IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0632421
(2005-07-15)
|
등록번호 |
US-8286908
(2012-10-16)
|
국제출원번호 |
PCT/US2005/025283
(2005-07-15)
|
§371/§102 date |
20080623
(20080623)
|
국제공개번호 |
WO2006/110156
(2006-10-19)
|
발명자
/ 주소 |
- Kebrle, John M.
- Andrews, III, James R.
- Daw, Justin
- Hurdle, Jim
- Sherrill, Paul
- Narramore, Jimmy C.
- Xue, Sidney
- Hollimon, Charles
- Smith, Dudley
- Docker, Bryce
- Brieger, John T.
|
출원인 / 주소 |
- Bell Helicopter Textron Inc.
|
대리인 / 주소 |
Pillsbury Winthrop Shaw Pittman LLP
|
인용정보 |
피인용 횟수 :
9 인용 특허 :
11 |
초록
▼
A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a
A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.
대표청구항
▼
1. A ducted fan for a helicopter, comprising: a transverse duct; anda counter-torque device supported within said duct, said counter-torque device including a rotor rotatably mounted within said duct and a stator fixedly mounted within said duct downstream from said rotor,said rotor including: a rot
1. A ducted fan for a helicopter, comprising: a transverse duct; anda counter-torque device supported within said duct, said counter-torque device including a rotor rotatably mounted within said duct and a stator fixedly mounted within said duct downstream from said rotor,said rotor including: a rotor hub having a rotor axis, androtor blades extending from said hub, said rotor blades having a modulated angular distribution about said rotor axis, said angular distribution being defined by the equation: θi′=θi+Δθi sin(mθi)where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi is the maximum modulation amplitude for a specific blade of said rotor blades, m is the modulation factor, and Δθi is not a constant for said rotor as a whole, and wherein the resulting rotor is substantially balanced, andsaid stator including: a stator hub, anda plurality of stator vanes distributed around said stator hub,wherein said stator vanes are angularly modulated around said hub such that the angular spacing between adjacent vanes of said stator vanes varies around said stator hub for each pair of said adjacent vanes. 2. The ducted fan according to claim 1, further comprising an annular support disk, said stator vanes being mounted between said stator hub and said support disk. 3. The ducted fan according to claim 1, wherein each of said stator vanes are configured to be in tension. 4. The ducted fan according to claim 1, wherein said stator vanes are non-radial with respect to a center point of said stator hub. 5. The ducted fan according to claim 1, wherein each of said stator vanes are modulated in a first direction such that said vanes are slanted in said first direction, which is transverse to a central axis of said hub. 6. The ducted fan according to claim 1, wherein one of said stator vanes is modulated in a first direction such that said one of said stator vanes is slanted transverse to a central axis of said hub and the remaining ones of said stator vanes are modulated in a second direction that is opposite to said first direction. 7. The ducted fan according to claim 1, wherein said rotor blades are equal in number to said stator vanes. 8. The ducted fan according to claim 1, wherein each of said rotor blades intersects a respective stator vane as viewed along the longitudinal axis of said duct at an intersection point, each of said intersection points for each of said respective rotor blades and stator vanes having a different radial length from a center of said stator hub. 9. The ducted fan according to claim 8, wherein said intersection points cooperate to form a helix. 10. The ducted fan according to claim 1, wherein said modulation of said stator vanes is configured and arranged relative to the distribution of said rotor blades such that each of said rotor blades intersects a respective stator vane, as viewed along the longitudinal axis of said duct, at a different radial distance from a center point of said hub. 11. The ducted fan according to claim 1, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I=9. 12. The ducted fan according to claim 11, wherein said modulation factor m=1. 13. The ducted fan according to claim 11, wherein said modulation factor m=2. 14. The ducted fan according to claim 1, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I is a prime number. 15. The ducted fan according to claim 1, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I equals 7 or 11. 16. The ducted fan according to claim 1, wherein said modulation factor m=1. 17. The ducted fan according to claim 1, wherein said modulation factor m=2. 18. The ducted fan according to claim 1, wherein a first angle defining the angular spacing between two stator vanes equals a second angle defining the angular spacing between two rotor blades. 19. The ducted fan according to claim 18, wherein none of said stator vanes is positioned between said two stator vanes and none of said rotor blades is positioned between said two rotor blades. 20. A ducted fan for a helicopter, comprising: a transverse duct; anda counter-torque device supported within said duct, said counter-torque device including a rotor rotatably mounted within said duct and a stator fixedly mounted within said duct downstream from said rotor,said rotor including: a rotor hub having a rotor axis, androtor blades extending from said hub, said rotor blades having a modulated angular distribution about said rotor axis, said angular distribution being defined by the equation: θi′=θi+Δθi sin(mθi)where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi is the maximum modulation amplitude for a specific blade of said rotor blades and is equal to Δφ/I where Δφ is phase-modulation amplitude and I is the number of blades, and m is the modulation factor that is not equal to a prime of the number of blades, andsaid stator including: a stator hub, anda plurality of stator vanes distributed around said stator hub,wherein said stator vanes are angularly modulated around said stator hub such that the angular spacing between adjacent vanes of said stator vanes varies around said stator hub for each pair of said adjacent vanes. 21. A rotor according to claim 20, wherein said number of blades on said rotor is nine. 22. A rotor according to claim 21, wherein said modulation factor m=1. 23. A rotor according to claim 21, wherein said modulation factor m=2. 24. A rotor according to claim 20, wherein said number of blades on said rotor equals 7 or 11. 25. A rotor according to claim 20, wherein said modulation factor m=1. 26. A rotor according to claim 20, wherein said modulation factor m=2. 27. The ducted fan according to claim 20, further comprising an annular support disk, said stator vanes being mounted between said stator hub and said support disk. 28. The ducted fan according to claim 20, wherein each of said stator vanes are configured to be in tension. 