, at least one propulsion turbine and a power supply system, a thermal energy recovery device is installed on the turbine to generate energy. using a thermal energy contained in the exhaust gas of the turbine as a hot source and one of the following sources as a cold source: the ambient air, a motor oil, a fuel oil or a cooling fluid of the turbine. The recovery device comprises a transformation machine including an electric generator connected to the power supply system provided with a reconfiguration system adapted to be reconfigured so as to feed a main power bar of the aircraft by means of the device. thermal energy recovery in case of loss of a main generation.