Half-plow vortex generators for rotorcraft blades for reducing blade-vortex interaction noise

• US 5,785,282 A
• Filed: 08/07/1996
• Issued: 07/28/1998
• Est. Priority Date: 08/18/1995
• Status: Expired due to Term

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Landgrebe, Anton J., Wake, Brian E., Lorber, Peter F.
• Primary Examiner(s): Oberleitner, Robert J.
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/693,579
• Time in Patent Office: 720 Days
• Field of Search: 244/199, 244/130, 244/200, 244/198
• US Class Current: 244/199.2
• CPC Class Codes: B64C 27/463 Blade tips

Abstract

In one embodiment for a helicopter main rotor assembly, a half-plow vortex generator is mounted in combination with the upper aerodynamic surface of each main rotor blade and is operative to generate a primary corotating vortex of sufficient strength to interact with and dissipate the tip vortex generated by the same main rotor blade, thereby reducing blade-vortex interaction noise radiating from the helicopter main rotor assembly. The half-plow vortex generator has a right triangular planform configuration defined by a length, a width, and an apex angle. The three-dimensional configuration of the vortex generator is further defined by an apex height. The apex height is the primary determinant of the strength of the generated primary corotating vortex and is defined in terms of the magnitude of the local chord where the vortex generator is mounted. The apex height preferably has a magnitude within the range of about 0.01 to about 0.08 of the magnitude of the local chord. The length, width, and apex angle are secondary determinants of the strength of the primary corotating vortex generated by the half-plow vortex generator. The length and width of the vortex generator are also defined in terms of the magnitude of the local chord, the length preferably having a magnitude within the range of about one-fourth to about one-half of the magnitude of the local chord and the width preferably having a value of about one-third of the length of the vortex generator. The apex angle preferably has a value within the range of about twenty to about thirty degrees. The mounting site for the half-plow vortex generator is defined in terms of the length of the local and tip chords. The vortex generator is mounted inboardly from the tip of the main rotor blade a spanwise distance having a magnitude preferably within the range of about one-half to about equal to the tip chord length and is mounted with the length thereof in substantial alignment with the local chord. The apex of the vortex generator is mounted inwardly from the leading edge of the main rotor blade by a chordal distance having a magnitude of about one-quarter of the magnitude of the local chord.

Claims

1. A vortex generator system for use with a rotor blade defined by a tip chord, comprising:

a half-plow vortex generator having a right triangular planform configuration;

said right triangular planform configuration being defined by a length, a width, and an apex angle, and an apex height;

said apex height, in combination with said length, said width, and said apex angle of said right triangular planform configuration defining the three-dimensional configuration of said half-plow vortex generator; and

wherein

said half-plow vortex generator is mounted in combination with an aerodynamic surface of the rotor blade at a mounting site defined by a local chord, said mounting site being inboardly from the tip of the rotor blade a predetermined spanwise distance from the tip of the rotor blade, said predetermined spanwise distance being defined in terms of the tip chord length, and wherein said half-plow vortex generator is further mounted inwardly from the leading edge of the rotor blade by a predetermined chordal distance, said predetermined chordal distance being defined in terms of the length of said local chord; and

wherein

said length of said mounted half-plow vortex generator is substantially aligned with said local chord;

said apex height of said half-plow vortex generator has a magnitude defined in terms of said local chord;

said length of said half-plow vortex generator has a magnitude defined in terms of said local chord;

said width of said half-plow vortex generator has a magnitude defined in terms of said local chord.

2. The vortex generator system of claim 1 wherein said magnitude of said apex height is within the range of about 0.01 to about 0.08 of the magnitude of said local chord.

3. The vortex generator system of claim 2 wherein said magnitude of said apex height is about 0.04 of the magnitude of said local chord.

4. The vortex generator system of claim 1 wherein said magnitude of said length is within the range of about one-quarter to about one-half of the magnitude of said local chord.

5. The vortex generator system of claim 1 wherein said magnitude of said width is about one-third of said magnitude of said length of said half-plow vortex generator.

6. The vortex generator system of claim 1 wherein said apex angle has a value within the range of about twenty degrees to about thirty degrees.

7. The vortex generator system of claim 6 wherein said apex angle has a value of about twenty-three degrees.

8. The vortex generator system of claim 1 wherein said predetermined spanwise distance has a magnitude within the range of about one-half to about equal to the magnitude of the tip chord.

9. The vortex generator system of claim 1 wherein said predetermined chordal distance has a magnitude approximately equal to one-quarter of the magnitude of said local chord.