29. The ducted fan according to claim 20, wherein said stator vanes are non-radial with respect to a center point of said stator hub. 30. The ducted fan according to claim 20, wherein each of said stator vanes are modulated in a first direction such that said vanes are slanted in said first direction, which is transverse to a central axis of said hub. 31. The ducted fan according to claim 20, wherein one of said stator vanes is modulated in a first direction such that said one of said stator vanes is slanted in said first direction and the remaining ones of said stator vanes are modulated in a second direction that is opposite to said first direction. 32. The ducted fan according to claim 20, wherein said rotor blades are equal in number to said stator vanes. 33. The ducted fan according to claim 20, wherein each of said rotor blades intersects a respective stator vane as viewed along the longitudinal axis of said duct at an intersection point, each of said intersection points for each of said respective rotor blades and stator vanes having a different radial length from a center of said stator hub. 34. The ducted fan according to claim 33, wherein said intersection points cooperate to form a helix. 35. The ducted fan according to claim 20, wherein said modulation of said stator vanes is configured and arranged relative to the distribution of said rotor blades such that each of said rotor blades intersects a respective stator vane, as viewed along the longitudinal axis of said duct, at a different radial distance from a center point of said hub. 36. The ducted fan according to claim 20, wherein a first angle defining the angular spacing between two stator vanes equals a second angle defining the angular spacing between two rotor blades. 37. The ducted fan according to claim 36, wherein none of said stator vanes is positioned between said two stator vanes and none of said rotor blades is positioned between said two rotor blades. 38. A rotor for a counter-torque device for a helicopter, comprising: a hub having a rotor axis; andblades extending from said hub, said blades having a modulated angular distribution about said rotor axis, said angular distribution being defined by the equation: θi′=θi+Δθi sin(mθi)where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi is the maximum modulation amplitude for a specific blade of said blades, m is the modulation factor, and Δθi is not a constant for said rotor as a whole, and wherein the resulting rotor is substantially balanced. 39. A rotor according to claim 38, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I=9. 40. A rotor according to claim 39, wherein said modulation factor m=1. 41. A rotor according to claim 39, wherein said modulation factor m=2. 42. A rotor according to claim 38, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I is a prime number. 43. A rotor according to claim 42, wherein said modulation factor m=2. 44. A rotor according to claim 38, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I equals 7 or 11. 45. A rotor according to claim 38, wherein said modulation factor m=1. 46. A rotor according to claim 38, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I equals any number of blades in which modulation factor m is not a prime of I. 47. A counter-torque device for a helicopter, comprising: a duct with a longitudinal axis; anda rotor secured within said duct for rotation within said duct about said longitudinal axis of said duct, said rotor having: a hub having a rotor axis; andblades extending from said hub, said blades having a modulated angular distribution about said rotor axis, said angular distribution being defined by the equation: θi′=θi+Δθi sin(mθi)where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi′ is the maximum modulation amplitude for a specific blade of said blades, m is the modulation factor, and Δθi is not a constant for said rotor as a whole, and wherein the resulting rotor is substantially balanced. 48. A counter-torque device according to claim 47, further comprising a stator coupled to said duct and positioned within said duct, said stator having a plurality of vanes. 49. A counter-torque device according to claim 47, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I=9, and said modulation factor m=1. 50. A counter-torque device according to claim 47, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I=9, and said modulation factor m=2. 51. A rotor according to claim 47, wherein Δθi=Δφ/I, wherein I is the number of blades on said rotor, and I equals any number of blades in which modulation factor m is not a prime of I. 52. A rotor for a counter-torque device for a helicopter, comprising: a hub having a rotor axis; andblades extending from said hub, said blades having an modulated angular distribution about said rotor axis, said angular distribution being defined by the equation: θi′=θi+Δθi sin(mθi),where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi is the maximum modulation amplitude and is equal to Δφ/I where Δφ is phase-modulation amplitude for a given blade of said blades, and I is the number of blades, and m is the modulation factor that is not equal to a prime of the number of blades. 53. A rotor according to claim 52, wherein said number of blades on said rotor is nine. 54. A rotor according to claim 53, wherein said modulation factor m=1. 55. A rotor according to claim 53, wherein said modulation factor m=2. 56. A rotor according to claim 52, wherein said number of blades on said rotor equals 7 or 11. 57. A rotor according to claim 52, wherein said modulation factor m=1. 58. A rotor according to claim 52, wherein said modulation factor m=2. 59. A method for determining a substantially balanced, modulated angular spacing between blades of a tail rotor for a helicopter, comprising: selecting a modulation factor m;selecting a number of blades for attachment to a rotor;determining the modulated angular spacing between each of the rotors using a modified sinusoidal law wherein θi′=θi+Δθi sin(mθi),where θi′ is the modulated blade angle for the ith blade; θi is the nominal blade angle for the ith blade; Δθi is the maximum modulation amplitude for a given blade of the blades, m is the modulation factor, and Δθi is not a constant for the rotor as a whole. 60. A method according to claim 59, wherein the selecting of a modulation factor and the selecting a number of blades include selecting a modulation factor that is prime to the number of blades. 61. A method according to claim 59, wherein the selecting of a modulation factor and the selecting a number of blades include selecting a modulation factor of m=1 and the number of blades being 9. 62. A method according to claim 59, wherein the selecting of a modulation factor and the selecting a number of blades include selecting a modulation factor of m=2 and the number of blades being 9.
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