IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0838379
(2007-08-14)
|
등록번호 |
US-8708643
(2014-04-29)
|
발명자
/ 주소 |
- Giffin, Rollin George
- Murrow, Kurt David
- Fakunle, Oladapo
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
30 |
초록
▼
A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-ro
A counter-rotatable fan turbine engine includes a counter-rotatable fan section, a worm gas generator, and a low pressure turbine to power the counter-rotatable fan section. The low pressure turbine maybe counter-rotatable or have a single direction of rotation in which case it powers the counter-rotatable fan section through a gearbox. The gas generator has inner and outer bodies having offset inner and outer axes extending through first, second, and third sections of a core assembly. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes and extending radially outwardly and inwardly respectively. The helical blades have first, second, and third twist slopes in the first, second, and third sections respectively. A combustor section extends through at least a portion of the second section.
대표청구항
▼
1. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a counter-rotatable low pressure turbine operably connected to the counter-rotatable fan section;an inlet transition duct between the counter-ro
1. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a counter-rotatable low pressure turbine operably connected to the counter-rotatable fan section;an inlet transition duct between the counter-rotatable fan section and the worm gas generator; andradially spaced apart approximately 90 degree outer and inner inlet bends in the inlet transition duct. 2. The engine as claimed in claim 1 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 3. The engine as claimed in claim 2 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 4. The engine as claimed in claim 3 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 5. The engine as claimed in claim 2 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 6. The engine as claimed in claim 5 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 7. The engine as claimed in claim 1 further comprising the counter-rotatable low pressure turbine including upstream and downstream low pressure turbines. 8. The engine as claimed in claim 7 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 9. The engine as claimed in claim 8 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 10. The engine as claimed in claim 9 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 11. The engine as claimed in claim 8 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 12. The engine as claimed in claim 11 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 13. The engine as claimed in claim 7 further comprising upstream and downstream low pressure turbines in the counter-rotatable low pressure turbine drivingly connected to counter-rotatable upstream and downstream fan stages in the counter-rotatable fan section. 14. The engine as claimed in claim 13 further comprising the downstream low pressure turbine drivingly connected to the upstream fan stage by a low pressure inner shaft and the upstream low pressure turbine drivingly connected to the downstream fan stage by a low pressure outer shaft. 15. The engine as claimed in claim 14 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 16. The engine as claimed in claim 15 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 17. The engine as claimed in claim 16 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 18. The engine as claimed in claim 15 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 19. The engine as claimed in claim 18 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 20. The engine as claimed in claim 7 further comprising: annular low pressure inner and outer drums in the counter-rotatable low pressure turbine drivingly connected to counter-rotatable upstream and downstream fan stages in the counter-rotatable fan section,a plurality of axially spaced apart rows of circumferentially spaced apart and radially outwardly extending turbine blades of the inner drum,a plurality of axially spaced apart rows of circumferentially spaced apart and radially inwardly extending turbine blades of the outer drum, andthe radially inwardly extending turbine blades being interdigitated with the radially outwardly extending turbine blades. 21. The engine as claimed in claim 20 further comprising the annular low pressure inner drum drivingly connected to the downstream fan stage by a low pressure outer shaft and the outer drum drivingly connected to the upstream fan stage by a low pressure inner shaft. 22. The engine as claimed in claim 20 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 23. The engine as claimed in claim 22 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 24. The engine as claimed in claim 23 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 25. The engine as claimed in claim 22 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 26. The engine as claimed in claim 25 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 27. The engine as claimed in claim 1 further comprising counter-rotatable upstream and downstream fan stages having upstream and downstream low inlet radius ratios respectively in a range of about 0.10-0.15. 28. The engine as claimed in claim 27 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 29. The engine as claimed in claim 28 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 30. The engine as claimed in claim 29 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 31. The engine as claimed in claim 28 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 32. The engine as claimed in claim 31 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 33. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a counter-rotatable low pressure turbine operably connected to the counter-rotatable fan section,an inlet transition duct between the counter-rotatable fan section and the worm gas generator, radially spaced apart outer and inner inlet bends in the inlet transition duct, andradially spaced apart annular outer and inner inlet turning vanes disposed within the outer and inner inlet bends respectively. 34. The engine as claimed in claim 33 further comprising: an outlet transition duct between the worm gas generator and the counter-rotatable low pressure turbine,radially spaced apart outer and inner outlet bends in the outlet transition duct, andradially spaced apart annular outer and inner outlet turning vanes disposed within the outer and inner outlet bends respectively. 35. The engine as claimed in claim 34 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 36. The engine as claimed in claim 35 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 37. The engine as claimed in claim 36 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 38. The engine as claimed in claim 35 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 39. The engine as claimed in claim 38 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 40. