Mixer assembly for a gas turbine engine
A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
1. A mixer assembly for a gas turbine engine comprising:
a main mixer comprising:
an annular inner radial wall;
an annular outer radial wall surrounding at least a portion of the annular inner radial wall, wherein the annular outer radial wall incorporates a first outer radial wall swirler with a first axis oriented substantially radially to a centerline axis of the mixer assembly;
a forward wall extending primarily radially outward with respect to the first axis and connecting the annular inner radial wall and the annular outer radial wall, the inner radial wall, forward wall, and outer radial wall forming a single annular cavity therebetween, wherein the forward wall incorporates a first forward wall swirler with a second axis oriented substantially axially to the centerline axis of the mixer assembly; and
a plurality of fuel injection holes in the forward wall between the first outer radial wall swirler and the first forward wall swirler, the fuel injection holes oriented to inject a fuel into the main mixer, wherein the fuel is atomized and dispersed by the airflow from the first forward wall swirler and is subsequently atomized and dispersed by the airflow from the first outer radial wall swirler, wherein the first outer radial wall swirler is on a first side of the plurality of fuel injection holes and the first forward wall swirler is on a second side of the plurality of fuel injection holes, the first side being opposite the second side.
2. The mixer assembly of claim 1 , wherein
the first outer radial wall swirler further comprises a first plurality of vanes forming a first plurality of air passages, wherein the first plurality of vanes are oriented at an angle with respect to the first axis to cause the air passing through the first outer radial wall swirler to rotate in a first direction; and
the first forward wall swirler further comprises a second plurality of vanes forming a second plurality of air passages, wherein the second plurality of vanes are oriented at an angle with respect to the second axis to cause the air passing through the first forward wall swirler to rotate in a second direction.
3. The mixer assembly of claim 2 , wherein the first direction is substantially opposite of the second direction.
4. The mixer assembly of claim 1 , further comprising a pilot mixer, at least a portion of which is surrounded by the main mixer, wherein the pilot mixer comprises an annular housing having an outer surface that forms the annular inner wall of the main mixer.
5. The mixer assembly of claim 1 , further comprising a fuel manifold in flow communication with the plurality of fuel injection holes.
6. The mixer assembly of claim 1 , wherein the plurality of fuel injection holes are oriented substantially perpendicularly to the second axis.
7. The mixer assembly of claim 1 , wherein the first side of the plurality of fuel injection holes is substantially opposite of the second side of the plurality of fuel injection holes.
8. A mixer assembly for a gas turbine engine comprising:
a main mixer comprising:
an annular inner radial wall;
an annular outer radial wall surrounding at least a portion of the annular inner radial wall, wherein the annular outer radial wall incorporates a plurality of outer radial wall swirlers with a first axis oriented substantially radially to a centerline axis of the mixer assembly;
a forward wall extending primarily radially outward with respect to the first axis and connecting the annular inner radial wall and the annular outer radial wall, the inner radial wall, forward wall, and outer radial wall forming a single annular cavity therebetween, wherein the forward wall incorporates a first forward wall swirler with a second axis oriented substantially axially to the centerline axis of the mixer assembly; and
a plurality of fuel injection holes in the forward wall between the plurality of outer radial wall swirlers and the first forward wall swirler, the fuel injection holes oriented to inject a fuel into the main mixer, wherein the fuel is atomized and dispersed by the airflow from the first forward wall swirler and is subsequently atomized and dispersed by the airflow from the first outer radial wall swirler, wherein the plurality of outer radial wall swirlers is on a first side of the plurality of fuel injection holes and the first forward wall swirler is on a second side of the plurality of fuel injection holes, the first side being opposite the second side.
9. The mixer assembly of claim 8 , wherein the plurality of outer radial wall swirlers further comprises:
a first outer radial wall swirler comprising a first plurality of vanes forming a first plurality of air passages, wherein the first plurality of vanes are oriented at an angle with respect to the first axis to cause the air passing through the first outer radial wall swirler to rotate in a first direction; and
a second outer radial wall swirler comprising a second plurality of vanes forming a second plurality of air passages, wherein the second plurality of vanes are oriented at an angle with respect to the first axis to cause the air passing through the second outer radial wall swirler to rotate in a second direction.
10. The mixer assembly of claim 9 , wherein the first direction is substantially opposite of the second direction.
11. The mixer assembly of claim 9 , wherein the plurality of outer radial wall swirlers further comprises a third outer radial wall swirler comprising a third plurality of vanes forming a third plurality of air passages, wherein the third plurality of vanes are oriented at an angle with respect to the first axis to cause the air passing through the third outer radial wall swirler to rotate in a third direction.
12. The mixer assembly of claim 11 , wherein the first direction is substantially the same as the third direction.
13. The mixer assembly of claim 8 , wherein the first forward wall swirler further comprises a first plurality of vanes forming a first plurality of air passages, wherein the first plurality of vanes are oriented at an angle with respect to the second axis to cause the air passing through the first forward wall swirler to rotate in a fourth direction.
14. The mixer assembly of claim 8 , further comprising a second forward wall swirler proximate the first forward wall swirler.
15. The mixer assembly of claim 14 , wherein the second forward wall swirler further comprises a second plurality of vanes forming a second plurality of air passages, wherein the second plurality of vanes are oriented at an angle with respect to the second axis to cause the air passing through the second forward wall swirler to rotate in a fifth direction.
16. The mixer assembly of claim 15 , wherein the fourth direction is substantially opposite of the fifth direction.
17. The mixer assembly of claim 8 , wherein the plurality of fuel injection holes are oriented substantially perpendicularly to the second axis.
18. The mixer assembly of claim 8 , wherein the first side of the plurality of fuel injection holes is substantially opposite of the second side of the plurality of fuel injection holes.