An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle
An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.
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1. Burner of a gas turbine, comprising: a tubular body with an inlet for entrance of a gas flow;at least one side vortex generator located downstream of the inlet;a lance projecting into the tubular body and having a terminal portion extending parallel to a longitudinal axis of the burner which is p
1. Burner of a gas turbine, comprising: a tubular body with an inlet for entrance of a gas flow;at least one side vortex generator located downstream of the inlet;a lance projecting into the tubular body and having a terminal portion extending parallel to a longitudinal axis of the burner which is provided with at least one nozzle group for injecting fuel into the tubular body, the at least one nozzle group laying in an injection plane perpendicular to an axis of a terminal portion of the lance downstream of the lance;an outlet downstream of said lance configured to supply a mixture of gas and fuel formed in the tubular body to a combustion chamber, wherein a ratio x/L between an axial distance x between a trailing edge of the at least one side vortex generator and the injection plane, and a length L of the tubular body is less than approximately 0.1052; andwherein a trailing edge of an intermediate portion of the lance, which is inside the tubular body and extends perpendicularly to the longitudinal axis of the burner, is downstream of tips of all the at least one side vortex generators, wherein each of the tips is a downstream edge of a corresponding side vortex generator of the at least one side vortex generators. 2. Burner as claimed in claim 1, wherein said ratio x/L is between −0.0276 and 0.1052. 3. Burner as claimed in claim 1, comprising: two side vortex generators having trailing edges which lay in a plane perpendicular to the longitudinal axis of the burner. 4. Burner as claimed in claim 1, wherein said lance comprises: at least a first tubular element arranged to carry a fuel; andan outer tubular element defining with said first tubular element an annular conduit arranged to carry air, said first tubular element being provided with a first nozzle of said nozzle group and said outer tubular element being provided with an outer nozzle of said nozzle group, wherein each outer nozzle is provided with a sleeve protruding outwards. 5. Burner according to claim 4, wherein a length of each sleeve of the outer nozzles from an external surface of the outer tubular element to a free edge of the tubular element is equal or less than 10 millimeters. 6. Burner according to claim 4, wherein a length of each sleeve of the outer nozzles from an external surface of the outer tubular element to a free edge of the tubular element is within a range of than 1-10 millimeters. 7. Burner according to claim 4, wherein an inner surface of the sleeve of each outer nozzle is conical in shape. 8. Burner according to claim 7, wherein a ratio between an outlet inner diameter and an inlet inner diameter of the sleeve is between 85-91%. 9. Burner according to claim 7, wherein a ratio between an outlet inner diameter and an inlet inner diameter of the sleeve is greater than 50%. 10. Burner according to any of claim 4, wherein an inlet edge of the sleeve of each outer nozzle is rounded at the outer tubular element. 11. Burner according to claim 4, wherein the first tubular element encloses a second tubular element to define an annular conduit, said second tubular element having a closed end with a second nozzle of each nozzle group being coaxial with said first nozzle and said outer nozzle and said sleeve of each outer nozzle. 12. Burner according to claim 11, wherein said first nozzle and said second nozzle of each group of nozzles are provided with cylindrical outwardly protruding portions having aligned free edges. 13. Burner according to claim 12, wherein an outer wall of a cylindrical portion of each first nozzle is conical in shape. 14. Burner according to claim 1, configured as a second burner of a sequential combustion machine. 15. Burner as claimed in claim 1, wherein said ratio x/L is between 0.000 and 0.1052. 16. Burner as claimed in claim 1, wherein the burner has a ratio z/d, where z is an axial distance from the lance stem trailing edge to the injection plane and d is a diameter of the terminal portion of the lance, and wherein the ratio z/d is between 0.17 and 1.35. 17. Burner as claimed in claim 16, wherein the ratio z/d is between 0.420 and 0.854. 18. Burner of a gas turbine, comprising: a tubular body with an inlet for entrance of a gas flow;at least one side vortex generator located downstream of the inlet;a lance projecting into the tubular body and having a terminal portion extending parallel to a longitudinal axis of the burner which is provided with at least one nozzle group for injecting fuel into the tubular body, the at least one nozzle group laying in an injection plane perpendicular to an axis of a terminal portion of the lance downstream of the lance;an outlet downstream of said lance, wherein a ratio x/L between an axial distance x between a trailing edge of the at least one side vortex generator and the injection plane, and a length L of the tubular body is less than approximately 0.1052; andwherein the cylindrical outwardly protruding portions of the first and second nozzles of each group are housed within said outer tubular element and outside the corresponding sleeve of the outer tubular element of the group. 