Co-axial dual swirler nozzle

1. A combustion nozzle of a gas turbine, comprising:

a center cylinder formed by a sidewall of a cylinder shape having a first length in an axial direction, the first length measured from an imaginary plane disposed at an upstream end of the combustion nozzle, the imaginary plane passing perpendicularly through a cylinder axis of the center cylinder, the center cylinder having one end disposed at the imaginary plane;

a middle cylinder coaxially disposed with respect to the center cylinder and formed by a sidewall of a cylinder shape having a second length in the axial direction, the middle cylinder having one end disposed at the imaginary plane and surrounding the center cylinder, the second length measured from the imaginary plane;

an outer cylinder coaxially disposed with respect to the middle cylinder and formed by a sidewall of a cylinder shape having a third length in the axial direction, the outer cylinder having one end disposed at the imaginary plane and surrounding the middle cylinder, the third length measured from the imaginary plane; and

a perforated plate disposed inside the center cylinder to create turbulent flow through the center cylinder, the perforated plate including a circular plate having a disc shape that passes through the cylinder axis of the center cylinder and abuts the sidewall of the center cylinder on opposite sides of the cylinder axis of the center cylinder, the perforated plate having a plurality of holes to create the turbulent flow,

wherein a ratio of an area of the plurality of holes to an area of the perforated plate has a value of 60% to 80%,

wherein the middle cylinder creates two separate flow regions outside the center cylinder, and

wherein the second length is greater than the first length.

2. The combustion nozzle of claim 1 , further comprising inner vanes disposed between the center cylinder and the middle cylinder and outer vanes disposed between the middle cylinder and the outer cylinder, wherein the inner vanes and the outer vanes have a leading edge.

3. The combustion nozzle of claim 2 ,

wherein a vane angle of the inner vanes and the outer vanes is defined as a degree to which a vane is inclined from the leading edge of the vane with respect to the cylinder axis of the center cylinder, and

wherein a product of an angle of the inner vanes and an angle of the outer vanes has a negative value.

4. The combustion nozzle of claim 3 ,

wherein the middle cylinder (Rm) has a cylinder radius defined by

Rm=Rh +β×( R 0− Rh ), and

wherein β has a value from 0.1 to 0.9, Rh is a radius of the center cylinder, and R 0 is a radius of the outer cylinder.

5. The combustion nozzle of claim 4 ,

wherein the center cylinder is configured to pass a fluid at a flow velocity Uc, and the middle cylinder and outer cylinder may pass a fluid at a flow velocity U, and

wherein the ratio of Uc to U has a value of 0.4 to 0.6.

6. The combustion nozzle of claim 3 , further comprising a cone-shaped diverging nozzle tip attached to the outer cylinder to create a diverging flow downstream of the nozzle to improve fuel and air mixing efficiency.

7. The combustion nozzle of claim 3 , wherein the the plurality of holes are arranged along a plurality of concentric circles around the cylinder axis of the center cylinder.

8. The combustion nozzle of claim 2 ,

wherein a vane angle of the inner vanes and the outer vanes is defined as a degree to which a vane is inclined from the leading edge of the vane with respect to the cylinder axis of the center cylinder, and

wherein a product of an angle of the inner vanes and an angle of the outer vanes has a positive value.

9. The combustion nozzle of claim 8 ,

wherein the middle cylinder (Rm) has a cylinder radius defined by

Rm=Rh +β×( R 0− Rh ), and

wherein β has a value from 0.1 to 0.9, Rh is a radius of the center cylinder, and R 0 is a radius of the outer cylinder.

10. The combustion nozzle of claim 9 ,

wherein the center cylinder may pass a fluid at a flow velocity Uc, and the middle cylinder and outer cylinder is configured to pass a fluid at a flow velocity U, and

wherein the ratio of Uc to U has a value of 0.4 to 0.6.

11. The combustion nozzle of claim 8 , further comprising a cone-shaped diverging nozzle tip attached to the outer cylinder to create a diverging flow downstream of the nozzle to improve fuel and air mixing efficiency.

12. The combustion nozzle of claim 8 , wherein the the plurality of holes are arranged along a plurality of concentric circles around the cylinder axis of the center cylinder.

