Premixed combustion burner for gas turbine
View Patent ↗A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has a fuel nozzle, a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle, and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle. The swirler vanes gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vanes.
1. A premixed combustion burner for a gas turbine comprising:
a fuel nozzle;
a burner cylinder arranged so as to surround said fuel nozzle and form an air passageway between itself and said fuel nozzle; and
a plurality of swirler vanes arranged along an axial direction of said fuel nozzle in a plurality of positions around a circumferential direction of an outer circumference surface of said fuel nozzle and that gradually curve from an upstream side to a downstream side to spin air traveling within the air passageway from the upstream side to the downstream side,
wherein each of said swirler vanes has a forward section located at the upstream side that is connected to said fuel nozzle and a rear section located at the downstream side that has a cutaway section provided at a rear edge section on an inner circumference side,
wherein said cutaway section provides a gap between the rear edge section of each of said swirler vanes and the outer circumference surface of said fuel nozzle.
2. A premixed combustion burner for a gas turbine according to claim 1 , wherein a height of each of said cutaway sections is set to 3% to 20% of a maximum vane height of said swirler vanes.
3. A premixed combustion burner for a gas turbine according to claim 2 , wherein each of said swirler vanes has a plurality of injection holes for fuel injection provided in a vane back side surface and/or a vane front side surface, and, for each of said swirler vanes, a diameter of an injection hole of said injection holes positioned at a radial direction outer side is greater than a diameter of another injection hole of said injection holes positioned at a radial direction inner side.
4. A premixed combustion burner for a gas turbine according to claim 3 , wherein, for each of said swirler vanes, said other injection hole positioned at the radial direction inner side is provided at a position proximal to said cutaway section and enables fuel injected from said other injection hole to flow along the vane back side surface and/or the vane front side surface of said respective swirler vane to a rear edge of said respective swirler vane.
5. A premixed combustion burner for a gas turbine according to claim 4 , wherein, for each of said swirler vanes, said injection holes are provided in positions that are displaced from one another in a vane height direction and/or a vane length direction of said respective swirler vane.
6. A premixed combustion burner for a gas turbine according to claim 3 , wherein, for each of said swirler vanes, said injection holes are provided in positions that are displaced from one another in a vane height direction and/or a vane length direction of said respective swirler vane.
7. A premixed combustion burner for a gas turbine according to claim 2 , wherein each of said swirler vanes has a chamfer section provided on a rear edge section tip side and/or on a root side.
8. A premixed combustion burner for a gas turbine according to claim 2 , further comprising a ring member provided on a radial direction inner side of said cutaway sections of said swirler vanes.
9. A premixed combustion burner for a gas turbine according to claim 2 , wherein outer circumference side end surfaces of said swirler vanes and an inner surface of said burner cylinder have a clearance provided therebetween.
10. A combustor of a gas turbine comprising a premixed combustion burner for a gas turbine according to claim 2 .
11. A gas turbine comprising a combustor of a gas turbine according to claim 10 .
12. A premixed combustion burner for a gas turbine according to claim 1 , wherein each of said swirler vanes has a plurality of injection holes for fuel injection provided in a vane back side surface and/or a vane front side surface, and, for each of said swirler vanes, a diameter of an injection hole of said injection holes positioned at a radial direction outer side is greater than a diameter of another injection hole of said injection holes positioned at a radial direction inner side.
13. A premixed combustion burner for a gas turbine according to claim 12 , wherein, for each of said swirler vanes, said other injection hole positioned at the radial direction inner side is provided at a position proximal to said cutaway section and enables fuel injected from said other injection hole to flow along the vane back side surface and/or the vane front side surface of said respective swirler vane to a rear edge of said respective swirler vane.
14. A premixed combustion burner for a gas turbine according to claim 13 , wherein, for each of said swirler vanes, said injection holes are provided in positions that are displaced from one another in a vane height direction and/or a vane length direction of said respective swirler vane.
15. A premixed combustion burner for a gas turbine according to claim 12 , wherein, for each of said swirler vanes, said injection holes are provided in positions that are displaced from one another in a vane height direction and/or a vane length direction of said respective swirler vane.
16. A premixed combustion burner for a gas turbine according to claim 1 , wherein each of said swirler vanes has a chamfer section provided on a rear edge section tip side and/or on a root side.
17. A premixed combustion burner for a gas turbine according to claim 1 , further comprising a ring member provided on a radial direction inner side of said cutaway sections of said swirler vanes.
18. A premixed combustion burner for a gas turbine according to claim 1 , wherein outer circumference side end surfaces of said swirler vanes and an inner surface of said burner cylinder have a clearance provided therebetween.
19. A combustor of a gas turbine comprising a premixed combustion burner for a gas turbine according to claim 1 .
20. A gas turbine comprising a combustor of a gas turbine according to claim 19 .