Coaxial fuel and air premixer for a gas turbine combustor
An air/fuel premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage, at least one air inlet for introducing air through the inner air passage and the outer air passage to the mixing chamber, and at least one fuel inlet for injecting fuel through the fuel gas passage to the mixing chamber to form an air/fuel mixture.
1. An air/fuel premixer comprising:
a peripheral wall defining a mixing chamber;
a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall, so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage;
at least one air inlet for introducing air through the inner air passage and the outer air passage to the mixing chamber; and
at least one fuel inlet for injecting gaseous fuel through the fuel gas passage to the mixing chamber to form an air/fuel mixture,
wherein the at least one air inlet is located upstream of the mixing chamber such that the air introduced through the inner air passage and the outer air passage is axially oriented at the point it enters the mixing chamber.
2. The air/fuel premixer of claim 1 , wherein the outer annular wall and the inner annular wall have outlet ends which are curved.
3. The air/fuel premixer of claim 1 , wherein the outer annular wall and the inner annular wall have outlet ends which are sharpened to narrow edges.
4. The air/fuel premixer of claim 1 , wherein the nozzle further comprises a third annular wall disposed at least partially between and spaced from the outer annular wall and the inner annular wall, so as to define at least one inert annulus, the at least one inert annulus defining at least one inert gas passage adjacent to the at least one fuel gas passage, wherein the at least one inert annulus terminates at or immediately upstream of the end of the at least one fuel gas annulus.
5. The air/fuel premixer of claim 1 , wherein the nozzle further comprises:
a third annular wall disposed at least partially between and spaced from the outer annular wall and the inner annular wall, so as to define an outer inert annulus, the outer inert annulus defining an outer inert gas passage between the at least one fuel gas passage and the outer air passage; and
a fourth annular wall disposed at least partially between and spaced from the third annular wall and the inner annular wall, so as to define an inner inert annulus, the inner inert annulus defining an inner inert gas passage between the at least one fuel gas passage and the inner air passage.
6. The air/fuel premixer of claim 1 , wherein the nozzle is non-circular shaped.
7. The air/fuel premixer of claim 1 , wherein the at least one fuel gas annulus is non-circular shaped.
8. A gas turbine combustor comprising:
at least one air/fuel premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall, so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage;
at least one combustion chamber in connection with the mixing chamber;
at least one air inlet for introducing air through the inner air passage and the outer air passage to the mixing chamber; and
at least one fuel inlet for injecting gaseous fuel through the fuel gas passage to the mixing chamber to form an air/fuel mixture for injection into the at least one combustion chamber,
wherein the at least one air inlet is located upstream of the mixing chamber such that the air introduced through the inner air passage and the outer air passage is axially oriented at the point it enters the mixing chamber.
9. The gas turbine combustor of claim 8 , wherein the outer annular wall and the inner annular wall have outlet ends which are curved or rounded.
10. The gas turbine combustor of claim 8 , wherein the outer annular wall and the inner annular wall have outlet ends which are sharpened to narrow edges.
11. The gas turbine combustor of claim 8 , wherein the nozzle further comprises a third annular wall disposed at least partially between and spaced from the outer annular wall and the inner annular wall, so as to define at least one inert annulus, the at least one inert annulus defining at least one inert gas passage adjacent to the at least one fuel gas passage, wherein the at least one inert annulus terminates at or immediately upstream of the end of the at least one fuel gas annulus.
12. The gas turbine combustor of claim 8 , wherein the nozzle further comprises:
a third annular wall disposed at least partially between and spaced from the outer annular wall and the inner annular wall, so as to define an outer inert annulus, the outer inert annulus defining an outer inert gas passage between the at least one fuel gas passage and the outer air passage; and
a fourth annular wall disposed at least partially between and spaced from the third annular wall and the inner annular wall, so as to define an inner inert annulus, the inner inert annulus defining an inner inert gas passage between the at least one fuel gas passage and the inner air passage.
13. The gas turbine combustor of claim 8 , the premixer further comprising a swirling means downstream of the at least one air inlet.
14. The gas turbine combustor of claim 8 , further comprising a turbulence-generating screen or mesh downstream of the at least one air inlet.
15. A method of premixing fuel and air in a premixer for a combustion system of a gas turbine, the premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall, so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage, at least one air inlet, and at least one fuel inlet, the method comprising:
introducing air into the outer air passage to form an outer air stream;
introducing air into the inner air passage to form an inner air stream;
introducing gaseous fuel into the fuel gas passage to form a fuel stream;
flowing the incoming air coaxially as the incoming gaseous fuel;
flowing the outer air stream and the inner air stream coaxially as the fuel stream; and
thereafter, introducing the coaxially flowing fuel stream, outer air stream, and inner air stream in the mixing chamber to form an air/fuel mixture for injection into a combustion chamber in connection with the mixing chamber.
16. The method of claim 15 , wherein the outer annular wall and the inner annular wall have outlet ends which are curved or rounded.
17. The method of claim 15 , wherein the outer annular wall and the inner annular wall have outlet ends which are sharpened to narrow edges.
18. The method of claim 15 , wherein the premixer further comprises at least one inert gas inlet and the nozzle further comprises a third annular wall disposed at least partially between and spaced from the outer annular wall and the inner annular wall, so as to define an outer inert annulus, the outer inert annulus defining an outer inert gas passage between the at least one fuel gas passage and the outer air passage, and a fourth annular wall disposed at least partially between and spaced from the third annular wall and the inner annular wall, so as to define an inner inert annulus, the inner inert annulus defining an inner inert gas passage between the at least one fuel gas passage and the inner air passage, the method further comprising:
introducing an inert gas into the outer inert gas passage to form an outer inert gas stream;
introducing an inert gas into the inner inert gas passage to form an inner inert gas stream;
flowing the incoming inert gas coaxially as the incoming fuel;
flowing the outer inert gas stream and the inner inert gas stream coaxially as the fuel stream; and
injecting the inner and outer inert gas streams to the mixing chamber at or immediately upstream of where the fuel stream is injected into the mixing chamber.
19. The method of claim 15 , the premixer further comprising a swirling means downstream of the at least one air inlet and upstream of where the fuel stream is injected into the mixing chamber.
20. The method of claim 15 , wherein the at least one fuel gas annulus is circular, elliptical, or daisy-shaped.