Turbine containing system and an injector therefor
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/22
F02C-007/26
출원번호
US-0326580
(2002-12-20)
발명자
/ 주소
Haynes, Joel Meier
출원인 / 주소
General Electric Company
인용정보
피인용 횟수 :
65인용 특허 :
34
초록▼
A turbine containing system is disclosed. The system includes an intake section, a compressor section downstream from the intake section, a combustor section having a primary combustion system downstream from the intake section, a secondary combustion system downstream from the primary combustion sy
A turbine containing system is disclosed. The system includes an intake section, a compressor section downstream from the intake section, a combustor section having a primary combustion system downstream from the intake section, a secondary combustion system downstream from the primary combustion system, a turbine section, an exhaust section and a load. The secondary combustion system includes an injector for transversely injecting a secondary fuel into a stream of combustion products of the primary combustion system. The injector including a coupling, a wall defining an airfoil shape circumscribing a fuel mixture passage, and at least one exit for communication between said fuel mixture passage and said stream of primary combustion products.
대표청구항▼
1. A turbine containing system comprising:(a) an intake section; (b) a compressor section downstream from the intake section; (c) a combustor section having a primary combustion system downstream from the intake section; (d) a secondary combustion system downstream from the primary combustion system
1. A turbine containing system comprising:(a) an intake section; (b) a compressor section downstream from the intake section; (c) a combustor section having a primary combustion system downstream from the intake section; (d) a secondary combustion system downstream from the primary combustion system, said secondary combustion system including an injector for transversely injecting a secondary fuel mixture into a stream of combustion products of the primary combustion system, said injector including: (i) a coupling, (ii) a wall circumscribing a fuel mixture passage, wherein an area defined by the wall decreases as a distance from the coupling increases, and (iii) at least one exit for communicating between said fuel mixture passage and said stream of primary combustion products; (e) a turbine section; and (f) an exhaust section. 2. The turbine containing system according to claim 1, further including a load.3. The turbine containing system according to claim 2, wherein the load is an electrical generator.4. The turbine containing system according to claim 2, wherein the load is any one of a compressor and a propeller.5. The turbine containing system according to claim 1, wherein the secondary combustor section is provided to any one of a can of the combustor section, a transition piece of the combustor section, a turbine inlet section and an interface between a can and a transition piece of the combustor scion.6. The turbine containing system according to claim 5, wherein the secondary combustion system is provided substantially to the entrance of the transition piece.7. The turbine containing system according to claim 1, wherein the injector is provided as a first stage airfoil of the turbine section.8. The turbine containing system according to claim 1, wherein the secondary combustion system includes a plurality of injectors.9. The turbine containing system according to claim 8, wherein the plurality of injectors are spatially distributed in the stream of combustion products of the primary combustion system.10. The turbine containing system according to claim 9, wherein the plurality of injectors include a combination of long injectors and short injectors.11. The turbine containing system according to claim 10, wherein the long and short injectors are alternating.12. An injector for use in a turbine containing system including an intake section, a compressor section downstream from the intake section, a combustor section having a primary combustion system, a secondary combustion system downstream from the primary combustion system for further combusting a stream of primary combustion products, a turbine section, and an exhaust section, said injector including:(a) a coupling; (b) a wall defining an airfoil shape circumscribing a fuel mixture passage, wherein an area defined by the wall decreases as a distance from the coupling increases; and (c) at least one exit for communication between said fuel mixture passage and said stream of primary combustion products. 