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US 6,183,192 B2Granted
Durable turbine nozzle
AssigneeGeneral Electric Company
InventorsJudd D. Tressler, Glenn H. Nichols
Life of this patent
Estimating the term…
Abstract
A turbine nozzle includes a plurality of vanes joined at opposite ends to outer and inner bands. The inner band has a forward hook which is segmented to reduce thermal mismatch. And, in additional embodiments the vane includes an impingement baffle having preferential cooling.
Claims19
A turbine nozzle for a gas turbine engine, comprising:
- a plurality of vanes integrally joined at opposite ends to outer and inner bands;
- and
- said inner band having a forward hook inboard of a leading edge thereof, said hook including an inner lip and a plurality of circumferentially spaced apart outer lips spaced radially from said inner lip to define a retention slot therein.
A turbine nozzle for a gas turbine engine, comprising:
- a plurality of vanes integrally joined at opposite ends to outer and inner bands;
- said inner band having a forward hook inboard of a leading edge thereof, said hook including an inner lip and a plurality of circumferentially spaced apart outer lips spaced radially from said inner lip to define a retention slot therein;
- said vanes have generally concave, pressure sides and opposite, generally convex, suction sides extending between leading and trailing edges thereof and between said outer and inner bands along respective spans of said vanes;
- and
- said vanes include cavities each having an impingement baffle, and said baffles have a plurality of spaced apart impingement holes extending therethrough and arranged in different patterns facing an inner surface of said cavities for preferentially channeling cooling air in impingement jets toward midspan of said vane.
2 more elements
Dependencies are inferred from the claim text.