10. The vortex generator system of claim 1 wherein said aerodynamic surface is an upper aerodynamic surface and wherein said half-plow vortex generator is passively mounted in combination with said upper aerodynamic surface.

11. The vortex generator system of claim 1 wherein said aerodynamic surface is an upper aerodynamic surface and wherein said half-plow vortex generator is actively mounted in combination with said upper aerodynamic surface such that said half-plow vortex generator can be sequenced between a deployed state and a retracted state.

12. The vortex generator system of claim 1 wherein said half-plow vortex generator is defined as a first half-plow vortex generator, and wherein said vortex generator system further comprises a second half-plow vortex generator mounted in combination with the rotor blade, said second half-plow vortex generator having a length, a width, an apex angle, and an apex height, and wherein said length, said width, and said apex height of said second half-plow vortex generator are defined in terms of the magnitude of said local chord of said first half-plow vortex generator.

13. The vortex generator system of claim 12 wherein said aerodynamic surface is an upper aerodynamic surface and wherein said first and second half-plow vortex generators are mounted in combination with said upper aerodynamic surface.

14. The vortex generator system of claim 12 wherein said aerodynamic surface is an upper aerodynamic surface and wherein said first half-plow vortex generator is mounted in combination with said upper aerodynamic surface, and further wherein said second half-plow vortex generator is mounted in combination with said lower aerodynamic surface of the rotor blade in symmetrical relation to said first half-plow vortex generator.

15. The vortex generator system of claim 1 wherein said half-plow vortex generator is defined as a first half-plow vortex generator, and wherein said vortex generator system further comprises second and third half-plow vortex generators mounted in combination with the rotor blade, said second and third half-plow vortex generators each having a length, a width, an apex angle, and an apex height, and wherein said length, said width, and said apex height of said second and third half-plow vortex generators are defined in terms of the magnitude of said local chord of said first half-plow vortex generator, and wherein said first and second half-plow vortex generators are mounted in combination with said upper aerodynamic surface of the rotor blade and said third half-plow vortex generator is mounted in combination with said lower aerodynamic surface of the rotor blade in symmetrical relation to said first half-plow vortex generator.

16. The vortex generator system of claim 1 wherein said half-plow vortex generator is defined as a first half-plow vortex generator mounted in combination with said upper aerodynamic surface, and wherein said vortex generator system further comprises at least one and no more than two half-plow vortex generators mounted in combination with said upper aerodynamic surface of the rotor blade and at least one and no more than three half-plow vortex generators mounted in combination with said lower aerodynamic surface of the rotor blade, and wherein each of said half-plow vortex generators mounted in combination with said upper aerodynamic surface of the rotor blade and each of said half-plow vortex generators mounted in combination with said lower aerodynamic surface has a length, a width, an apex angle, and an apex height, and wherein said length, said width, and said apex height of said half-plow vortex generators are defined in terms of the magnitude of said local chord of said first half-plow vortex generator, and wherein each said half-plow vortex generator mounted in combination with said lower aerodynamic surface of the rotor blade is aligned in symmetrical relation with a corresponding one of said half-plow vortex generators mounted in combination on said upper aerodynamic surface of the rotor blade.

17. A half-plow vortex generator for use in mounted combination with a rotor blade defined by a tip chord, comprising:

a right triangular planform configuration being defined by a length, a width, and an apex angle; and

an apex height, which in combination with said length, said width, and said apex angle of said right triangular planform configuration, defines the three-dimensional configuration of said half-plow vortex generator; and

wherein

said half-plow vortex generator is mounted in combination with the upper aerodynamic surface of the rotor blade at a mounting site defined by a local chord, said mounting site being inboardly from the tip of the rotor blade a predetermined spanwise distance having a magnitude within the range of about one-half to about equal to the tip chord length, and wherein said half-plow vortex generator is further mounted inwardly from the leading edge of the rotor blade by a predetermined chordal distance having a magnitude of about one-quarter of the magnitude of said local chord; and

wherein

said length of said mounted half-plow vortex generator is substantially aligned with said local chord;

said apex height of said half-plow vortex generator has a magnitude within the range of about 0.01 to about 0.08 of the magnitude of said local chord;

said length of said half-plow vortex generator has a magnitude within the range of about one-quarter to about one-half of the magnitude of said local chord;

said width of said half-plow vortex generator has a magnitude of about one-third of said length; and

said apex angle has a value within the range of about twenty degrees to about thirty degrees.