Variable area flow duct employing secondary flows, and method therefor

• US 8,015,794 B2
• Filed: 10/20/2006
• Issued: 09/13/2011
• Est. Priority Date: 10/20/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Winkler, Chad M, Wright, Matthew J
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): Dwivedi; Vikansha S
• Application Number:
  US11/551,369
• Publication Number:
  US 20080092518A1
• Time in Patent Office: 1,789 Days
• Field of Search: 602/04, 602/42, 602/62, 602/71, 239/265.17
• US Class Current: 60/204
• CPC Class Codes: F02K 1/30 for varying effective area of jet pipe or nozzle
• CPC Class Codes: F02K 9/974 Nozzle- linings; Ablative coatings

Abstract

A variable area flow duct and method. In one embodiment the flow duct includes a plurality of helical vanes arranged around an interior surface wall of the flow duct. The vanes cause secondary flow vortices to be developed in the vicinity of each of the vanes that effectively reduce the interior cross-sectional area of the duct that a primary flow sees as it flows through the duct. In various embodiments fluidic injection is employed to suppress the formation of the secondary flow vortices during certain phases of operation, for example, during an afterburn phase of operation of a jet aircraft engine which the flow duct is being used with. In another embodiment, an ablative coating is used over the vanes to suppress the formation of the secondary flow vortices. The ablative material is removed by the hot fluid flow during an afterburn phase of operation, thus exposing the vanes and enabling the subsequent formation of secondary flow vortices to narrow the cross-sectional area of the throat.

Claims

1. A flow duct comprising:

a circumferential wall having an inner surface, the inner surface defining a fluid flow path for a primary flow flowing through the flow duct; and

at least one curving projection forming a non-moveable vane, and formed to project from the circumferential wall of the inner surface of the flow duct such that the non-moveable vane projects radially inwardly toward an axial center of the flow duct and non-parallel to a longitudinal centerline extending along the axial center of the flow duct, the non-moveable vane for generating a secondary flow adjacent the inner surface that effectively reduces an internal cross-sectional area of the duct for said primary flow.

2. The flow duct of claim 1, wherein said non-moveable vane extends in a helical path from the inner surface of the circumferential wall of the flow duct.

3. The flow duct of claim 1, further comprising a plurality of longitudinally spaced apart, non-moveable vanes arranged on said inner surface of the circumferential wall of the flow duct, with each of said non-moveable vanes forming a helical vane.

4. The flow duct of claim 1, further comprising at least one opening formed in said circumferential wall of said flow duct for injecting a fluid jet into said flow duct adjacent said non-moveable vane, the fluid jet suppressing the formation of said secondary flow by said non-moveable vane.

5. The flow duct of claim 1, further comprising a coating applied to said inner surface to at least partially cover said non-moveable vane, to at least partially impede the formation of said secondary flow;

and

the coating being able to be dissipated during a predetermined phase of use of the flow duct, to then enable said non-moveable vane to form said secondary flow.

6. The flow duct of claim 1, wherein said flow duct comprises an exhaust nozzle of a jet engine.

7. The flow duct of claim 1, further comprising a plurality of axially spaced apart projections arranged circumferentially on said inner surface of said wall of said duct, each of said projections forming a helical vane.

8. The flow duct of claim 6, further comprising a plurality of openings formed in said wall adjacent said helical vanes for enabling a plurality of fluid jets to be directed into said duct, said fluid jets suppressing the formation of secondary flows adjacent each of said helical vanes.

21. The flow duct of claim 1, wherein said non-moveable vane extends at an angle non-parallel to a longitudinal axis of the flow duct.

22. The flow duct of claim 21, wherein said non-moveable vane extends at an angle of about 45 degrees relative to the longitudinal axis of the flow duct.

9. A flow duct comprising:

a circumferential wall having an inner surface, the inner surface defining a fluid flow path of a primary flow flowing through the flow duct;

a plurality of non-moveable vanes extending radially inwardly toward an axial center of the flow duct from said inner surface of the circumferential wall, and further such that said non-moveable vanes extend non-parallel to a longitudinal centerline of the flow duct, the non-moveable vanes generating a plurality of secondary flows adjacent the inner surface that reduce an internal cross-sectional area of the flow duct for said primary flow; and

a plurality of fluid jets controllably injected through openings in said circumferential wall adjacent said non-moveable vanes, for suppressing the formation of said secondary flows.

10. The flow duct of claim 9, wherein at least some of said non-moveable vanes comprise helical vanes projecting from said inner surface.

11. The flow duct of claim 10, wherein at least some of said helical vanes are arranged generally at an angle relative to a longitudinal centerline extending through said flow duct.

12. The flow duct of claim 9, further comprising a dissipative coating covering at least a subplurality of said non-moveable vanes that prevents the formation of said secondary flows.

13. The flow duct of claim 12, wherein said dissipative coating comprises an ablative coating.

23. The flow duct of claim 9, wherein said non-moveable vane extends at an angle non-parallel to a longitudinal axis of the flow duct.

14. A method for controlling a flow of a fluid flowing through a duct, comprising:

forming a non-moveable vane on an interior circumferential wall of said duct such that said non-moveable vane projects radially inwardly toward an axial center of said duct and non-parallel to a longitudinal centerline of said duct;

flowing a fluid through said duct to form a primary flow; and

using said non-moveable vane to form a secondary flow adjacent said non-moveable vane, said secondary flow causing a reduction of an effective cross sectional area within said duct for said primary flow.

15. The method of claim 14, further comprising:

injecting a fluid jet through said interior circumferential wall of the duct in a vicinity of said non-moveable vane to suppress the formation of said secondary flow.

16. The method of claim 14, further comprising:

using a dissipative coating to cover said non-moveable vane to prevent said secondary flow from forming; and

causing said dissipative coating to dissipate during a predetermined phase of use of said duct, to thus expose said non-moveable vane and enable the formation of said secondary flow.

17. The method of claim 14, wherein the forming a non-moveable vane on said interior circumferential wall comprises forming a helical vane on said interior circumferential wall.

18. The method of claim 14, further comprising using a plurality of non-moveable vanes spaced apart from another, and arranged generally circumferentially about said interior circumferential wall of said duct, to cause a corresponding plurality of secondary flows adjacent said plurality of non-moveable vanes.

19. The method of claim 18, further comprising injecting a plurality of fluid jets through said interior circumferential wall of said duct at areas adjacent to each one of said plurality of non-moveable vanes to generate a plurality of secondary flows within said duct.

20. A mobile platform comprising:

an engine;

an exhaust nozzle operably associated with said engine to receive a primary fluid flow from said engine;

said exhaust nozzle having a circumferential inner surface, the circumferential inner surface defining a fluid flow path for said primary flow; and

a plurality of non-moveable vanes extending from said circumferential inner surface radially inwardly toward an axial center of said exhaust nozzle, and non-parallel to a longitudinal centerline of said exhaust nozzle, for generating a plurality of secondary flows adjacent said circumferential inner surface that effectively reduce an internal cross-sectional area of said exhaust nozzle for said primary flow.

24. The method 14, wherein the non-moveable vane is formed so as to extend non-parallel to a longitudinal axis of the duct.