Patent ID: 8522526
Filing Date: 2013-09-03
Classification: F02C,F05D,H02K

Abstract:
1. A two-shaft engine for aircraft with high electric power demand, comprising: a high-pressure shaft connected to at least one generator and driven by a high-pressure turbine, a low-pressure shaft driven by a low-pressure turbine, an electronic engine control system, an electromagnetic clutch connecting the low-pressure shaft to the high-pressure shaft for non-contact transmission of power from the low-pressure shaft to the high pressure shaft in a variable speed relationship, the electromagnetic clutch also connected to the engine control system, and wherein the engine control system controls the electromagnetic clutch to create a freely settable frequency-controllable rotary field in the electromagnetic clutch to compensate for significant speed ratio differences from idle to flight power conditions between the low-pressure shaft and the high-pressure shaft that allows the low-pressure shaft to transmit power to the high-pressure shaft even though the low-pressure shaft operates at a lower RPM than the high-pressure shaft.