A lean premix burner for a gas-turbine engine includes an annular center body (3) with a conically flaring fuel film applicator (11) supplied with fuel via an annular distributor chamber (14) and fuel channels (12) as well as air ducts (7, 9) with swirler elements (8, 10) provided on the outer and i
A lean premix burner for a gas-turbine engine includes an annular center body (3) with a conically flaring fuel film applicator (11) supplied with fuel via an annular distributor chamber (14) and fuel channels (12) as well as air ducts (7, 9) with swirler elements (8, 10) provided on the outer and inner circumference. A fuel prefilmer lip (15) is attached to the fuel film applicator (11), with a flow area of a portion of the annular air ducts (7, 9) downstream of the swirler elements (8, 10) decreasing to accelerate the air swirled in correspondence with the airflow direction. By this, the fuel is transported positively without interim separation and without the occurrence of compressive oscillation—to a defined flow break-away edge (16), providing for a good mixture, high combustion efficiency and reduced formation of nitrogen oxide.
대표청구항▼
1. A lean premix burner for a gas-turbine engine, comprising: an annular center body having a conically flaring fuel film applicator;an annular fuel distribution chamber;at least one annular fuel channel for receiving fuel from the annular fuel distribution chamber and supplying fuel to a radially i
1. A lean premix burner for a gas-turbine engine, comprising: an annular center body having a conically flaring fuel film applicator;an annular fuel distribution chamber;at least one annular fuel channel for receiving fuel from the annular fuel distribution chamber and supplying fuel to a radially inner surface of the fuel film applicator and a radially outer surface of the fuel film applicator, or to the radially outer surface of the fuel film applicator;a first annular air duct having a first swirler element positioned on an outer circumference of the annular center body;a second annular air duct having a second swirler element positioned on an inner circumference of the annular center body;a V-shroud flame stabilizer at least partially positioned within the inner circumference of the annular center body;a pilot fuel injector positioned radially inwardly of the V-shroud flame stabilizer;a fuel prefilmer lip attached to the fuel film applicator and configured to extend downstream beyond an adjacent wall of a combustion chamber wall into a combustion chamber of the gas-turbine engine, at least a portion of the fuel prefilmer lip being the most downstream portion of the lean premix burner, an entirety of the V-shroud flame stabilizer positioned upstream of the most downstream portion of the fuel prefilmer lip;wherein a flow area of the first annular air duct downstream of the first swirler element and upstream of a free end of the fuel prefilmer lip decreases with respect to a flow area of the first swirler element to accelerate air flowing in the first annular duct, and a flow area of the second annular air duct downstream of the second swirler element and upstream of the free end of the fuel prefilmer lip decreases with respect to a flow area of the second swirler element to accelerate air flowing in the second annular duct, the flow area of the second annular air duct steadily decreasing past and substantially downstream of the at least one annular fuel channel to steadily accelerate the air flowing in the second annular duct past and substantially downstream of the at least one annular fuel channel, the accelerated air in each of the annular ducts being imparted with swirl directions to act upon a fuel film of the fuel film applicator corresponding to a flow direction of the fuel film. 2. A lean premix burner in accordance with claim 1, and further comprising fuel openings issuing into at least one of the at least one annular fuel channel and the annular distributor chamber, which fuel openings are oriented to generate a fuel swirl in the at least one annular fuel channel that corresponds to the swirl direction of the air acting upon the fuel film. 3. A lean premix burner in accordance with claim 2, wherein the at least one annular fuel channel is oriented at an obtuse angle to the surface of the fuel film applicator. 4. A lean premix burner in accordance with claim 1, wherein the free end of the fuel prefilmer lip is formed as a plane surface with opposite edges to create a well-defined flow break-away edge for the fuel film. 5. A lean premix burner in accordance with claim 1, wherein the flow cross-sections in the first and second annular air ducts are different to achieve a defined air distribution. 6. A lean premix burner in accordance with claim 1, wherein the first and second swirler elements include guide vane assemblies with aerodynamic profile shaped guide vanes. 7. A lean premix burner in accordance with claim 1, wherein the first swirler element generates a first circumferential swirl of air in the first annular duct and the second swirler element generates a second circumferential swirl of air in the second annular duct and the first and second circumferential swirls of air swirl in a same rotating direction. 