19. Burner as claimed in claim 18, wherein said lance comprises: at least a first tubular element arranged to carry a fuel; andan outer tubular element defining with said first tubular element an annular conduit arranged to carry air, said first tubular element being provided with a first nozzle of said nozzle group and said outer tubular element being provided with an outer nozzle of said nozzle group, wherein each outer nozzle is provided with a sleeve protruding outwards, wherein an inner surface of the sleeve of each outer nozzle is conical in shape. 20. Burner according to claim 19, wherein a ratio between an outlet inner diameter and an inlet inner diameter of the sleeve is greater than 50%. 21. Burner according to claim 18, wherein said lance comprises: at least a first tubular element arranged to carry a fuel, wherein the first tubular element encloses a second tubular element to define an annular conduit, said second tubular element having a closed end with a second nozzle of each nozzle group being coaxial with said first nozzle and said outer nozzle and said sleeve of each outer nozzle, wherein said first nozzle and said second nozzle of each group of nozzles are provided with cylindrical outwardly protruding portions having aligned free edges; andan outer tubular element defining with said first tubular element an annular conduit arranged to carry air, said first tubular element being provided with a first nozzle of said nozzle group and said outer tubular element being provided with an outer nozzle of said nozzle group, wherein each outer nozzle is provided with a sleeve protruding outwards. 22. Burner according to claim 18, wherein the terminal portion of the lance extends from an intermediate portion which is inside said tubular body and connects the terminal portion to a fuel supply portion of the lance which is outside the tubular body, wherein the terminal portion has four nozzle groups which are placed in said injection plane, said four nozzle groups having two nozzle and have axes differently angled with respect to a circumferential transversal plane, and the nozzle groups are symmetrically placed with respect to a longitudinal plane which is perpendicular to the circumferential transversal plane; and wherein an angle of a first axis towards the intermediate portion of the lance is smaller than an angle of a second axis opposite the intermediate portion of the lance. 23. Burner of a gas turbine, comprising: a tubular body with an inlet for entrance of a gas flow;at least one side vortex generator located downstream of the inlet;a lance projecting into the tubular body and having a terminal portion extending parallel to a longitudinal axis of the burner which is provided with at least one nozzle group for injecting fuel into the tubular body, the at least one nozzle group laying in an injection plane perpendicular to an axis of a terminal portion of the lance downstream of the lance;an outlet downstream of said lance configured to supply a mixture of gas and fuel formed in the tubular body to a combustion chamber, wherein a ratio x/L between an axial distance x between a trailing edge of the at least one side vortex generator and the injection plane, and a length L of the tubular body is less than approximately 0.1052;wherein the terminal portion of the lance extends from an intermediate portion which is inside said tubular body and connects the terminal portion to a fuel supply portion of the lance which is outside the tubular body, wherein the terminal portion has four nozzle groups which are placed in said injection plane, said four nozzle groups having two nozzle axes differently angled with respect to a circumferential transversal plane, and the nozzle groups are symmetrically placed with respect to a longitudinal plane which is perpendicular to the circumferential transversal plane; andwherein the intermediate portion extends inside the tubular body perpendicularly to the axis of the burner and extends from the terminal portion to the tubular body, and wherein an angle of a first axis of the two nozzle axes towards a direction of an extension of the intermediate portion from the longitudinal axis of the burner of the lance is smaller than an angle of a second axis of the two nozzle axes opposite the direction of the extension of the immediate portion from the longitudinal axis of the burner. 24. Burner according to claim 23, wherein the angles between the axes of the nozzle groups towards the intermediate portion of the lance are smaller than 25° and greater than 15°.
Eroglu Adnan (Untersiggenthal CHX) Joos Franz (Weilheim-Bannholz DEX) Novacek Peter (Gebenstorf CHX) Senior Peter (Mellingen CHX), Fuel lance for liquid and/or gaseous fuels and method for operation thereof.
Matt Bernhard (Rheinheim DEX) Woringer Theo (Zurich CHX) Zouzoulas Gerassime (Dietikon CHX), Ring combustion chamber with ring burner for gas turbines.
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