US Patent 11788472 Engine bleed generators and aircraft generator systems

Aircraft generator systems are described. The aircraft generator systems include a main engine having a fan and a compressor section, a generator assembly having at least one expansion turbine operably connected to a generator, and a working fluid flow path defined between at least one extraction point at at least one of the fan and the compressor section of the main engine and at least one outlet, wherein the working fluid is configured to flow through the at least one expansion turbine to generate power at the generator. There are no heat exchangers arranged between the at least one extraction point and the at least one outlet along the working fluid flow path.