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a counter-rotatable low pressure turbine operably connected to the counter-rotatable fan section,counter-rotatable upstream and downstream fan stages having upstream and downstream low inlet radius ratios respectively in a range of about 0.10-0.15,an inlet transition duct between the counter-rotatable fan section and the worm gas generator,radially spaced apart outer and inner inlet bends in the inlet transition duct,radially spaced apart annular outer and inner inlet turning vanes disposed within the outer and inner inlet bends respectively,an outlet transition duct between the worm gas generator and the counter-rotatable low pressure turbine,radially spaced apart outer and inner outlet bends in the outlet transition duct, andradially spaced apart annular outer and inner outlet turning vanes disposed within the outer and inner outlet bends respectively. 41. The engine as claimed in claim 40 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 42. The engine as claimed in claim 41 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 43. The engine as claimed in claim 42 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 44. The engine as claimed in claim 41 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 45. The engine as claimed in claim 44 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 46. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a low pressure turbine operably connected to the counter-rotatable fan section;an inlet transition duct between the counter-rotatable fan section and the worm gas generator; andradially spaced apart approximately 90 degree outer and inner inlet bends in the inlet transition duct. 47. The engine as claimed in claim 46 further comprising the low pressure turbine being a single direction of rotation turbine drivingly connected to the counter-rotatable fan section by a single low pressure shaft through a drive gearbox. 48. The engine as claimed in claim 47 further comprising: the gas generator including an inlet axially spaced apart and upstream from an outlet,a core assembly including an inner body disposed within an outer body and the inner and outer bodies extending from the inlet to the outlet,the inner and outer bodies having offset inner and outer axes respectively,at least one of the inner and outer bodies being rotatable about a corresponding one of the inner and outer axes,the inner and outer bodies having intermeshed inner and outer helical blades wound about the inner and outer axes respectively,the inner and outer helical blades extending radially outwardly and inwardly respectively,the core assembly having first, second, and third sections in serial downstream flow relationship extending between the inlet and the outlet,the inner and outer helical blades having first, second, and third twist slopes in the first, second, and third sections respectively,the first twist slopes being less than the second twist slopes and the third twist slopes being less than the second twist slopes, anda combustor section extending axially downstream through at least a portion of the second section. 49. The engine as claimed in claim 48 further comprising the outer body being rotatable about the outer axis and the inner body and being rotatable about the inner axis. 50. The engine as claimed in claim 49 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 51. The engine as claimed in claim 48 further comprising the outer body being rotatably fixed about the outer axis and the inner body being orbital about the outer axis. 52. The engine as claimed in claim 51 further comprising the inner and outer bodies being geared together in a fixed gear ratio. 53. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section, a worm gas generator, and a low pressure turbine operably connected to the counter-rotatable fan section,an inlet transition duct between the counter-rotatable fan section and the worm gas generator,radially spaced apart outer and inner inlet bends in the inlet transition duct, andradially spaced apart annular outer and inner inlet turning vanes disposed within the outer and inner inlet bends respectively. 54. The engine as claimed in claim 53 further comprising: an outlet transition duct between the worm gas generator and the low pressure turbine,radially spaced apart outer and inner outlet bends in the outlet transition duct, andradially spaced apart annular outer and inner outlet turning vanes disposed within the outer and inner outlet bends respectively. 55. A counter-rotatable fan gas turbine engine comprising: in downstream serial flow relationship a counter-rotatable fan section having counter-rotatable upstream and downstream fan stages, a worm gas generator, and a low pressure turbine operably connected to the counter-rotatable fan section;an inlet transition duct between the counter-rotatable fan section and the worm gas generator;radially spaced apart approximately 90 degree outer and inner inlet bends in the inlet transition duct;the counter-rotatable upstream fan stage having a low inlet radius ratio in a range of about 0.10-0.15;the fan inlet radius ratio being defined as an inlet hub radius divided by an inlet fan blade tip radius; andthe inlet hub radius and inlet fan blade tip radius being measured with respect to an engine centerline of the engine. 56. The engine as claimed in claim 55 further comprising the low pressure turbine being a single direction of rotation turbine drivingly connected to the counter-rotatable fan section by a single low pressure shaft through a drive gearbox. 57. The engine as claimed in claim 55 further comprising the low pressure turbine being a counter-rotatable low pressure turbine. 58. The engine as claimed in claim 57 further comprising upstream and downstream low pressure turbines in the counter-rotatable low pressure turbine drivingly connected to the counter-rotatable upstream and downstream fan stages in the counter-rotatable fan section. 59. The engine as claimed in claim 57 further comprising: annular low pressure inner and outer drums in the counter-rotatable low pressure turbine drivingly connected to counter-rotatable upstream and downstream fan stages in the counter-rotatable fan section,a plurality of axially spaced apart rows of circumferentially spaced apart and radially outwardly extending turbine blades of the inner drum,a plurality of axially spaced apart rows of circumferentially spaced apart and radially inwardly extending turbine blades of the outer drum, andthe radially inwardly extending turbine blades being interdigitated with the radially outwardly extending turbine blades. 60. The engine as claimed in claim 59 further comprising the annular low pressure inner drum drivingly connected to the downstream fan stage by a low pressure outer shaft and the outer drum drivingly connected to the upstream fan stage by a low pressure inner shaft.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.