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AssigneeGeneral Electric Company
InventorsJohn Heyward, Gregg Ford, Christen Vonderau, Elizabeth Ervin
Estimating the term…
A method of assembling a gas turbine engine includes coupling at least one turbine nozzle segment within the gas turbine engine, each turbine nozzle segment includes at least one airfoil vane extending between an inner band and an outer band, wherein the airfoil vane includes a leading edge and a trailing edge, and wherein the outer band includes a front face, a rear face, and an inner surface extending therebetween. The method also includes coupling at least one turbine shroud segment downstream from the at least one turbine nozzle segment, wherein each turbine shroud segment includes a front face, a rear face, and an inner surface extending therebetween, and coupling a cooling fluid source to each turbine nozzle segment such that cooling fluid may be channeled to each turbine nozzle inner surface proximate to one of the leading edge and the trailing edge of each airfoil vane, such that cooling fluid channeled to each turbine nozzle outer band rear face is directed towards the front face of at least one turbine shroud segment.
A method of assembling a gas turbine engine, said method comprising:
A nozzle assembly comprising:
A gas turbine engine comprising a nozzle assembly comprising an inner band, an outer band, and at least one airfoil vane extending between said inner band and said outer band, each said at least one airfoil vane comprising a first sidewall and a second sidewall connected at a leading edge and a trailing edge, said outer band comprising a front face, a rear face, and an inner surface extending therebetween, said outer band rear face comprising a plurality of cooling holes configured to direct cooling fluid onto at least one turbine shroud segment, said inner surface comprising a plurality of cooling holes configured to facilitate cooling said inner surface.
Dependencies are inferred from the claim text.