Premixed combustion burner of gas turbine technical field
View Patent ↗A fuel nozzle 110 having a plurality of swirl vane 130 on an outer peripheral surface thereof is installed within a burner tube 120 , with a clearance 121 being provided. Each swirl vane 130 progressively curves from an upstream side toward a downstream side (inclines along a circumferential direction) in order to swirl compressed air A flowing through an air passage 111 to form a swirl air flow a. Here, curvature of each swirl vane 130 is greater on its outer peripheral side than on its inner peripheral side. By suppressing occurrence of an air streamline heading from the inner peripheral side toward the outer peripheral side, therefore, flow velocity on the inner peripheral side and flow velocity on the outer peripheral side become equal, thus preventing flashback on the inner peripheral side.
1. A premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and the angle is larger on an outer peripheral side of the rear edge of the swirl vane than the angle on the inner peripheral side of the rear edge of the swirl vane, and
a clearance is provided between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube,
wherein in order to render said clearance between said outer peripheral side end surface of the swirl vane and said inner peripheral surface of the burner tube constant, a clearance setting rib, which makes intimate contact with the inner peripheral surface of the burner tube, is provided at a portion of the outer peripheral side end surface of the swirl vane.
2. A premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, characterized in that
an angle formed by a tangent to an average camber line of the swirl vane at a rear edge of the swirl vane and an axis line extending along the axial direction of the fuel nozzle is 0 to 10 degrees on an inner peripheral side of the rear edge of the swirl vane, and is 25 to 35 degrees on an outer peripheral side of the rear edge of the swirl vane, and
a clearance is provided between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube,
wherein in order to render said clearance between said outer peripheral side end surface of the swirl vane and said inner peripheral surface of the burner tube constant, a clearance setting rib, which makes intimate contact with the inner peripheral surface of the burner tube, is provided at a portion of the outer peripheral side end surface of the swirl vane.
3. The premixed combustion burner of a gas turbine according to claim 1 or 2 , characterized in that
an aspect ratio between a vane chord length and the vane height of the swirl vane (vane height/vane chord length) is set at 0.2 to 0.75.
4. The premixed combustion burner of a gas turbine according to claim 1 or 2 , characterized in that
a vane thickness of the swirl vane is a length which is 0.1 to 0.3 times a vane chord length of the swirl vane.
5. The premixed combustion burner of a gas turbine according to claim 1 or 2 , characterized in that
a vane thickness at the rear edge of the swirl vane is smaller than 0.2 times a throat length.
6. The premixed combustion burner of a gas turbine according to claim 1 or 2 , characterized in that
fuel injection holes for injecting a fuel supplied from the fuel nozzle through fuel passages are formed in the swirl vane, and
the fuel injection holes formed in opposed vane surfaces of the adjacent swirl vanes are positioned such that positions of the fuel injection holes formed in one of the vane surfaces, and positions of the fuel injection holes formed in the other vane surface are displaced with respect to each other.
7. The premixed combustion burner of a gas turbine according to claim 1 or 2 , wherein:
a ratio between a vane height of the swirl vane and a length of the clearance (clearance length/vane height) is set at 1 to 10%.
8. A premixed combustion burner of a gas turbine, the premixed combustion burner comprising:
a fuel nozzle;
a burner tube disposed to encircle the fuel nozzle for forming an air passage between the burner tube and the fuel nozzle; and
swirl vanes which are arranged at a plurality of locations along a circumferential direction of an outer peripheral surface of the fuel nozzle in such a state as to extend along an axial direction of the fuel nozzle, and which progressively curve from an upstream side toward a downstream side for swirling air flowing through the air passage from the upstream side toward the downstream side, and
a clearance is provided between an outer peripheral side end surface of the swirl vane and an inner peripheral surface of the burner tube,
wherein in order to render the clearance between the outer peripheral side end surface of the swirl vane and the inner peripheral surface of the burner tube constant, a clearance setting rib, which makes intimate contact with the inner peripheral surface of the burner tube, is provided at a portion of the outer peripheral side end surface of the swirl vane.
9. The premixed combustion burner of a gas turbine according to claim 8 , characterized in that
a ratio between a vane height of the swirl vane and a length of the clearance (clearance length/vane height) is set at 1 to 10%.
10. The premixed combustion burner of a gas turbine according to claim 8 or 9 , characterized in that
an aspect ratio between a vane chord length and the vane height of the swirl vane (vane height/vane chord length) is set at 0.2 to 0.75.
11. The premixed combustion burner of a gas turbine according to claim 8 or 9 , characterized in that
a vane thickness of the swirl vane is a length which is 0.1 to 0.3 times a vane chord length of the swirl vane.
12. The premixed combustion burner of a gas turbine according to claim 8 or 9 , characterized in that
a vane thickness at a rear edge of the swirl vane is smaller than 0.2 times a throat length.
13. The premixed combustion burner of a gas turbine according to claim 8 or 9 , characterized in that
fuel injection holes for injecting a fuel supplied from the fuel nozzle through fuel passages are formed in the swirl vane, and
the fuel injection holes formed in opposed vane surfaces of the adjacent swirl vanes are positioned such that positions of the fuel injection holes formed in one of the vane surfaces, and positions of the fuel injection holes formed in the other vane surface are displaced with respect to each other.