Hybrid aircraft propulsion system with electric motor alignment

Abstract

A hybrid aircraft propulsion system includes a first motor operatively connected to a propulsor via a first motor driveshaft and is mounted to an engine static structure through engine mounts operable to adjust a position of the first motor and the first motor driveshaft. A second motor is an electric motor having a second motor driveshaft which is coaxial to the first motor driveshaft. The second motor is operatively connected to the propulsor via the second motor driveshaft to selectively drive the propulsor. A height compensation structure is operatively connected to the second motor and structured to adjust axial alignment of the second motor driveshaft relative to the first motor driveshaft to make the first motor driveshaft more coaxial to the second motor driveshaft.

Dependencies are inferred from the claim text.