Premixer for low emissions gas turbine combustor
A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.
1. A premixer comprising:
a centerbody disposed along a longitudinal axis of the premixer, the centerbody defining a fuel passage therethrough and a plurality of fuel ports in communication with the fuel passage and defined through a centerbody wall;
a swirler assembly comprising:
a hub circumferentially surrounding a portion of the centerbody upstream of the plurality of fuel ports;
an annular splitter circumferentially surrounding and radially outward of the hub;
an inner swirler comprising inner swirler vanes extending between the hub and the annular splitter to impart swirl in a first direction to a flow of incoming air; and
an outer swirler comprising outer swirler vanes extending radially outward of the annular splitter to impart swirl in a second direction opposite the first direction to the flow of incoming air, the outer swirler defining an outlet plane;
a mixing duct extending downstream from the swirler assembly, the mixing duct defining a mixing chamber configured to promote mixing of the flow of incoming air and fuel,
wherein each inner swirler vane of the inner swirler includes a trailing edge disposed at an oblique angle relative to the outlet plane, and wherein the inner swirler vanes are axially offset from the outer swirler vanes in the upstream direction such that the fuel ports are axially closer to the outer swirler vanes than the inner swirler vanes; and
an outer ring circumferentially surrounding and radially outward of the outer swirler, the outer ring defining a primary fuel plenum therein, wherein the mixing duct comprises a secondary fuel manifold defining a secondary fuel plenum proximate to the primary fuel plenum, wherein a conical wall extends downstream from the secondary fuel manifold, the conical wall defining a series of secondary fuel passages that extend from the secondary fuel plenum to respective secondary fuel outlets on a downstream end of the mixing duct.
2. The premixer of claim 1 , wherein the oblique angle is from 20 degrees to 55 degrees.
3. The premixer of claim 2 , wherein the oblique angle is a 45-degree angle.
4. The premixer of claim 1 , wherein the inner swirler has from three inner swirler vanes to eleven inner swirler vanes.
5. The premixer of claim 1 , wherein the series of secondary fuel passages has from eight to thirty-two passages.
6. The premixer of claim 1 , wherein the centerbody comprises a cylindrical upstream portion and a conical downstream portion, the plurality of fuel ports being defined through the centerbody wall in the cylindrical upstream portion.
7. The premixer of claim 6 , wherein the cylindrical upstream portion of the centerbody comprises a first portion having a first diameter and extending through the hub and a second portion having a second diameter extending axially downstream of the hub, the first portion having a smaller diameter than the second portion, and the second portion engaging the hub.
8. A dual fuel premixer comprising:
a centerbody disposed along a longitudinal axis of the dual fuel premixer, the centerbody defining a fuel passage therethrough and a plurality of fuel ports in communication with the fuel passage and defined through a centerbody wall;
a swirler assembly comprising:
a hub circumferentially surrounding a portion of the centerbody upstream of the plurality of fuel ports;
an annular splitter circumferentially surrounding and radially outward of the hub;
an outer ring circumferentially surrounding and radially outward of the annular splitter, the outer ring defining a primary fuel plenum therein;
a first array of inner swirler vanes extending between the hub and the annular splitter to impart swirl in a first direction to a flow of incoming air; and
a second array of outer swirler vanes extending between the annular splitter and the primary fuel plenum to impart swirl in a second direction opposite the first direction to the flow of incoming air, each outer swirler vane of the second array defining at least one fuel metering hole therein in fluid communication with the primary fuel plenum, the second array of outer swirler vanes defining an outlet plane; and
a mixing duct extending downstream from the primary fuel plenum, the mixing duct defining a mixing chamber configured to promote mixing of the flow of incoming air and fuel,
wherein each inner swirler vane of the first array has a first portion connected to the hub and a second portion connected to the annular splitter, the first portion being shorter than the second portion, such that an oblique angle is defined between a trailing edge of each inner swirler vane and the outlet plane of the second array of outer swirler vanes, wherein the inner swirler vanes are axially offset from the outer swirler vanes in the upstream direction such that the fuel ports are axially closer to the outer swirler vanes than the inner swirler vanes, and wherein the trailing edge of each inner swirler vane curves circumferentially at an increasing rate from the first portion to the second portion.
9. The dual fuel premixer of claim 8 , wherein the oblique angle is from 20 degrees to 55 degrees.
10. The dual fuel premixer of claim 9 , wherein the oblique angle is a 45-degree angle.
11. The dual fuel premixer of claim 8 , wherein the first array of inner swirler vanes has from three inner swirler vanes to eleven inner swirler vanes.
12. The dual fuel premixer of claim 8 , wherein the mixing duct comprises a secondary fuel manifold defining a secondary fuel plenum proximate to the primary fuel plenum;
and a conical wall extending downstream from the secondary fuel manifold, the conical wall defining a series of secondary fuel passages that extend from the secondary fuel plenum to respective secondary fuel outlets on a downstream end of the mixing duct.
13. The dual fuel premixer of claim 12 , wherein the series of secondary fuel passages has from eight to thirty-two passages.
14. The dual fuel premixer of claim 8 , wherein the centerbody comprises a cylindrical upstream portion and a conical downstream portion, the plurality of fuel ports being disposed through the centerbody wall in the cylindrical upstream portion.
15. The dual fuel premixer of claim 14 , wherein the cylindrical upstream portion of the centerbody comprises a first portion having a first diameter and extending through the hub and a second portion having a second diameter extending axially downstream of the hub, the first portion having a smaller diameter than the second portion, and the second portion engaging the hub.
16. A premixer comprising:
a centerbody disposed along a longitudinal axis of the premixer, the centerbody defining a fuel passage therethrough and a plurality of fuel ports in communication with the fuel passage and defined through a centerbody wall;
a swirler assembly comprising:
a hub circumferentially surrounding a portion of the centerbody upstream of the plurality of fuel ports;
an annular splitter circumferentially surrounding and radially outward of the hub;
an inner swirler comprising inner swirler vanes extending between the hub and the annular splitter to impart swirl in a first direction to a flow of incoming air; and
an outer swirler comprising outer swirler vanes extending radially outward of the annular splitter to impart swirl in a second direction opposite the first direction to the flow of incoming air, the outer swirler defining an outlet plane;
a mixing duct extending downstream from the swirler assembly, the mixing duct defining a mixing chamber configured to promote mixing of the flow of incoming air and fuel,
wherein each inner swirler vane has a first portion connected to the hub and a second portion connected to the annular splitter, wherein each inner swirler vane of the inner swirler includes a trailing edge disposed at an oblique angle relative to the outlet plane, wherein the inner swirler vanes are axially offset from the outer swirler vanes in the upstream direction such that the fuel ports are axially closer to the outer swirler vanes than the inner swirler vanes, and wherein the trailing edge of each inner swirler vane curves circumferentially at an increasing rate from the first portion to the second portion.
17. The premixer of claim 16 , wherein the oblique angle is from 20 degrees to 55 degrees.
18. The premixer of claim 17 , wherein the oblique angle is a 45-degree angle.
19. The premixer of claim 16 , wherein the inner swirler has from three inner swirler vanes to eleven inner swirler vanes.