The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for intr
The disclosure relates to a burner for a combustion chamber of a gas turbine, with an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner. The at least one nozzle has its outlet orifice at or in a trailing edge of the streamlined body, and with reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions.
대표청구항▼
1. A burner for a combustion chamber of a gas turbine, comprising: an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at l
1. A burner for a combustion chamber of a gas turbine, comprising: an injection device for the introduction of at least one gaseous and/or liquid fuel into the burner, wherein the injection device has at least one body which is arranged in the burner with at least one nozzle for introducing the at least one fuel into the burner, the at least one body being configured as a streamlined body which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the burner, the at least one nozzle having its outlet orifice at or in a trailing edge of the streamlined body; andwith reference to a central plane of the streamlined body, the trailing edge is provided with at least two lobes extending in opposite transverse directions. 2. The burner according to claim 1, wherein the trailing edge is provided with at least 3, lobes sequentially arranged adjacent one another along the trailing edge and alternatingly lobing in the two opposite transverse directions. 3. The burner according to claim 1, wherein the streamlined body comprises: an essentially straight leading edge. 4. The burner according to claim 1, wherein the streamlined body, in its straight upstream portion with respect to the main flow direction, has a maximum width (W) downstream of which the width essentially continuously diminishes towards the trailing edge, and wherein a height (h), defined as a distance in the transverse direction of apexes of adjacent lobes, is at least half of the maximum width (W). 5. The burner according to claim 4, wherein the height (h) is at least as large as the maximum width (W), and not more than three times as large as the maximum width (W). 6. The burner according to claim 1, wherein lobe periodicity (λ) is in the range of 20-100 mm. 7. The burner according to claim 1, wherein a transverse displacement of the streamlined body forming the lobes is only at most in the downstream two thirds of the length (l) of the streamlined body. 8. The burner according to claim 1, comprising: at least two fuel nozzles located at the trailing edge and distributed along the trailing edge, and wherein the fuel nozzles are located essentially on the central plane of the streamlined body. 9. The burner according to claim 1, comprising: at least two fuel nozzles located at the trailing edge and distributed along the trailing edge, the fuel nozzles being located essentially at turning points between two lobes, wherein at each turning point along the trailing edge there is a fuel nozzle. 10. The burner according to claim 1, comprising: downstream of said body, a mixing zone wherein at and/or downstream of said body the cross-section of said mixing zone is reduced by at least 10% compared to the flow cross-section upstream of said body. 11. The burner according to claim 1, wherein at least one nozzle injects fuel and/or carrier gas parallel to the main flow direction. 12. The burner according to claim 1, wherein at least one nozzle injects fuel and/or carrier gas at an inclination angle between 0-30° with respect to the main flow direction. 13. The burner according to claim 1, wherein the streamlined body extends across an entire flow cross section between opposite top and bottom walls of the burner, the burner comprising: at least two streamlined bodies, the longitudinal axes of which are arranged essentially parallel to each other, and/or wherein the burner is bordered by burner sidewalls arranged essentially parallel to the longitudinal axes of the streamlined bodies, wherein the sidewalls have an undulated surface facing the flow path, and wherein an undulation of the sidewalls has essentially a same periodicity and/or is arranged in phase with lobes of the streamlined bodies and/or have essentially an undulation height which equals a height of the lobes of the streamlined bodies. 14. The burner according to claim 1, wherein the body is provided with cooling elements, wherein these cooling elements are for internal circulation of cooling medium along the sidewalls of the body and/or film cooling holes, located near the trailing edge, and wherein the cooling elements are configured to receive air from a carrier gas feed used for the fuel injection. 15. The burner according to claim 1, wherein the fuel is injected from the nozzle together with a carrier gas stream, and wherein the carrier gas air is low pressure air with a pressure in a range of 10-25 bar. 16. The burner as claimed in claim 1, wherein the streamlined body has a cross-sectional profile which, in a portion where it is not lobed, is mirror symmetric with respect to a central plane of the body. 17. The burner according to claim 1, in combination with a combustion chamber configured for combustion under high reactivity conditions, and/or for combustion at high burner inlet temperatures and/or for combustion of MBtu fuel and/or for combustion of hydrogen rich fuel. 18. The burner according to claim 1, wherein lobe periodicity (λ) is in a range of 30-60 mm. 19. The burner according to claim 1, wherein a transverse displacement of the streamlined body forming the lobes is only at most in a length (l) of the streamlined body. 20. The burner according to claim 1, comprising: at least two fuel nozzles located at the trailing edge and distributed along the trailing edge, and wherein at each position, where the lobed trailing edge crosses the central plane, there is a fuel nozzle.
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이 특허에 인용된 특허 (31)
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