Patent ID: 9634597
Date: 2017-04-25
CPC Classifications: F01D,F02C,F05D,F16H,H02K,H02P

Claim:
1. An aircraft engine comprising: a driveshaft; an electrical apparatus, driven by the driveshaft, to generate electrical energy, a hydrodynamic torque converter with adjustable guide blades arranged between the driveshaft and the electrical apparatus; an adjustment mechanism for adjusting a position of the guide blades; a coupling mechanism arranged between the driveshaft and a shaft of the electrical apparatus, via which a drive torque generated by the electrical apparatus when operated as a motor can be supplied in a direction of the driveshaft; wherein the coupling mechanism includes a switch element, via which the hydrodynamic torque converter can be bypassed during a starting sequence performed by the drive torque generated by the electrical apparatus.