13. The injector according to claim 12, further including a fuel circulation prevention means.14. The injector according to claim 12, further including an inner wall for defining a coolant passage.15. The injector according to claim 14, further including a mixer-containing element between said wall and said inner wall.16. The injector according to claim 15, wherein said mixer-containing element between the wall and inner wall defines a second coolant passage.17. The injector according to claim 16, further including a communications passage in the mixer-containing element between said coolant passage and said second coolant passage.18. The injector according to claim 15, further including mixing passages for communicating a coolant to said exit.19. The injector according to claim 18, wherein an axis of the mixing passage is substantially perpendicular to an axis of the exit.20. The injector according to claim 19, wherein a diameter of the exit is greater than the diameter of the mixing passage.21. The injector according to claim 19, wherein a diameter of the mixing passage providing the coolant is greater than a diameter of an entrance providing fuel to the exit.22. The injector according to claim 19, wherein a length of the exit is between about 1-10 diameters of an entrance providing fuel to the exit.23. The injector according to claim 22, wherein the length is between about 3-7 diameters of the entrance providing fuel to the exit.24. The injector according to claim 23, wherein the exit is about 5 diameters of the entrance providing fuel to the exit.25. The injector according to claim 14, wherein the coolant passage is adjacent to the wall.26. The injector according to claim 14, further including holes for creating a cooling film on an outer surface of said injector.27. The injector according to claim 12, when the wall tapers.28. The injector according to claim 12, further including an area-decreasing member.29. The injector according to claim 12, wherein there is a plurality of exits for communication between the fuel mixture passage and the stream of the primary combustion products.30. The injector according to claim 29, wherein the plurality of exits are configured so as to provide a fuel mass proportional to the oxidants in a region of the injector location.31. The injector according to claim 30, wherein the plurality of exits set at a pre-selected exit spacing.32. The injector according to claim 30, wherein the plurality of exits are set at a pre-selected distribution of exit diameters.33. The injector according to claim 30, wherein the plurality of exits are set at a pre-selected exit spacing and a pre-selected exit diameter distribution.34. The injector according to claim 12, further including a turning angle.35. The injector according to claim 12, wherein an inscribed circle diameter of a leading edge and a length from the leading edge to a trailing edge has an aspect ratio (d/l) between about 1 and 12.36. The injector according to claim 35, wherein the aspect ratio (d/l) is between about 1 and 2.37. The injector according to claim 36, wherein the aspect ratio (d/l) is about 1.4.38. A turbine containing system comprising:(a) an intake section; (b) a compressor section downstream from the intake section; (c) a combustor section having a primary combustion system downstream from the intake section; (d) a secondary combustion system downstream from the primary combustion system, said secondary combustion system including an injector for transversely injecting a secondary fuel into a stream of combustion products of the primary combustion system, the injector including; (i) a coupling, (ii) a wall defining an airfoil shape circumscribing a fuel mixture passage, wherein an area defined by the wall decreases as a distance from the coupling increases, and (iii) an exit for communicating between said fuel mixture passage and said stream of primary combustion products; (e) a turbine section; (f) an exhaust section; and (g) a load. 39. The turbine containing system according to claim 38, wherein the load is an electrical generator.40. The turbine containing system according to claim 38, wherein the load is any one of a compressor and a propeller.41. The turbine containing system according to claim 38, wherein the secondary combustor section is provided to any one of a can of the combustor section, a transition piece of the combustor section, a turbine inlet section and an interface between a can and a transition piece of the combustor section.42. The turbine containing system according to claim 41, wherein the secondary combustion system is provided substantially to the entrance of the transition piece.43. The turbine containing system according to claim 38, wherein the injector is provided as a first stage airfoil of the turbine section.44. The turbine containing system according to claim 38, wherein the secondary combustion system includes a plurality of injectors.45. The turbine containing system according to claim 44, wherein the plurality of injectors are spatially distributed in the stream of combustion products of the primary combustion system.46. The turbine containing system according to claim 45, wherein the plurality of injectors include a combination of long injectors and short injectors.47. The turbine containing system according to claim 46, wherein the long and short injectors are alternating.48. The injector according to claim 38, further including a fuel circulation prevention means.49. The injector according to claim 38, further including an inner wall for defining a coolant passage.50. The injector according to claim 49, further including a mixer-containing element between said wall and said inner wall.51. The injector according to claim 50, wherein said mixer-containing element between the wall and inner wall defines a second coolant passage.52. The injector according to claim 51, further including a communications passage in the mixer-containing element between said coolant passage and said second coolant passage.53. The injector according to claim 50, further including mixing passages for communicating a coolant to said exit.54. The