Line replaceable fuel nozzle apparatus, system and method
In various embodiments, a fuel injector may comprise a fuel nozzle and a pilot stage. The fuel nozzle may define a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area. The main fuel channel may be disposed about at least a portion of the simplex fuel channel. The secondary fuel channel may be disposed about at least a portion of the simplex fuel channel. The heat shield area may be configured to separate and protect the fuel channels from a heat load to prevent fuel coking. The pilot stage may be operatively coupled to the fuel nozzle and may be configured to receive fuel from the secondary fuel channel or the simplex fuel channel. The main stage may be operatively coupled to the fuel nozzle. The main stage may be configured to receive fuel from the main fuel channel.
1. A fuel injector, comprising:
a fuel nozzle, including a radially extending inlet stem, defining a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area,
wherein the heat shield area is disposed about and configured to separate and protect the main fuel channel, the secondary fuel channel and the simplex fuel channel from a heat load to prevent fuel coking,
wherein a portion of the simplex fuel channel located in the radially extending inlet stem is of circular cross section defining a circumference having a first half and a second half, wherein the secondary fuel channel surrounds the first half circumference of the simplex fuel channel and the main fuel channel surrounds the second half circumference of the simplex fuel channel;
a pilot stage operatively coupled to, and in fluid communication with, the fuel nozzle and configured to receive fuel from the the secondary fuel channel and the simplex fuel channel; and
a main stage in fluid communication with and configured to receive fuel from the main fuel channel, wherein the simplex fuel channel is disposed in the center of the fuel nozzle and wherein the main fuel channel and the secondary fuel channel are disposed about the simplex fuel channel.
2. The fuel injector of claim 1 , wherein the fuel injector is a line replaceable unit.
3. The fuel injector of claim 1 , wherein the fuel nozzle has an outer profile that has a cross sectional shape that is at least one of a circle, a diamond, or a square.
4. The fuel injector of claim 1 , wherein the fuel nozzle is produced by an additive manufacturing process.
5. The fuel injector of claim 1 , wherein the fuel injector is a single piece made by an additive manufacturing process.
6. The fuel injector of claim 1 , wherein at least one of the main fuel channel, the secondary fuel channel, or the simplex fuel channel includes a turn defined within the fuel nozzle.
7. The fuel injector of claim 1 , wherein the radially extending inlet stem includes a main flow area in fluid communication with the main fuel channel, a secondary flow area in fluid communication with the secondary fuel channel, and a simplex flow area in fluid communication with the simplex fuel channel.
8. The fuel injector of claim 7 , wherein the simplex flow area is disposed in the middle of the the radially extending inlet stem.
9. The fuel injector of claim 8 , wherein the main stage is an area defined between a pilot can and a radial swirler.
10. The fuel injector of claim 8 , wherein a heat shield flow area is disposed about the main flow area, the secondary flow area and the simplex flow area.
11. The fuel injector of claim 7 , wherein the main flow area disposed about a portion of the simplex flow area and the secondary flow area is disposed about a portion of the simplex flow area.
12. The fuel injector of claim 11 , wherein the main flow area and the secondary flow area are disposed circumferentially about the simplex flow area.
13. A gas turbine engine comprising,
a compressor;
a combustor in fluid communication with the compressor;
a turbine in fluid communication with the combustor; and
a fuel injector that is removable and installable within the combustor and configured to conduct fuel to the combustor, the fuel injector comprising: a fuel nozzle, including a radially extending inlet stem, defining a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area,
wherein the heat shield area is disposed about and configured to surround the simplex fuel channel,
wherein a portion of the simplex fuel channel located in the radially extending inlet stem is of circular cross section defining a circumference having a first half and a second half, wherein the secondary fuel channel surrounds the first half circumference of the simplex fuel channel and the main fuel channel surrounds the second half circumference of the simplex fuel channel, and
wherein the simplex fuel channel is disposed in the center of the fuel nozzle and wherein the main fuel channel and the secondary fuel channel are disposed about the simplex fuel channel;
a pilot stage operatively coupled to, and in fluid communication with, the fuel nozzle and configured to receive fuel from the secondary fuel channel and the simplex fuel channel; and
a main stage in fluid communication with and configured to receive fuel from the main fuel channel.
14. The gas turbine engine of claim 13 , wherein the fuel injector is a line replaceable unit.
15. The gas turbine engine of claim 13 , wherein the fuel injector is an assembly.
16. The gas turbine engine of claim 13 , wherein the fuel nozzle is made from an additive manufacturing process.
17. A fuel injector, comprising:
a fuel nozzle having a radially extending inlet stem and defining a main fuel channel, a secondary fuel channel, a simplex fuel channel and a heat shield area,
wherein the inlet defines a main flow area in fluid communication with the main fuel channel, a secondary flow area in fluid communication with the secondary fuel channel, and a simplex flow area in fluid communication with the simplex fuel channel,
wherein the simplex fuel channel is disposed in the center of the fuel nozzle and wherein the main fuel channel and the secondary fuel channel are disposed about the simplex fuel channel,
wherein the heat shield area is configured to separate and protect the main fuel channel, the secondary fuel channel and the simplex fuel channel from a heat load to prevent fuel coking,
wherein a portion of the simplex fuel channel located in the radially extending inlet stem is of circular cross section defining a circumference having a first half and a second half, wherein the secondary fuel channel surrounds the first half circumference of the simplex fuel channel and the main fuel channel surrounds the second half circumference of the simplex fuel channel; and
wherein the fuel nozzle is formed as a single piece;
a pilot stage operatively coupled to, and in fluid communication with, the fuel nozzle and configured to receive fuel from the secondary fuel channel and the simplex fuel channel; and
a main stage in fluid communication with and configured to receive fuel from the main fuel channel.
18. The fuel injector of claim 17 , wherein the fuel injector is a line replaceable unit.
19. The fuel injector of claim 17 , wherein the fuel nozzle is formed by an additive manufacturing process.
20. The fuel injector of claim 17 , wherein the pilot stage is defined by a pilot can, wherein a radial swirler is disposed about the pilot can, and wherein the main stage is defined between the pilot can and the radial swirler.