Retractable vortex generator

• US 7,878,457 B2
• Filed: 06/30/2006
• Issued: 02/01/2011
• Est. Priority Date: 06/30/2005
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Narramore, Jimmy Charles
• Primary Examiner(s): Dinh; Tien
• Assistant Examiner(s): Green; Richard R
• Application Number:
  US11/477,806
• Publication Number:
  US 20070018056A1
• Time in Patent Office: 1,677 Days
• Field of Search: 244/200.1, 244/199.1, 244/199.4, 244/204.1, 244/198, 244/200, 244/201, 244/204, 244/206, 244/213, 244/91, 244/99.12, 244/99.13, 244/99.14, 244/76.C, 244/3.29, 244/113, 244/130
• US Class Current: 244/200.1
• CPC Class Codes: B64C 23/06 by generating vortices
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A flow control device is disclosed including a flow control surface over which fluid is designed to flow in a predetermined direction. Vortex generators are associated with the flow control surface. Each respective vortex generator has a pivot axis that forms an acute angle with respect to the predetermined direction and is capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie adjacent to the flow control surface. An actuator is associated with each of the vortex generators, each actuator adapted to position the associated vortex generator between the extended and retracted states. The flow control device is disclosed to be used in tiltrotor vehicles.

Claims

1. A flow control device comprising:

vortex generators associated with a flow control surface of an aircraft over which fluid is designed to flow in a predetermined direction, each respective vortex generator having a pivot axis that forms an acute angle with respect to the predetermined direction and capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie generally parallel to, and overlying and protruding from the flow control surface; and

an actuator associated with each of the respective vortex generators, each actuator adapted to position the associated vortex generator reversibly between the extended and retracted states,

wherein each of the respective vortex generators comprises a shape memory material, and wherein the actuator includes a heater configured to actuate the shape memory material from the retracted state to the extended state,

wherein the vortex generators are spaced from a leading edge of the flow control surface.

2. A flow control device according to claim 1, wherein the acute angle is from 5 to 45 degrees.

3. A flow control device according to claim 1, wherein each of the respective vortex generators is in the form of a fin that lies parallel to the flow control surface when in the retracted state and is set at an angle greater than 0 degrees and less than 180 degrees with respect to the flow control surface when in the extended state.

4. A flow control device according to claim 1, wherein the flow control surface is part of a tiltrotor vehicle.

5. A flow control device according to claim 1, wherein a surface of said vortex generator exposed to the fluid flow in the retracted state protrudes from said flow control surface when the control surface is exposed to the fluid flow.

6. A flow control device according to claim 1, wherein each actuator is configured to deploy the associated vortex generator from the retracted state into the extended state and to retract the associated vortex generator from the extended state into the retracted state.

7. A flow control device according to claim 1, wherein the vortex generators are positioned in a staggered fashion on the flow control surface such that pivot axes of two consecutive vortex generators form an angle.

8. A flow control device according to claim 1, wherein the vortex generators are disposed on the flow control surface and within a perimeter of the flow control surface.

9. A tiltrotor aircraft comprising:

a tiltrotor wing having a flow control surface over which fluid is designed to flow in a predetermined direction;

vortex generators associated with the flow control surface, each respective vortex generator having a pivot axis that forms an acute angle with respect to the predetermined direction and capable of being positioned in both of an extended state, in which the respective vortex generators function to create a swirling fluid flow, and a retracted state, in which the respective vortex generators are pivoted via the pivot axis so as to lie generally parallel to, and overlying and protruding from the flow control surface; and

an actuator associated with each of the respective vortex generators, each actuator adapted to position the associated vortex generator reversibly between the extended and retracted states,

wherein each of the respective vortex generators comprises a shape memory material, and wherein the actuator includes a heater configured to actuate the shape memory material from the retracted state to the extended state wherein the vortex generators are spaced from a leading edge of the flow control surface.

10. A tiltrotor aircraft according to claim 9, wherein the acute angle is from 5 to 45 degrees.

11. A tiltrotor aircraft according to claim 9, wherein each of the respective vortex generators is in the form of a fin that lies parallel to the flow control surface when in the retracted state and is set at an angle greater than 0 degrees and less than 180 degrees with respect to the flow control surface when in the extended state.

12. A tiltrotor aircraft according to claim 9, wherein a surface of said vortex generator exposed to the fluid flow in the retracted state protrudes from said flow control surface when the control surface is exposed to the fluid flow.

13. A tiltrotor aircraft according to claim 9, wherein the vortex generators are disposed on the flow control surface and within a perimeter of the flow control surface.