Inlet assembly for an aircraft aft fan
The present disclosure is directed to a low-distortion inlet assembly for reducing airflow swirl distortion entering an aft fan mounted to a fuselage of an aircraft. Further, the inlet assembly includes a plurality of structural members, such as struts or strakes, mounted at predetermined locations around a circumference of the fan shaft of the fan at the inlet. The predetermined location(s) may be determined as a function of swirl distortion entering the inlet. As such, the structural member(s) are configured to reduce swirl distortion of the airflow entering the fan. In some embodiments, the inlet assembly may also include inlet guide vanes. In alternative embodiments, the inlet assembly may be absent of inlet guide vanes.
1. A boundary layer ingestion fan assembly for mounting to an aft end of a fuselage of an aircraft, the boundary layer ingestion fan assembly comprising:
a fan rotatable about a central axis of the boundary layer ingestion fan assembly, the fan comprising a plurality of fan blades rotatable about a fan shaft;
a nacelle surrounding the plurality of fan blades of the fan, the nacelle defining an inlet with the fuselage of the aircraft, the inlet extending substantially around the fuselage of the aircraft when the boundary layer ingestion fan is mounted at the aft end of the aircraft;
a low-distortion inlet assembly configured with the inlet, the inlet assembly comprising:
one or more inlet guide vanes configured within the inlet; and
one or more structural members mounted at predetermined radial locations around a circumference of the fan shaft of the fan at the inlet, the structural members configured to reduce a swirl distortion entering the inlet of the fan.
2. The boundary layer ingestion fan assembly of claim 1 , wherein the one or more structural members comprise at least one of a strut or a strake.
3. The boundary layer ingestion fan assembly of claim 1 , wherein one or more of the structural members are integrated with at least one of the nacelle of the fan or the fuselage.
4. The boundary layer ingestion fan assembly of claim 3 , wherein the one or more structural members are integrated with and extend past the nacelle of the fan in a radial direction.
5. The boundary layer ingestion fan assembly of claim 1 , wherein one or more of the structural members extend in front of the nacelle of the fan in an axial direction.
6. The boundary layer ingestion fan assembly of claim 1 , wherein one or more of the structural members are spaced apart from and upstream of the nacelle of the fan in an axial direction.
7. The boundary layer ingestion fan assembly of claim 1 , wherein one or more of the structural members comprises a cambered cross-sectional shape configured to reduce swirl distortion entering the fan.
8. The boundary layer ingestion fan assembly of claim 1 , wherein one or more of the structural members are non-uniformly spaced around the circumference of the fan shaft.
9. A low-distortion inlet assembly for an aft fan mounted to a fuselage of an aircraft, the inlet assembly comprising:
a plurality of structural members mounted at predetermined radial locations around a circumference of the fan shaft of the fan at the inlet, the structural members configured to reduce a swirl distortion entering the inlet of the fan; and
wherein the inlet assembly is absent of inlet guide vanes.
10. The inlet assembly of claim 9 , wherein the one or more structural members comprise at least one of a strut or a strake.
11. The inlet assembly of claim 9 , wherein one or more of the structural members are integrated with at least one of the nacelle of the fan or the fuselage.
12. The inlet assembly of claim 11 , wherein the one or more structural members are integrated with and extend past the nacelle of the fan in a radial direction.
13. The inlet assembly of claim 9 , wherein one or more of the structural members extend in front of the nacelle of the fan in an axial direction.
14. The inlet assembly of claim 9 , wherein one or more of the structural members are spaced apart from and located upstream of the nacelle of the fan in an axial direction.
15. The inlet assembly of claim 9 , wherein one or more of the structural members comprises a cambered cross-sectional shape configured to reduce swirl distortion entering the fan.
16. The inlet assembly of claim 9 , wherein one or more of the structural members are non-uniformly spaced around the circumference of the fan shaft.
17. A method for retrofitting a boundary layer ingestion fan for an aft end of a fuselage of an aircraft with an inlet assembly configured to reduce swirl distortion at an inlet of the fan, the method comprising:
determining one or more radial locations around a circumference of a fan shaft of the fan having a swirl distortion exceeding a predetermined threshold; and
replacing one or more inlet guide vanes at the predetermined locations with one or more structural members.
18. The method of claim 17 , wherein the one or more structural members comprise at least one of a strut or a strake.
19. The method of claim 17 , further comprising replacing all of the inlet guide vanes with a fewer number of structural members.