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AssigneeGeneral Electric Company
InventorsWei Chen, Stephen Robert Thomas, Geoffrey David Myers, Vijay Kumar Turaga
Estimating the term…
A method for assembling a combustor assembly is provided. The method includes providing at least one sleeve having a plurality of inlets, and coupling at least one airfoil to at least one of the plurality of inlets defined in the at least one sleeve. The airfoil includes a pair of opposing sidewalls coupled together at a leading edge and at a trailing edge and at least one channel is formed between the airfoil sidewalls for channeling cooling air. The cooling air is directed to flow substantially perpendicularly to a direction of air flowing around the airfoil in a portion of the combustor assembly that is to be cooled. The method also includes coupling the at least one sleeve around the portion of the combustor assembly to be cooled. Also provided are a sleeve and an airfoil for use in a combustor assembly.
A method for assembling a combustor assembly, said method comprises:
A sleeve for use in a combustor assembly, said sleeve comprising a plurality of airfoil projections defined in said sleeve, each airfoil projection configured to channel cooling air into a cooling passage of said combustor assembly, each airfoil projection comprising:
An airfoil for channeling cooling air into a cooling passage of a combustor assembly, said airfoil comprising:
A template for channeling cooling air into a cooling passage of a combustor assembly, said template comprising an outer surface, an inner surface, and a plurality of openings extending therebetween, said outer surface having a contour that substantially matches a contour of a portion of a flow sleeve, said template removably coupled to said flow sleeve for directing the cooling air through said plurality of openings into the cooling passage.
Dependencies are inferred from the claim text.