A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to
A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to a second end. The first end may be configured to be fluidly coupled to a compressor of the turbine engine and the second end may be configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a perforated plate positioned proximate the first end of the passageway. The perforated plate may be configured to direct compressed air into the annular passageway with a first pressure drop. The fuel injector may also include at least one fuel discharge orifice positioned downstream of the perforated plate. The at least one fuel discharge orifice may be configured to discharge a fuel into the annular passageway with a second pressure drop. The second pressure drop may have a value between about the first pressure drop and about 1.75 times the first pressure drop.
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1. A fuel injector for a turbine engine, comprising: a body member disposed about a longitudinal axis;a barrel member located radially outwardly from the body member;an annular passageway extending between the body member and the barrel member from a first end to a second end, the first end configur
1. A fuel injector for a turbine engine, comprising: a body member disposed about a longitudinal axis;a barrel member located radially outwardly from the body member;an annular passageway extending between the body member and the barrel member from a first end to a second end, the first end configured to be fluidly coupled to a compressor of the turbine engine and the second end configured to be fluidly coupled to a combustor of the turbine engine;a perforated plate, having a plurality of perforations, positioned proximate the first end of the passageway, the perforated plate being configured to direct compressed air into the annular passageway with a first pressure drop; andat least one fuel discharge orifice positioned downstream of the perforated plate, the at least one fuel discharge orifice being configured to discharge a fuel into the annular passageway with a second pressure drop, the second pressure drop having a value between about the first pressure drop and about 1.75 times the first pressure drop. 2. The fuel injector of claim 1, wherein the second pressure drop has a value between about the first pressure drop and about 1.5 times the first pressure drop. 3. The fuel injector of claim 1, wherein a distance between the at least one fuel discharge orifice and the perforated plate is less than or equal to about 4% of a wavelength of a combustion induced pressure wave induced in the combustor during operation of the turbine engine. 4. The fuel injector of claim 1, wherein a distance between the at least one fuel discharge orifice and the perforated plate is less than or equal to about 2% of a wavelength of a combustion induced pressure wave induced in the combustor during operation of the turbine engine. 5. The fuel injector of claim 1, wherein a distance between the at least one fuel discharge orifice and the perforated plate is less than or equal to about 0.75 inches. 6. The fuel injector of claim 1, wherein the perforated plate includes a plurality of perforations arranged substantially symmetrically around the longitudinal axis. 7. The fuel injector of claim 6, wherein the plurality of perforations include a first array of perforations having a substantially constant first diameter, and a second array of perforations spaced radially inwardly of the first array and having a substantially constant second diameter smaller than the first diameter. 8. The fuel injector of claim 1, further including an air swirler having a plurality of vanes positioned in the annular passageway, the at least one fuel discharge orifice being positioned on a first vane of the plurality of vanes. 9. The fuel injector of claim 8, wherein the at least one fuel discharge orifice includes a plurality of fuel discharge orifices positioned on an upstream side of the first vane. 10. The fuel injector of claim 1, wherein the at least one fuel discharge orifice is configured to discharge a gaseous fuel into the annular passageway. 11. A method of operating a turbine engine including a fuel injector fluidly coupling a compressor and a combustor of the turbine engine, comprising: directing a compressed air stream into an upstream end of the fuel injector with a first pressure drop;directing a fuel with a second pressure drop into the compressed air stream at a location less than or equal to about 0.75 inches downstream of the upstream end, wherein the second pressure drop has a value between about the first pressure drop and about 1.75 times the first pressure drop; anddelivering the fuel and the compressed air stream to the combustor as a fuel-air mixture. 12. The method of claim 11, wherein directing the fuel includes directing the fuel into the compressed air stream with a second pressure drop having a value between about the first pressure drop and about 1.5 times the first pressure drop. 13. The method of claim 11, wherein directing the compressed air stream includes directing compressed air into the upstream end of the fuel injector through a perforated plate, the perforated plate including a plurality of perforations arranged substantially symmetrically around a longitudinal axis of the fuel injector. 14. The method of claim 11, wherein directing a fuel includes directing a gaseous fuel into the compressed air stream. 15. The method of claim 11, wherein directing a fuel includes directing the fuel into the compressed air stream through a plurality of fuel discharge orifices positioned on an air swirler of the fuel injector. 16. A method of operating a turbine engine configured to have a combustion induced pressure wave induced in a combustor of the turbine engine during the operation, including: directing a fuel-air mixture to the combustor through a fuel injector having a longitudinal axis, including: directing compressed air into the fuel injector through a perforated plate having a plurality of perforations arranged substantially symmetrically around the longitudinal axis, the compressed air being subject to a first pressure drop across the perforated plate;discharging a fuel into the fuel injector through a plurality of fuel discharge orifices positioned at a first length downstream of the perforated plate, the first length being less than or equal to about 4% of a wavelength of the pressure wave induced in the combustor, and the fuel being subject to a second pressure drop across the fuel discharge orifices, wherein the second pressure drop has a value between about the first pressure drop and about 1.75 times the first pressure drop;mixing the fuel in the compressed air to create the fuel-air mixture; andcombusting the fuel-air mixture in the combustor. 17. The method of claim 16, wherein discharging the fuel includes discharging a gaseous fuel into the compressed air, and the first length is less than or equal to about 2% of the wavelength of the pressure wave. 18. The method of claim 16, wherein the second pressure drop has a value between about the first pressure drop and about 1.5 times the first pressure drop. 19. The method of claim 16, wherein discharging the fuel includes discharging a fuel through a plurality of fuel discharge orifices positioned on an air swirler of the fuel injector. 20. The method of claim 16, wherein the first length is about 0.5 inches.
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이 특허에 인용된 특허 (7)
Morford Stephen A., Durability flame stabilizing fuel injector with impingement and transpiration cooled tip.
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