Burner assembly for a burner of a gas turbine
AssigneeGeneral Electric Technology GmbH
InventorsJost Imfeld, Alen Markovic, Igor Bizic, Vedran Druzak, Giancarlo Ruggieri, Jeffrey Alan De Jonge
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Abstract
A burner assembly of a gas turbine comprising: a tubular body defining the flow path for the hot gas of the combustion during the turbine operation; an aperture for a fuel lance; a wearing ring of a sacrificial material configured to correspond to the edge of the aperture; a contacting leg extending from the wearing ring on the tubular body; a pre-tension system configured to contact the contacting leg in order to provide a pre-tension force on the ring.
Claims12
A burner assembly of a gas turbine comprising:
- a tubular body defining a flow path for a hot gas of combustion during a turbine operation;
- an aperture for a fuel lance, said aperture defined by an edge, said edge extending through a top surface of said tubular body and including a protruding portion extending transversely outward from said top surface of said tubular body;
- a wearing ring fabricated from a sacrificial material, said wearing ring including i) a rim which rests on said protruded portion of said edge and ii) a section extending from said rim into said aperture and shaped to substantially correspond to said edge of said aperture;
- at least one contacting leg extending from said rim along said tubular body;
- and
- a pre-tension system configured to contact said contacting leg to induce a pre-tension force on said ring against said tubular body;
- wherein said at least one contacting leg comprises a first contacting leg and a second contacting leg, said first and second contacting legs extending in opposite directions outwardly from said rim along said tubular body, such that each first and second contacting legs are each substantially parallel to the hot gas flow path, said pre-tension system further configured to contact said first and second contacting legs.
A method for installing a fuel lance in a burner assembly of a gas turbine, said method comprising:
- forming a tubular body that at least partially defines a hot gas flow path within the turbine, wherein the tubular body includes an aperture defined by an edge, said edge extending through a top surface of said tubular body and including a protruding portion extending transversely outward from said top surface of said tubular body;
- positioning a wearing ring, including a rim and a section extending from the rim, within the aperture, such that the rim of the wearing ring rests on said protruded portion of said edge and the section extends into the aperture to substantially correspond to the edge of said aperture, the wearing ring fabricated from a sacrificial material;
- positioning a pre-tension system on the tubular body such that the pre-tension system contacts each of a pair of contacting legs extending in opposite directions from the rim of the wearing ring along the tubular body to induce a pre-tension force on the wearing ring, wherein the pair of contacting legs are oriented substantially parallel to the hot gas flow path, and
- inserting the fuel lance within the aperture such that the lance contacts the wearing ring and is positioned with the hot gas flow path.
Dependencies are inferred from the claim text.