IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
UP-0496676
(2006-07-31)
|
등록번호 |
US-7758303
(2010-08-09)
|
발명자
/ 주소 |
- Wadia, Aspi Rustom
- Turner, Alan Glen
- Dziech, Aaron Michael
- Szucs, Peter Nicholas
- Decker, John Jared
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
12 인용 특허 :
8 |
초록
▼
A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cro
A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.
대표청구항
▼
What is claimed: 1. A FLADE counter-rotating fan aircraft gas turbine engine comprising: axially spaced-apart forward and aft counter-rotatable fans circumferentially disposed about a centerline, at least one row of FLADE fan blades having radially outer airfoils disposed radially outwardly of and
What is claimed: 1. A FLADE counter-rotating fan aircraft gas turbine engine comprising: axially spaced-apart forward and aft counter-rotatable fans circumferentially disposed about a centerline, at least one row of FLADE fan blades having radially outer airfoils disposed radially outwardly of and drivingly connected to one of the forward and aft counter-rotatable fans having radially inner airfoils, an annular shroud disposed between the radially inner and outer airfoils, the radially inner and outer airfoils extending radially inwardly and outwardly respectively from the annular shroud, a core engine and in flow receiving relationship with and located downstream of the radially inner airfoils, and a bypass duct surrounding the core engine and in flow receiving relationship with and located downstream of the radially outer airfoils, inner and outer chords extending between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively, inner and outer stagger angles between the inner and outer chords respectively at the annular shroud and the centerline, and the inner and outer stagger angles being different. 2. An engine as claimed in claim 1 further comprising the radially outer airfoils outnumbering the radially inner airfoils. 3. An engine as claimed in claim 2 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 4. An engine as claimed in claim 2 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 5. An engine as claimed in claim 2 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 6. An engine as claimed in claim 2 further comprising radially extending linear load paths extend radially along radii from the centerline through the inner and outer airfoils and through the annular shroud between the inner and outer airfoils. 7. An engine An assembly as claimed in claim 6 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 8. An engine as claimed in claim 6 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 9. An engine as claimed in claim 6 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 10. An engine as claimed in claim 6 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, and a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges. 11. An engine as claimed in claim 6 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges, and a third portion of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 12. An engine as claimed in claim 6 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, and multiple portions of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 13. An engine as claimed in claim 2 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, at least a first circumferential row of radii extending radially outwardly from and normal to the centerline, and each radius of the radii intersecting one of the inner chords and one of the outer chords. 14. An engine as claimed in claim 13 further comprising: a second circumferential row of the radii extending radially outwardly from and normal to the centerline, the radii in the first circumferential row passing near or through the inner and outer leading edges, and the radii in the second circumferential row passing near or through the inner and outer trailing edges. 15. An engine as claimed in claim 14 further comprising a third circumferential row of the radii extending radially outwardly from and normal to the centerline and the radii in the third circumferential row passing between the inner and outer trailing edges along the inner and outer chords respectively. 16. A FLADE counter-rotating fan aircraft gas turbine engine comprising: axially spaced-apart forward and aft counter-rotatable fans circumferentially disposed about a centerline, at least one row of FLADE fan blades having radially outer airfoils disposed radially outwardly of and drivingly connected to one of the forward and aft counter-rotatable fans having radially inner airfoils, an annular shroud disposed between the radially inner and outer airfoils, the radially inner and outer airfoils extending radially inwardly and outwardly respectively from the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively, inner and outer stagger angles between the inner and outer chords respectively at the annular shroud and the centerline, the inner and outer stagger angles being different, and the radially outer airfoils outnumbering the radially inner airfoils. 17. An engine as claimed in claim 16 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 18. An engine as claimed in claim 16 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 19. An engine as claimed in claim 16 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 20. An engine as claimed in claim 16 further comprising radially extending linear load paths extend radially along radii from the centerline through the inner and outer airfoils and through the annular shroud between the inner and outer airfoils. 21. An engine as claimed in claim 20 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 22. An engine as claimed in claim 20 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 23. An engine as claimed in claim 20 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 24. An engine as claimed in claim 20 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, and a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges. 25. An engine as claimed in claim 20 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges, and a third portion of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 26. An engine as claimed in claim 20 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, and multiple portions of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 27. An engine as claimed in claim 16 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, at least a first circumferential row of radii extending radially outwardly from and normal to the centerline, and each radius of the radii intersecting one of the inner chords and one of the outer chords. 28. An engine as claimed in claim 27 further comprising: a second circumferential row of the radii extending radially outwardly from and normal to the centerline, the radii in the first circumferential row passing near or through the inner and outer leading edges, and the radii in the second circumferential row passing near or through the inner and outer trailing edges. 29. An engine as claimed in claim 28 further comprising a third circumferential row of the radii extending radially outwardly from and normal to the centerline and the radii in the third circumferential row passing between the inner and outer trailing edges along the inner and outer chords respectively. 