injector according to claim 53, wherein an axis of the mixing passage is substantially perpendicular to an axis of the exit.55. The injector according to claim 54, wherein a diameter of the exit is greater than the diameter of the mixing passage.56. The injector according to claim 54, wherein a diameter of the mixing passage providing the coolant is greater than a diameter of an entrance providing fuel to the exit.57. The injector according to claim 54, wherein a length of the exit is between about 1-10 diameters of an entrance providing fuel to the exit.58. The injector according to claim 57, wherein the length is between about 3-7 diameters of the entrance providing fuel to the exit.59. The injector according to claim 58, wherein the exit is about 5 diameters of the entrance providing fuel to the exit.60. The injector according to claim 59, wherein the coolant passage is adjacent to the wall.61. The injector according to claim 59, further including holes for creating a cooling film on an outer surface of said injector.62. The injector according to claim 38, wherein the wall tapers.63. The injector according to claim 38, further including an area-decreasing member.64. The injector according to claim 38, wherein there is a plurality of exits for communication between the fuel mixture passage and the stream of the primary combustion products.65. The injector according to claim 64, wherein the plurality of exits are configured so as to provide a fuel mass proportional to the oxidants in a region of the injector location.66. The injector according to claim 65, wherein the plurality of exits are set at a pre-selected exit spacing.67. The injector according to claim 65, wherein the plurality of exits are set at a pre-selected distribution of exit diameters.68. The injector according to claim 65, wherein the plurality of exits are set at a pre-selected exit spacing and a pre-selected exit diameter distribution.69. The injector according to claim 38, further including a turning angle.70. The injector according to claim 38, wherein an inscribed circle diameter of a leading edge and a length from the leading edge to a trailing edge has an aspect ratio (d/l) between about 1 and 12.71. The injector according to claim 70, wherein the aspect ratio (d/l) is between about 1 and 2.72. The injector according to claim 71, wherein the aspect ratio (d/l) is about 1.4.73. A method for reducing NOx emissions of turbine containing system, the method comprising:(a) providing a turbine containing system comprising (i) an intake section, (ii) a compressor section downstream from the intake section, (iii) a combustor section having a primary combustion system downstream from the intake section, (iv) a turbine section, and (v) an exhaust section; and (b) providing a secondary combustion system downstream from the primary combustion system, said secondary combustion system including an injector for transversely injecting a secondary fuel mixture into a stream of combustion products of the primary combustion system, said injector including: (i) a coupling, (ii) a wall circumscribing a fuel mixture passage wherein an area defined by the wall decreases as a distance from the coupling increases, and (iii) at least one exit for communicating between said fuel mixture passage and said stream of primary combustion products. 74. A method for reducing NOx emissions of turbine containing system, the method comprising:(a) providing a turbine containing system comprising (i) an intake section, (ii) a compressor section downstream from the intake section, (iii) a combustor section having a primary combustion system downstream from the intake section, (iv) a turbine section, and (v) an exhaust section; and (b) providing a secondary combustion system downstream from the primary combustion system, said secondary combustion system including an injector for transversely injecting a secondary fuel mixture into a stream of combustion products of the primary combustion system, and injector including: (i) a coupling, (ii) a wall defining an airfoil shape circumscribing a fuel mixture passage, wherein an area defined by the wall decreases as a distance from the coupling increases, and (iii) at least one exit for communicating between said fuel mixture passage and said stream of primary combustion products. 75. A method for reducing NOx emissions of turbine containing system, the method comprising:(a) providing a turbine containing system comprising (i) an intake section, (ii) a compressor section downstream from the intake section, (iii) a combustor section having a primary combustion system downstream from the intake section, (iv) a turbine section, (v) an exhaust section, and (vi) a load; and (b) providing a secondary combustion system downstream form the primary combustion system, said secondary combustion system including an injector for transversely injecting a secondary fuel mixture into a stream of combustion products of the primary combustion system, said injector including: (i) a coupling, (ii) a wall defining an airfoil shape circumscribing a fuel mixture passage, wherein an area defined by the wall decreases as a distance from the coupling increases, and (iii) at least one exit for communicating between said fuel mixture passage and said stream of primary combustion products.
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