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US 8,938,968 B2Granted
Burner of a gas turbine
AssigneeALSTOM Technology Ltd
InventorsJohannes Buss, Andrea Ciani, Michael Düsing, Adnan Eroglu
Life of this patent
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Abstract
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.
Claims24
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;
- and
- wherein 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.
3 more elements
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;
- and
- wherein 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.
3 more elements
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;
- and
- wherein 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.
4 more elements
Dependencies are inferred from the claim text.