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AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Eric Alan Estill, James Harvey Laflen, Katherine Jaynetorrence Andersen
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A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.
A method for cooling a shroud segment of a gas turbine engine, said method comprising:
A turbine nozzle and shroud assembly for a gas turbine engine, said turbine nozzle and shroud assembly comprising:
A cooling system for a gas turbine engine that includes a shroud segment having a leading edge and an inner surface that is substantially perpendicular to the leading edge, and a turbine nozzle that is upstream from the shroud segment and that includes an outer band having an aft edge, said cooling system comprising:
Dependencies are inferred from the claim text.