Vibration-reducing and noise-reducing spoiler for helicopter rotors, aircraft wings, propellers, and turbine blades

• US 7,413,408 B1
• Filed: 02/22/2007
• Issued: 08/19/2008
• Est. Priority Date: 02/22/2007
• Status: Expired due to Fees

• Current Assignee: Samuel B. Tafoya
• Original Assignee: Samuel B. Tafoya
• Inventors: Tafoya, Samuel B
• Primary Examiner(s): Look; Edward K.
• Assistant Examiner(s): White; Dwayne J
• Application Number:
  US11/709,613
• Time in Patent Office: 544 Days
• Field of Search: 416/228, 416/235, 416/240, 416/62, 416/100, 416/66, 244/215, 244/200, 244/213
• US Class Current: 416/228
• CPC Class Codes: B64C 21/10 using other surface properties, e.g. roughness
• CPC Class Codes: B64C 2230/14 achieving noise reductions
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A spoiler attached to helicopter main rotor blades, tail rotor blades, propellers, aircraft wings, and machined into turbine blades, that reduces vibration and silences their operation. Also, when added to a substantial part of the trailing edges of its rotor blades, the spoiler eliminates the repetitive pop-pop sound common to current helicopter flight. Preferably, the spoiler is made from durable resilient materials that bend with resistance for high speed oscillation and it is secured on the top or bottom side, or both, of the trailing edge of a blade or wing. Further, the free edge of the spoiler exhibits a non-repeating pattern of feather-like projections that collectively break up vortex formation so that the next wing or blade traveling through the same location has clean air/fluid in which to move. In addition to noise reduction, the spoiler increases blade efficiency and wing lift.

Claims

1. A replaceable spoiler for the trailing edges of blades and airfoils used for preventing the formation of an organized Karmen vortex on the top surface of the trailing edge where it would otherwise become a target for the next blade or airfoil entering the same air space and create undesired noise and vibration, said spoiler comprising:

a substantially thin and elongated flap made from resilient and flexible material that bends with resistance and is capable of high-speed oscillating movement without permanent deformation, said flap also having a distal edge with a plurality of projections each comprising a shape and pitch different from the next adjacent one of said projections, with said projections collectively defining a non-repeating pattern of angular indentations that when attached to a trailing edge directs airflow under the trailing edge rearward and downward to create disorganized discharge that will not sustain vortex formation.

2. The spoiler of claim 1 wherein said flap extends fully across the trailing edge to which it is secured.

3. The spoiler of claim 1 wherein said proximal surface is attached to rotors, propeller blades, and airfoils via attachment means selected from a group consisting of grooves, pre-machined grooves, rivets, bolts, self-locking bolts, adhesives, and bonding materials.

4. The spoiler of claim 1 wherein said proximal surface is attached to the trailing edges of rotors, propeller blades, and airfoils via at least one groove selected from a group consisting of grooves made in the top surface of a trailing edge and grooves made in the bottom surface of a trailing edge.

5. The improvement of claim 1 as applied to helicopters with at least two tail rotor blades, wherein said flap is secured to each of said at least two main rotor blades as a result of which noise and vibration of said helicopter during its operation are reduced.

6. The spoiler of claim 1 as applied to helicopters, winged aircraft, helicopters with a turbine blade system, winged aircraft with a turbine blade system, and marine vehicles with a turbine blade system, wherein said flap is secured to each of said at least two main rotor blades as a result of which noise and vibration of said helicopters, aircraft, and marine vehicles are reduced.

7. The spoiler of claim 1 as applied to helicopters, aircraft, and marine vehicles with at least one airfoil surface, wherein said projections are incorporated into said at least one airfoil surface whereby noise and vibration of said helicopters, aircraft, and marine vehicles are reduced.

8. The spoiler of claim 1 as applied to helicopters with at least two main rotor blades, wherein one of said flaps is secured to each of said at least two main rotor blades as a result of which noise and vibration of said helicopter during its operation are reduced.

9. The spoiler of claim 8 as applied to helicopters with at least one tail rotor, wherein said projections are incorporated into said at least one tail rotor whereby noise and vibration of said helicopter are reduced.

10. The spoiler of claim 9 as applied to helicopters with a turbine blade system, wherein said projections are is incorporated into said turbine blade system whereby noise and vibration of said helicopter are reduced.

11. The spoiler of claim 8 as applied to helicopters with a turbine blade system, wherein said projections are incorporated into said turbine blade system whereby noise and vibration of said helicopter are reduced.

12. A method for preventing the formation of an organized Karmen vortex on the top surface of the trailing edge where it would otherwise become a target for the next blade or airfoil entering the same air space and create undesired noise and vibration, said method comprising the steps of:

providing a substantially thin and elongated flap made from resilient and flexible material that bends with resistance and is capable of high-speed oscillating movement without permanent deformation, said flap also having a distal edge with a plurality of projections each comprising a shape and pitch different from the next adjacent one of said projections, with said projections collectively defining a non-repeating pattern of angular indentations; and

attaching said flap to a trailing edge so that said flap directs airflow under the trailing edge rearward and downward to create disorganized discharge that will not sustain vortex formation.

13. The method of claim 12 further comprising the steps of providing a spoiler having a non-repeating feathered pattern, and attaching said spoiler to said trailing edge.

14. The method of claim 12 wherein said non-repeating pattern is incorporated fully across said trailing edge.

15. The method of claim 12 as applied to helicopters with at least one rotor, wherein said projections are incorporated into said at least one rotor whereby noise and vibration of said helicopter are reduced.

16. The method of claim 12 as applied to helicopters with at least one tail rotor, wherein said projections are incorporated into said at least one tail rotor whereby noise and vibration of said helicopter are reduced.

17. The method of claim 12 as applied to helicopters, aircraft, and marine vehicles with a turbine blade system, wherein said projections are incorporated into said turbine blade system whereby noise and vibration of said helicopters, aircraft, and marine vehicles are reduced.

18. The method of claim 12 as applied to helicopters, aircraft, and marine vehicles with at least one airfoil surface, wherein said projections are incorporated into said at least one airfoil surface whereby noise and vibration of said helicopters, aircraft, and marine vehicles are reduced.