8. A lean premix burner in accordance with claim 1, wherein fuel is supplied to at least one chosen from of a radially inner surface and a radially outer surface of at least one chosen from the fuel film applicator and the fuel prefilmer lip for the formation of the fuel film. 9. A lean premix burner in accordance with claim 8, wherein the at least one annular fuel channel issues equal quantities of fuel to both the radially inner surface and the radially outer surface of the at least one chosen from the fuel film applicator and the fuel prefilmer lip. 10. A lean premix burner in accordance with claim 9, wherein the at least one annular fuel channel is only partly filled with fuel. 11. A lean premix burner in accordance with claim 1, wherein the pilot fuel injector is at least one of a pressure atomizer, an air-blast atomizer type, and a combination of both. 12. A lean premix burner in accordance with claim 1, wherein an upper edge of an outer flank of the V-shroud flame stabilizer ends in an area which extends beyond a flow break-away edge of the fuel prefilmer lip. 13. A lean premix burner in accordance with claim 4, wherein the flow break-away edge is positioned in an area downstream of a front side of an outer ring of the burner. 14. A lean premix burner in accordance with claim 1, wherein the first swirler element generates a first circumferential swirl of air in the first annular duct and the second swirler element generates a second circumferential swirl of air in the second annular duct and the first and second circumferential swirls of air swirl in a counter-rotating direction. 15. A lean premix burner in accordance with claim 8, wherein the at least one annular fuel channel issues fuel to both the radially inner surface and the radially outer surface of the at least one chosen from the fuel film applicator and the fuel prefilmer lip, with quantities of fuel being issued to the inner and outer surfaces being different. 16. A lean premix burner in accordance with claim 9, wherein the at least one annular fuel channel is fully filled with fuel. 17. A lean premix burner in accordance with claim 1, wherein the at least one annular fuel channel supplies fuel to the radially inner surface of the fuel film applicator and the radially outer surface of the fuel film applicator. 18. A method for providing a lean premix combustion for a gas-turbine engine, comprising: providing a lean premix burner having: an annular center body having a conically flaring fuel film applicator;an annular fuel distribution chamber;at least one annular fuel channel for receiving fuel from the annular fuel distribution chamber and supplying fuel to a radially inner surface of the fuel film applicator and a radially outer surface of the fuel film applicator, or to the radially outer surface of the fuel film applicator;a first annular air duct having a first swirler element positioned on an outer circumference of the annular center body;a second annular air duct having a second swirler element positioned on an inner circumference of the annular center body;a V-shroud flame stabilizer at least partially positioned within the inner circumference of the annular center body;a pilot fuel injector positioned radially inwardly of the V-shroud flame stabilizer;a fuel prefilmer lip attached to the fuel film applicator and configured to extend downstream beyond an adjacent wall of a combustion chamber wall into a combustion chamber of the gas-turbine engine, at least a portion of the fuel prefilmer lip being the most downstream portion of the lean premix burner, an entirety of the V-shroud flame stabilizer positioned upstream of the most downstream portion of the fuel prefilmer lip;providing that a flow area of the first annular air duct downstream of the first swirler element and upstream of a free end of the fuel prefilmer lip decreases with respect to a flow area of the first swirler element to accelerate air flowing in the first annular duct, and a flow area of the second annular air duct downstream of the second swirler element and upstream of the free end of the fuel prefilmer lip decreases with respect to a flow area of the second swirler element to accelerate air flowing in the second annular duct;providing that the flow area of the second annular air duct steadily decreases past and substantially downstream of the at least one annular fuel channel to steadily accelerate the air flowing in the second annular duct past and substantially downstream of the at least one annular fuel channel;imparting the accelerated air in each of the annular ducts with swirl directions to act upon a fuel film of the fuel film applicator corresponding to a flow direction of the fuel film. 19. A method in accordance with claim 18, wherein the at least one annular fuel channel supplies fuel to the radially inner surface of the fuel film applicator and the radially outer surface of the fuel film applicator.
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