WE CLAIM:
1. A propulsion system for an aircraft having a fuselage, the propulsion
system comprising:
an aft engine configured to be mounted to the aircraft at an aft end of the aircraft, the aft engine defining a central axis and comprising:
a fan rotatable about the central axis of the aft engine and including a plurality of fan blades attached to a fan shaft;
a nacelle encircling the plurality of fan blades of the fan and extending around the mean line of the aircraft at the aft end of the aircraft when the aft engine is mounted to the aircraft; and
a structural support system for mounting the aft engine to the aircraft extending from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft.
2. The propulsion system as claimed in claim 1, wherein the aft engine is configured as a boundary layer ingestion fan.
3. The propulsion system as claimed in claim 1, wherein the structural support system includes a support shaft extending through the fan shaft.
4. The propulsion system as claimed in claim 3, wherein the support shaft is concentric with the fan shaft, and wherein the propulsion system further includes a bearing assembly between the fan shaft and the support shaft.
5. The propulsion system as claimed in claim 3, wherein the structural support system further includes one or more structural members extending from the structural support shaft to the nacelle.
6. The propulsion system as claimed in claim 5, wherein the one or more structural members are each configured as an outlet guide vane.
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7. The propulsion system as claimed in claim 1, wherein the structural support system includes one or more structural members attached to the nacelle at a location aft of the plurality of fan blades.
8. The propulsion system as claimed in claim 1, wherein the fan shaft is mechanically coupled to a power source located at least partially within the fuselage of the aircraft.
9. The propulsion system as claimed in claim 8, wherein the power source is configured as an electric motor.
10. The propulsion system as claimed in claim 8, wherein the power source is configured as an outrunner electric motor.
11. The propulsion system as claimed in claim 8, wherein the propulsion system further includes two or more aircraft engines, wherein the two or more aircraft engines at least in part drive an electric generator, and wherein the power source is configured as an electric motor in electrical communication with the electric generator.
12. The propulsion system as claimed in claim 1, wherein the fan is configured as a variable pitch fan.
13. The propulsion system as claimed in claim 1, wherein the nacelle defines an inlet extending substantially 360 degrees around the mean line of the aircraft when the aft engine is mounted to the aircraft.
14. The propulsion system as claimed in claim 1, wherein the aft engine is configured to be mounted to an aircraft having a pair of wings, and wherein the propulsion system further includes two or more aircraft engines, each of which mounted to one of the pair of wings of the aircraft.
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15. The propulsion system as claimed in claim 1, wherein the structural support system is configured for mounting to a bulkhead of the fuselage of the aircraft when the aft engine is mounted to the aircraft.
16. A boundary layer ingestion fan for mounting to an aircraft at an aft end of the aircraft, the boundary layer ingestion fan comprising:
a fan rotatable about a central axis of the boundary layer ingestion fan and
including a plurality of fan blades attached to a fan shaft;
a nacelle encircling the plurality of fan blades of the fan; and
a structural support system for mounting the aft engine to the aircraft
extending from the fuselage of the aircraft, through the fan shaft, and to the
nacelle when the aft engine is mounted to the aircraft.
17. The boundary layer ingestion fan as claimed in claim 16, wherein the structural support system includes a support shaft extending through the fan shaft.
18. The boundary layer ingestion fan as claimed in claim 17, wherein the support shaft is concentric with the fan shaft, and wherein the propulsion system further includes a bearing assembly between the fan shaft and the support shaft.
19. The boundary layer ingestion fan as claimed in claim 17, wherein the structural support system further includes one or more structural members extending from the structural support shaft to the nacelle.
20. The boundary layer ingestion fan as claimed in claim 19, wherein the one or more structural members are each configured as an outlet guide vane.