13. A gas turbine, comprising:

a compressor for compressing air received from an external environment;

a combustor for producing combustion gas by mixing the compressed air with fuel and combusting the mixture at a constant pressure, the combustor including a combustion nozzle; and

a turbine for generating power by receiving the combustion gas,

wherein the combustion nozzle comprises:

a center cylinder formed by a sidewall of a cylinder shape having a first length in an axial direction, the first length measured from an imaginary plane disposed at an upstream end of the combustion nozzle, the imaginary plane passing perpendicularly through a cylinder axis of the center cylinder, the center cylinder having one end disposed at the imaginary plane;

a middle cylinder coaxially disposed with respect to the center cylinder and formed by a sidewall of a cylinder shape having a second length in the axial direction, the middle cylinder having one end disposed at the imaginary plane and surrounding the center cylinder, the second length measured from the imaginary plane;

an outer cylinder coaxially disposed with respect to the middle cylinder and formed by a sidewall of a cylinder shape having a third length in the axial direction, the outer cylinder having one end disposed at the imaginary plane and surrounding the middle cylinder, the third length measured from the imaginary plane; and

a perforated plate disposed inside the center cylinder to create turbulent flow through the center cylinder, the perforated plate including a circular plate having a disc shape that passes through the cylinder axis of the center cylinder and abuts the sidewall of the center cylinder on opposite sides of the cylinder axis of the center cylinder, the circular plate having a plurality of holes to create the turbulent flow,

wherein a ratio of an area of the plurality of holes to an area of the perforated plate has a value of 60% to 80%,

wherein the middle cylinder creates two separate flow regions outside the center cylinder, and

wherein the second length is greater than the first length.

14. The gas turbine of claim 13 , further comprising inner vanes disposed between the center cylinder and the middle cylinder and outer vanes disposed between the middle cylinder and the outer cylinder, wherein the inner vanes and the outer vanes have a leading edge.

15. The gas turbine of claim 14 ,

wherein a vane angle of the inner vanes and the outer vanes is defined as a degree to which a vane is inclined from the leading edge of the vane with respect to the cylinder axis of the center cylinder, and

wherein a product of an angle of the inner vanes and an angle of the outer vanes has a negative value.

16. The gas turbine of claim 15 ,

wherein the middle cylinder (Rm) has a cylinder radius defined by

Rm=Rh +β×( R 0− Rh ), and

wherein β has a value from 0.1 to 0.9, Rh is a radius of the center cylinder, and R 0 is a radius of the outer cylinder.

17. The gas turbine of claim 16 ,

wherein the center cylinder may pass a fluid at a flow velocity Uc, and the middle cylinder and outer cylinder is configured to pass a fluid at a flow velocity U, and

wherein the ratio of Uc to U has a value of 0.4 to 0.6.

18. The gas turbine of claim 14 ,

wherein a vane angle of the inner vanes and the outer vanes is defined as a degree to which a vane is inclined from the leading edge of the vane with respect to the cylinder axis of the center cylinder, and

wherein a product of an angle of the inner vanes and an angle of the outer vanes has a positive value.

19. The gas turbine of claim 13 , wherein the second length and the third length are equal to each other.

20. The combustion nozzle of claim 1 , wherein the second length and the third length are equal to each other.

21. A combustion nozzle of a gas turbine, comprising:

a center cylinder formed by a sidewall of a cylinder shape having a first length in an axial direction, the first length measured from an imaginary plane disposed at an upstream end of the combustion nozzle, the imaginary plane passing perpendicularly through a cylinder axis of the center cylinder, the center cylinder having one end disposed at the imaginary plane;

a middle cylinder coaxially disposed with respect to the center cylinder and formed by a sidewall of a cylinder shape having a second length in the axial direction, the middle cylinder having one end disposed at the imaginary plane and surrounding the center cylinder, the second length measured from the imaginary plane;

an outer cylinder coaxially disposed with respect to the middle cylinder and formed by a sidewall of a cylinder shape having a third length in the axial direction, the outer cylinder having one end disposed at the imaginary plane and surrounding the middle cylinder, the third length measured from the imaginary plane;

a perforated plate disposed inside the center cylinder to create turbulent flow through the center cylinder, the perforated plate including a circular plate having a disc shape that passes through the cylinder axis of the center cylinder and abuts the sidewall of the center cylinder on opposite sides of the cylinder axis of the center cylinder;

inner vanes disposed between the center cylinder and the middle cylinder; and

outer vanes disposed between the middle cylinder and the outer cylinder,

wherein the inner vanes and the outer vanes have a leading edge,

wherein the middle cylinder creates two separate flow regions outside the center cylinder, and

wherein the second length is greater than the first length.