Inlet assembly for an aircraft aft fan

Patent metadata

Field	Value
Publication number	US-10259565-B2
Application number	US-201615234067-A
Country	US
Kind code	B2
Filing date	Aug 11, 2016
Priority date	Aug 11, 2016
Publication date	Apr 16, 2019
Grant date	Apr 16, 2019

Abstract

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 mounted at one or more predetermined locations around a circumference of the fan shaft of the fan. More specifically, the predetermined location(s) has a swirl distortion exceeding a predetermined threshold. Further, the inlet assembly includes at least one airflow modifying element configured within the inlet so as to reduce swirl distortion entering the fan.

First claim

What is claimed is:

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 assembly is mounted at the aft end of the aircraft;
a low-distortion inlet assembly mounted within the inlet, the inlet assembly comprising:
one or more structural members mounted at predetermined locations around a circumference of the fan shaft of the fan within the inlet, the predetermined locations comprising a swirl distortion exceeding a predetermined threshold; and
at least one airflow modifying element configured within the inlet so as to reduce swirl distortion entering the fan.

2. The boundary layer ingestion fan assembly of claim 1 , wherein the one or more structural members comprise at least one of an inlet guide vane or a strut.

3. The boundary layer ingestion fan assembly of claim 2 , further comprising a plurality of inlet guide vanes placed in groups at the predetermined locations around the circumference of the fan shaft.

4. The boundary layer ingestion fan assembly of claim 3 , wherein each of the plurality of inlet guide vanes comprises a shape and an orientation configured to reduce swirl distortion entering the fan.

5. The boundary layer ingestion fan assembly of claim 3 , wherein only a portion of the circumference of the fan shaft includes the plurality of structural members.

6. The boundary layer ingestion fan assembly of claim 1 , wherein the at least one airflow modifying element comprises at least one of a vortex generator, a contoured surface, a flap, or variable inlet guide vanes.

7. The boundary layer ingestion fan assembly of claim 6 , wherein the at least one vortex generator or flap is mounted on one of the plurality of structural members.

8. The boundary layer ingestion fan assembly of claim 6 , wherein the contoured surface is located on an inner surface of the nacelle.

9. The boundary layer ingestion fan assembly of claim 1 , further comprising at least one of trailing edge blowing, trailing edge suction, or angled flow injection configured to reduce flow distortion entering the fan.

10. The boundary layer ingestion fan assembly of claim 1 , wherein the predetermined locations are substantially evenly spaced with respect to the circumference of the fan shaft.

11. The boundary layer ingestion fan assembly of claim 2 , wherein a leading edge radius of one or more of the inlet guide vanes is designed as a function of the airflow conditions entering the fan.

12. The boundary layer ingestion fan assembly of claim 10 , wherein the leading edge radius of one or more of the inlet guide vanes varies in a span-wise direction as a function of the airflow conditions entering the fan.

13. 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 one or more predetermined locations around a circumference of the fan shaft of the fan within the inlet, the one or more predetermined locations comprising a swirl distortion exceeding a predetermined threshold; and
at least one airflow modifying element configured within the inlet of the aft fan so as to reduce swirl distortion entering the fan.

14. The inlet assembly of claim 13 , wherein the plurality of structural members comprise at least one of an inlet guide vane or a strut.

15. The inlet assembly of claim 13 , further comprising a plurality of inlet guide vanes placed in groups at the predetermined locations around the circumference of the fan shaft.

16. The inlet assembly of claim 13 , wherein only a portion of the circumference of the fan shaft includes the plurality of structural members.

17. The inlet assembly of claim 13 , wherein the at least one airflow modifying element comprises at least one of a vortex generator, a contoured surface, a flap, or variable inlet guide vanes.

18. The inlet assembly of claim 13 , wherein the at least one airflow modifying element is mounted on one of the plurality of structural members.

19. The inlet assembly of claim 12 , further comprising at least one of trailing edge blowing, trailing edge suction, or angled flow injection configured to reduce flow distortion entering the fan.

20. 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, the aft engine comprising a fan comprising a plurality of fan blades rotatable about a fan shaft and a nacelle surrounding the plurality of fan blades, the nacelle defining an inlet with the fuselage of the aircraft; and
a low-distortion inlet assembly mounted within the inlet, the inlet assembly comprising:
a plurality of structural members mounted at one or more predetermined locations around a circumference of the fan shaft of the fan within the inlet, the one or more predetermined locations comprising a swirl distortion exceeding a predetermined threshold; and
at least one airflow modifying element configured with the inlet so as to reduce swirl distortion entering the fan.

Assignees

• Gen Electric

Inventors

• Ramakrishnan Kishore
• Otta Shourya Prakash

Classifications

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title

• F04D29/38

  Blades {(for axial flow compressors F04D29/324)} · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title