Embedded electric machine

A propulsion system for an aeronautical device comprising:

• an electric propulsor;
• and
• gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising
• a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
• a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
• a static frame member;
• a stator connection member and a rotor connection member;
• and
• an electric machine comprising a rotor and a stator, the rotor being rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine electrically connected to the electric propulsor, the stator connection member supporting the stator of the electric machine and mounted to the static frame member and the rotor connection member supporting the rotor of the electric machine, wherein at least one of the stator connection member or rotor connection member comprises a torsional damper such that the electric machine is flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both;
• wherein the stator connection member comprises the torsional damper such that the stator connection member flexibly mounts the stator to the static frame member.

A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

• a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
• a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
• a static frame member;
• an electric machine rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both, wherein the electric machine is positioned at least partially within or aft of the turbine section along the axial direction;
• and
• a power gearbox, the electric machine being mechanically driven by the rotary component through the power gearbox and the power gearbox being flexibly mounted to the static frame member.

A gas turbine engine defining a radial direction and an axial direction, the gas turbine engine comprising:

• a compressor section and a turbine section arranged in serial flow order, the compressor section and turbine section together defining a core air flowpath;
• a rotary component rotatable with at least a portion of the compressor section and with at least a portion of the turbine section;
• a static frame member;
• a rotor connection member;
• and
• an electric machine comprising a rotor and a stator, the rotor being rotatable with the rotary component, the electric machine positioned at least partially inward of the core air flowpath along the radial direction, the electric machine flexibly mounted to the static frame member, or flexibly coupled to the rotary component, or both, the rotor connection member supporting the rotor of the electric machine, wherein the rotor connection member flexibly couples the rotor to the rotary component of the gas turbine engine;
• a stator connection member supporting the stator of the electric machine,
• wherein the stator connection member flexibly mounts the stator to the static frame member.