Electric propulsion engine for an aircraft
A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a power gearbox mechanically coupled to an electric motor. The electric propulsion engine further includes a fan rotatable about a central axis of the electric propulsion engine by the electric motor through the power gearbox. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor or the power gearbox. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor or the power gearbox.
1. A propulsion system for an aircraft having a structural member, the propulsion system comprising:
an electric propulsion engine configured to be mounted to the aircraft, the electric propulsion engine defining a central axis and comprising:
an electric motor;
a power gearbox mechanically coupled to the electric motor;
a fan rotatable about the central axis of the electric propulsion engine by the electric motor through the power gearbox;
a fan frame mounted about the central axis of the propulsion engine; and
an attachment assembly for mounting at least one of the electric motor or the power gearbox, the attachment assembly including a torsional damper for accommodating torsional vibration of the electric motor or the power gearbox, wherein the attachment assembly is configured to mount the electric motor to at least one of the fan frame or the bulkhead of the aircraft, and wherein the torsional damper is positioned between the electric motor and the at least one of the fan frame or the bulkhead.
2. The propulsion system of claim 1 , wherein the electric propulsion engine defines an axial direction, a radial direction, and a circumferential direction, and wherein the torsional damper of the attachment assembly provides dampening along each of the axial direction, radial direction, and circumferential direction of the electric propulsion engine.
3. The propulsion system of claim 1 , wherein the torsional damper of the attachment assembly comprises an elastomeric material for absorbing vibration.
4. The propulsion system of claim 1 , wherein the torsional damper of the attachment assembly comprises a plurality of interdigitated members and an elastomeric material positioned at least partially between the interdigitated members.
5. The propulsion system of claim 1 , wherein the torsional damper comprises one or more flexible couplings.
6. The propulsion system of claim 1 , wherein the electric propulsion engine is configured as a boundary layer ingestion fan.
7. The propulsion system of claim 1 , wherein the electric motor is mechanically coupled to the power gearbox through a drive shaft, and wherein the power gearbox is mechanically coupled to the fan through a fan shaft.
8. The propulsion system of claim 7 , wherein the drive shaft comprises a flexible element for accommodating misalignment.
9. The propulsion system of claim 8 , wherein the flexible element comprises a pair of bellows.
10. The propulsion system of claim 8 , wherein the flexible element comprises a torsional damper.
11. The propulsion system of claim 1 , wherein the electric propulsion engine is configured to be mounted to the aircraft along a mean line of the aircraft.
12. A boundary layer ingestion fan assembly for an aircraft having an aft end and a structural member, the boundary layer ingestion fan assembly comprising:
an electric motor;
a power gearbox mechanically coupled to the electric motor;
a fan rotatable about a central axis of the boundary layer ingestion fan assembly by the electric motor through the power gearbox;
a fan frame mounted about the central axis of the propulsion engine; and
an attachment assembly for mounting at least one of the electric motor or the power gearbox, the attachment assembly including a torsional damper for accommodating torsional vibration of the electric motor or the power gearbox, wherein the attachment assembly is configured to mount the power gearbox to at least one of the fan frame or the bulkhead of the aircraft, and wherein the torsional damper is positioned between the power gearbox and the at least one of the fan frame or the bulkhead.
13. The boundary layer ingestion fan assembly of claim 12 , wherein the boundary layer ingestion fan assembly defines an axial direction, a radial direction, and a circumferential direction, and wherein the torsional damper of the attachment assembly provides dampening along each of the axial direction, radial direction, and circumferential direction of the fan assembly.
14. The boundary layer ingestion fan assembly of claim 12 , wherein the torsional damper of the attachment assembly comprises at least one of an elastomeric material for absorbing vibration, viscous damper, or pneumatic damper.
15. The boundary layer ingestion fan assembly of claim 12 , wherein the torsional damper of the attachment assembly comprises a plurality of interdigitated members and an elastomeric material positioned at least partially between the interdigitated members.
16. The boundary layer ingestion fan assembly of claim 12 , wherein the torsional damper comprises one or more flexible couplings.
17. The propulsion system of claim 1 , wherein the attachment assembly includes a plurality of attachment members spaced along a circumferential direction of the electric propulsion engine for mounting of the electric motor.
18. The propulsion system of claim 1 , wherein the electric motor and the power gearbox are aligned with the central axis of the electric propulsion engine.