Methods and apparatus for cooling gas turbine nozzles
AssigneeGeneral Electric Company
InventorsRobert F. Manning, Randall B. Rydbeck, Christopher Roach
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Abstract
A method for fabricating a nozzle for a gas turbine engine facilitates extending a useful life of the nozzles. The nozzle includes an airfoil. The method includes forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge, forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge, and extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.
Claims20
A turbine nozzle for a gas turbine engine, said nozzle comprising an airfoil vane comprising a first wall, a second wall, and a plurality of pins extending therebetween, said first and second walls connected at a leading edge and a trailing edge, said first wall comprising a plurality of slots extending towards said trailing edge, said plurality of pins comprising at least a first row of pins having a substantially elliptical cross-sectional area, said first row of pins between said remaining plurality of pins and said first wall slots.
An airfoil for a gas turbine engine nozzle, said airfoil comprising a root, a tip, a plurality of pins, a convex sidewall and a concave sidewall connected at a trailing edge, each said sidewall extending between said root and tip, said convex sidewall defining a pressure side of said airfoil and comprising a plurality of slots extending towards said trailing edge, said plurality of pins comprising at least a first row of pins and a second row of pins, said first row of pins concentrically aligned radially, each said first row pin having a substantially elliptical cross sectional profile and tapered such that an upstream side of each said first row pin has a width that is greater than a downstream side of each said first row pin, said slots adjacent to and downstream from said first row of pins.
A method for fabricating a nozzle for a gas turbine engine, the nozzle including an airfoil, said method comprising:
- forming the airfoil to include a suction side and a pressure side connected at a leading edge and a trailing edge;
- forming a plurality of slots in the pressure side of the airfoil extending towards the trailing edge;
- and
- extending a plurality of pins arranged in rows between the airfoil suction and pressure sides, such that at each of a first row of pins has a substantially elliptical cross-sectional area, wherein the first row of pins is between the remaining rows of pins and the airfoil pressure side slots.
Dependencies are inferred from the claim text.