Blade vortex interaction noise reduction techniques for a rotorcraft

• US 5,711,651 A
• Filed: 06/13/1996
• Issued: 01/27/1998
• Est. Priority Date: 05/31/1994
• Status: Expired due to Term

• Current Assignee: McDonnell Douglas Helicopter Co. (The Boeing Co.)
• Original Assignee: McDonnell Douglas Helicopter Co. (The Boeing Co.)
• Inventors: Sankar, Lakshmi N., Hassan, Ahmed A., JanakiRam, Ram D., Charles, Bruce D., Tadghighi, Hormoz
• Primary Examiner(s): KWON, JOHN
• Application Number:
  US08/662,601
• Time in Patent Office: 593 Days
• Field of Search: 416/20, 416/24, 244/17.13, 244/17.15
• US Class Current: 416/24
• CPC Class Codes: B64C 2027/7266 actuated by actuators
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/463 Blade tips
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

An active control device for reducing blade-vortex interactions (BVI) noise generated by a rotorcraft, such as a helicopter, comprises a trailing edge flap located near the tip of each of the rotorcraft'"'"'s rotor blades. The flap may be actuated in any conventional way, and is scheduled to be actuated to a deflected position during rotation of the rotor blade through predetermined regions of the rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of the rotor azimuth. Through the careful azimuth-dependent deployment and retraction of the flap over the rotor disk, blade tip vortices which are the primary source for BVI noise are (a) made weaker and (b) pushed farther away from the rotor disk (that is, larger blade-vortex separation distances are achieved).

Claims

1. An active control device for reducing blade vortex-interaction (BVI) noise generated by a rotorcraft having a rotor blade including a tip end, a root end, a leading edge, and a trailing edge, said rotor blade being attached at said root end to a rotor hub on said rotorcraft and extending radially outwardly therefrom, having a radius R and a chord C, such that when said rotor hub is rotatably driven, said rotor blade rotates about said hub through a 360 degree azimuth, said active control device comprising:

a movable flap pivotally attached to said rotor blade trailing edge by a hinge oriented generally radially along said rotor blade, at least a portion of said flap being positioned near said rotor blade tip, in about the outboard 25% of the rotor blade radial length;

an actuator for deflecting and retracting the flap about said hinge;

wherein said flap is adapted to be actuated to a deflected position during rotation of said rotor blade through predetermined regions of said rotor azimuth, and is further adapted to be actuated to a retracted position through the remaining regions of said rotor azimuth, thereby functioning to reduce BVI noise during operation of said rotorcraft.

2. An active control device as recited in claim 1, wherein said trailing edge flap is of a unitary construction.

3. An active control device as recited in claim 1, wherein said trailing edge flap is comprised of a plurality of segments.

4. An active control device as recited in claim 1, wherein said trailing edge flap has a radial length of approximately 0.20 R.

5. An active control device as recited in claim 1, said rotor azimuth having first, second, third, and fourth quadrants, the first quadrant comprising 0 to 90 degrees azimuth, the second quadrant comprising 90 to 180 degrees azimuth, the third quadrant comprising 180 to 270 degrees azimuth, and the fourth quadrant comprising 270 to 360 degrees azimuth, wherein said trailing edge flap is adapted to be actuated according to a schedule such that it is in a deflected position when said rotor blade is advancing through at least a portion of said first and second quadrants.

6. An active control device as recited in claim 5, wherein said trailing edge flap is adapted, according to said schedule, to be always in a retracted position in said third and fourth quadrants.

7. An active control device as recited in claim 5, wherein said flap is adapted to be deflected in at least portions of each of said first and second quadrants.

8. A rotor blade for a rotorcraft, having a tip end, a root end, a leading edge, a trailing edge, a radius R and a chord C and further comprising:

a movable flap pivotally attached to said rotor blade trailing edge by a hinge oriented generally radially along said rotor blade, said flap being positioned near said rotor blade tip, in about the outboard 25% of the rotor blade radial length;

an actuator for deflecting and retracting the flap about said hinge;

said rotor blade being attached at said root end to a rotor hub on said rotorcraft, such that when said rotor hub is rotatably driven, said rotor blade rotates about said hub through a 360 degree azimuth;

wherein said flap is scheduled to be actuated to a deflected position during rotation of said rotor blade through predetermined regions of said rotor azimuth, and is further scheduled to be actuated to a retracted position through the remaining regions of said rotor azimuth, thereby functioning to reduce blade vortex-interaction (BVI) noise during operations of said rotorcraft.

9. A rotor blade as recited in claim 8, said rotor azimuth having first, second, third, and fourth quadrants, the first quadrant comprising 0 to 90 degrees azimuth, the second quadrant comprising 90 to 180 degrees azimuth, the third quadrant comprising 180 to 270 degrees azimuth, and the fourth quadrant comprising 270 to 360 degrees azimuth, said trailing edge flap being scheduled to be actuated such that it is in a deflected position when said rotor blade is advancing through at least a portion of two of said quadrants.

10. A rotor blade as recited in claim 9, wherein said trailing edge flap is scheduled to be always in a retracted position during rotation through the remaining two quadrants.

11. A rotor blade as recited in claim 9, wherein said flap is scheduled to be deflected during rotation through at least portions of each of said first and second quadrants.

12. A method for reducing blade vortex-interaction (BVI) noise generated by a rotorcraft having a rotor blade including a tip end, a root end, a leading edge, and a trailing edge, wherein said rotor blade is attached at said root end to a rotor hub on said rotorcraft and extends radially outwardly therefrom, such that when said rotor hub is rotatably driven, said rotor blade rotates about said hub through a 360 degree azimuth comprised of first, second, third, and fourth quadrants, the first quadrant comprising 0 to 90 degrees azimuth, the second quadrant comprising 90 to 180 degrees azimuth, the third quadrant comprising 180 to 270 degrees azimuth, and the fourth quadrant comprising 270 to 360 degrees azimuth, said rotor blade further comprising a movable flap pivotally attached to said trailing edge, said method comprising the steps of:

a) actuating said flap to a deflected position during rotation of said rotor blade through predetermined regions of said rotor azimuth, thereby reducing the strength of blade tip vortices and increasing the separation of said blade tip vortices and the rotor blade tip, such that said BVI noise is reduced; and

b) actuating said flap to a retracted position during rotation of said rotor blade through the remaining regions of said rotor azimuth.

13. A method for reducing BVI noise as recited in claim 12, wherein said flap is actuated to a deflected position when said rotor blade is advancing through at least a portion of two of said quadrants.

14. A method for reducing BVI noise as recited in claim 13, wherein said flap is actuated to a retracted position during the entire time said rotor blade is rotating through the remaining two quadrants.

15. A method for reducing BVI noise as recited in claim 12, wherein said flap is actuated to a deflected position when said rotor blade is rotating through at least portions of each of said first and second quadrants.