30. A FLADE counter-rotating fan aircraft gas turbine engine comprising: axially spaced-apart forward and aft counter-rotatable fans circumferentially disposed about a centerline, at least one row of FLADE fan blades having radially outer airfoils disposed radially outwardly of and drivingly connected to the aft counter-rotatable fan having radially inner airfoils, an annular shroud disposed between the radially inner and outer airfoils, the radially inner and outer airfoils extending radially inwardly and outwardly respectively from the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively, inner and outer stagger angles between the inner and outer chords respectively at the annular shroud and the centerline, and the inner and outer stagger angles being different and the radially outer airfoils outnumbering the radially inner airfoils. 31. An engine as claimed in claim 30 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 32. An engine as claimed in claim 30 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 33. An engine as claimed in claim 30 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 34. An engine as claimed in claim 30 further comprising radially extending linear load paths extend radially along radii from the centerline through the inner and outer airfoils and through the annular shroud between the inner and outer airfoils. 35. An engine as claimed in claim 34 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 36. An engine as claimed in claim 34 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 37. An engine as claimed in claim 34 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 38. An engine as claimed in claim 34 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, and a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges. 39. An engine as claimed in claim 34 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges, and a third portion of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 40. An engine as claimed in claim 34 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, and multiple portions of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 41. An engine as claimed in claim 30 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, at least a first circumferential row of radii extending radially outwardly from and normal to the centerline, and each radius of the radii intersecting one of the inner chords and one of the outer chords. 42. An engine as claimed in claim 41 further comprising: a second circumferential row of the radii extending radially outwardly from and normal to the centerline, the radii in the first circumferential row passing near or through the inner and outer leading edges, and the radii in the second circumferential row passing near or through the inner and outer trailing edges. 43. An engine as claimed in claim 42 further comprising a third circumferential row of the radii extending radially outwardly from and normal to the centerline and the radii in the third circumferential row passing between the inner and outer trailing edges along the inner and outer chords respectively. 44. An aircraft gas turbine engine comprising: a FLADE fan circumferentially disposed about a centerline and having at least one row of FLADE fan blades disposed in a FLADE duct, the FLADE fan including radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline, inner and outer chords extending between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively, inner and outer stagger angles between the inner and outer chords respectively at the annular shroud and the centerline, and the inner and outer stagger angles being different, a core engine and in flow receiving relationship with and located downstream of the radially inner airfoils, and a bypass duct surrounding the core engine and in flow receiving relationship with and located downstream of the radially outer airfoils. 45. An engine as claimed in claim 44 further comprising the radially outer airfoils outnumbering the radially inner airfoils. 46. An engine as claimed in claim 45 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 47. An engine as claimed in claim 45 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 48. An engine as claimed in claim 45 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 49. An engine as claimed in claim 45 further comprising radially extending linear load paths extend radially along radii from the centerline through the inner and outer airfoils and through the annular shroud between the inner and outer airfoils. 50. An engine as claimed in claim 49 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio in a range of 1.5:1 to about 4:1. 51. An engine as claimed in claim 49 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 2:1. 52. An engine as claimed in claim 49 further comprising the radially outer airfoils outnumbering the radially inner airfoils by a ratio of 1.5:1. 53. An engine as claimed in claim 49 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, and a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges. 54. An engine as claimed in claim 49 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, a first portion of the radially extending linear load paths passing near or through the inner and outer leading edges, a second portion of the radially extending linear load paths passing near or through the inner and outer trailing edges, and a third portion of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 55. An engine as claimed in claim 49 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, and multiple portions of the radially extending linear load paths passing through inner and outer points between the inner and outer trailing edges along the inner and outer chords respectively. 56. An engine as claimed in claim 45 further comprising: inner and outer airfoil cross-sections of the inner and outer airfoils at the annular shroud, inner and outer chords extending between inner and outer leading and trailing edges of the inner and outer airfoil cross-sections respectively, at least a first circumferential row of radii extending radially outwardly from and normal to the centerline, and each radius of the radii intersecting one of the inner chords and one of the outer chords. 57. An engine as claimed in claim 56 further comprising: a second circumferential row of the radii extending radially outwardly from and normal to the centerline, the radii in the first circumferential row passing near or through the inner and outer leading edges, and the radii in the second circumferential row passing near or through the inner and outer trailing edges. 58. An engine as claimed in claim 57 further comprising a third circumferential row of the radii extending radially outwardly from and normal to the centerline and the radii in the third circumferential row passing between the inner and outer trailing edges along the inner and outer chords respectively. 59. An engine as claimed in claim 44 further comprising variable FLADE inlet guide vanes disposed axially forward and upstream of the outer airfoils.
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