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Nozzle cavity impingement/area reduction insert

United States Patent

October 22, 2002
View the Complete Patent at the US Patent & Trademark Office
A turbine vane segment is provided that has inner and outer walls spaced from one another, a vane extending between the inner and outer walls and having leading and trailing edges and pressure and suction sides, the vane including discrete leading edge, intermediate, aft and trailing edge cavities between the leading and trailing edges and extending lengthwise of the vane for flowing a cooling medium; and an insert sleeve within at least one of the cavities and spaced from interior wall surfaces thereof. The insert sleeve has an inlet for flowing the cooling medium into the insert sleeve and has impingement holes defined in first and second walls thereof that respectively face the pressure and suction sides of the vane. The impingement holes of at least one of those first and second walls are defined along substantially only a first, upstream portion thereof, whereby the cooling flow is predominantly impingement cooling along a first region of the insert wall corresponding to the first, upstream portion and the cooling flow is predominantly convective cooling along a second region corresponding to a second, downstream portion of the at least one wall of the insert sleeve.
Yu; Yufeng Phillip (Simpsonville, SC), Itzel; Gary Michael (Simpsonville, SC), Osgood; Sarah Jane (East Thetford, VT)
General Electric Company (Schenectady, NY)
09/ 571,835
May 16, 2000
This invention was made with Government support under Government contract No. DE-FC21-95-MC31176 awarded by the Department of Energy. The Government has certain rights in this invention.