Fluidic traverse actuator

Patent metadata

Field	Value
Publication number	US-9511849-B2
Application number	US-201213662466-A
Country	US
Kind code	B2
Filing date	Oct 27, 2012
Priority date	Oct 27, 2012
Publication date	Dec 6, 2016
Grant date	Dec 6, 2016

Abstract

A system and methods for a self-rotating fluidic traverse actuator are presented. A turbine rotates in response to a fluid flow, and an outer cylinder with a longitudinal slot that ejects the fluid flow. An inner cylinder rotates inside the outer cylinder in response to a rotation of the turbine and at least one helical slot of the inner cylinder ejects the fluid flow into the longitudinal slot.

First claim

The invention claimed is:

1. A self-rotating fluidic traverse actuator for an aircraft comprising:
a turbine operable to rotate in response to a fluid flow;
an outer cylinder comprising a longitudinal slot operable to eject the fluid flow; and
an inner cylinder operable to rotate inside the outer cylinder in response to a rotation of the turbine,
wherein the turbine is operable to introduce the fluid flow into the inner cylinder, and
wherein the inner cylinder comprises at least one helical slot operable to eject the fluid flow into the longitudinal slot.

2. The self-rotating fluidic traverse actuator of claim 1 , further comprising a fluid dynamic surface comprising an ejection slot coupled to the outer cylinder and operable to eject the fluid flow over the fluid dynamic surface.

3. The self-rotating fluidic traverse actuator of claim 2 , wherein the at least one helical slot induces a periodical fluid flow sweep on the fluid dynamic surface.

4. The self-rotating fluidic traverse actuator of claim 1 , wherein the turbine comprises an axial turbine with a plurality of radial turbine blades.

5. The self-rotating fluidic traverse actuator of claim 1 , wherein the turbine comprises one of: an axial turbine, a split turbine, a tangential turbine, a circumferential turbine, a combination manifolded axial/circumferential turbine, a helical turbine, and inward-oriented ribs running a length of the inner cylinder.

6. The self-rotating fluidic traverse actuator of claim 1 , further comprising a fluid flow bypass operable:
to direct a bypass portion of the fluid flow around the turbine; and
reintegrate the bypass portion with the fluid flow in the inner cylinder.

7. The self-rotating fluidic traverse actuator of claim 6 , wherein the turbine comprises the fluid flow bypass.

8. The self-rotating fluidic traverse actuator of claim 1 , further comprising:
a second outer cylinder comprising a second longitudinal slot operable to eject the fluid flow; and
a second inner cylinder operable to rotate inside the second outer cylinder in response to a rotation of the turbine and comprising at least one second helical slot operable to eject the fluid flow into the second longitudinal slot.

9. The self-rotating fluidic traverse actuator of claim 1 , wherein the helical slot comprises substantially of one or more full revolutions around the inner cylinder.

10. A method for configuring a self-rotating fluidic traverse actuator for an aircraft, the method comprising:
configuring a turbine to rotate in response to a fluid flow;
configuring a longitudinal slot in an outer cylinder;
configuring the longitudinal slot to eject the fluid flow;
configuring at least one helical slot in an inner cylinder;
configuring the inner cylinder to rotate inside the outer cylinder in response to a rotation of the turbine, wherein the turbine is configured to introduce the fluid flow into the inner cylinder; and
configuring the at least one helical slot to eject the fluid flow into the longitudinal slot.

11. The method of claim 10 , further comprising coupling the inner cylinder inside the outer cylinder.

12. The method of claim 10 , further comprising coupling the outer cylinder to a fluid dynamic surface comprising an ejection slot operable to eject the fluid flow over the fluid dynamic surface.

13. The method of claim 12 , further comprising configuring the outer cylinder such that the longitudinal slot aligns and overlaps the ejection slot under the fluid dynamic surface.

14. The method of claim 12 , further comprising configuring the ejection slot on an upper side of the fluid dynamic surface.

15. The method of claim 10 , further comprising coupling the turbine to the inner cylinder.

16. A method for operating a self-rotating fluidic traverse actuator for an aircraft, the method comprising:
rotating a turbine in response to a fluid flow;
rotating an inner cylinder comprising at least one helical slot inside an outer cylinder comprising a longitudinal slot in response to a rotation of the turbine;
introducing the fluid flow through the turbine into the inner cylinder;
ejecting the fluid flow into the at least one helical slot; and
ejecting the fluid flow out the longitudinal slot.

17. The method of claim 16 , further comprising guiding the fluid flow through the longitudinal slot and an ejection slot when the longitudinal slot and the at least one helical slot coincide.

18. The method of claim 16 , further comprising:
directing a bypass portion of the fluid flow around the turbine via a fluid flow bypass; and
reintegrating the bypass portion with the fluid flow in the inner cylinder.

19. The method of claim 18 , wherein the turbine comprises the fluid flow bypass.

20. The self-rotating fluidic traverse actuator of claim 1 , wherein the turbine comprises a split turbine.

Assignees

• Boeing Co

Inventors

• Shmilovich Arvin
• Kent Steven Richard

Classifications

• B64C2230/04

  by actively generating fluid flow · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic

• B64C21/04 Primary

  for blowing · CPC title

• Y10T29/4932

  Turbomachine making · CPC title

• Y02T50/10

  Drag reduction · CPC title