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US 2007/0183898 A1Published application
Airfoil for a second stage nozzle guide vane
AssigneeRolls-Royce Power Engineering PLC
InventorsAndrew Hurst, Simon Harding
Life of this patent
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Abstract
The present invention provides an airfoil a second stage nozzle guide vane having an external surface with first and second sides. The external surface extends spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge of the airfoil. The external surface includes a contour substantially defined by Table 1 as listed in the specification.
Claims22
An airfoil comprising:
- an external surface having first and second sides, the external surface extending spanwise between a hub and a tip and streamwise between a leading edge and a trailing edge;
- and
- the external surface having a contour substantially defined by Table 1 as listed in the specification.
A turbine nozzle guide vane assembly for a gas turbine engine comprising:
- an inner shroud having an upper surface and a lower surface, the upper surface of the inner shroud partially defining an inner flow path wall;
- an airfoil extending radially outward from the upper surface of the inner shroud relative to an axis of rotation of the gas turbine engine, the airfoil having first and second three-dimensional external surfaces extending between a hub and a tip in a spanwise direction and between a leading edge and a trailing edge in a streamwise direction;
- and
- a Cartesian coordinate array having X,Y and Z axis coordinates listed in Table 1 of the specification defining the first and second external surfaces of the airfoil, wherein the Z axis generally extends radially outward from at least one of the upper surface of the inner shroud or a longitudinal axis of the engine, the X axis generally extends normal to the Z axis in the streamwise direction, and the Y axis generally extends normal to both the X axis and the Z axis in a lateral direction.
1 more element
A method of forming an airfoil for a turbine nozzle guide vane comprising:
- forming a contoured three-dimensional external surface of an airfoil defined by Cartesian (X, Y and Z) coordinates listed in the specification as Table 1, wherein the Z axis coordinates are generally measured from an inner shroud or an engine centerline axis, the X axis coordinates are generally measured normal to the Z axis in a streamwise direction, and the Y axis coordinates are generally measured normal to the Z axis and normal to the X axis.
Dependencies are inferred from the claim text.