Compressor turbine vane airfoil profile
AssigneePratt & Whitney Canada Corp.
InventorConstantinos Ravanis
Life of this patent
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Abstract
A compressor turbine includes a vane having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
Claims12
A compressor turbine vane for a gas turbine engine comprising an airfoil having a portion defined by a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 9 set forth in Table 2, wherein a point of origin of orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y values are coordinate values defining the profile at each distance Z.
A compressor turbine vane for a gas turbine engine, the compressor turbine vane having a cold coated intermediate airfoil portion defined by a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 9 set forth in Table 2, wherein a point of origin of orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y values are coordinate values defining the profile at each distance Z.
A compressor turbine stator assembly for a gas turbine engine comprising a plurality of vanes, each vanes including an airfoil having an intermediate portion defined by a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 9 set forth in Table 2, wherein a point of origin of orthogonally related axes X, Y and Z is located at an intersection of a centerline of the gas turbine engine and a stacking line of the turbine vane, the Z values are radial distances measured along the stacking line, the X and Y values are coordinate values defining the profile at each distance Z.
A compressor turbine vane comprising at least one airfoil having a surface defined by coordinate values given in Table 2, the at least one airfoil extending between platforms defined by coordinate values given in Table 1, wherein a fillet radius is applied around the at least one airfoil between the at least one airfoil and the platforms.
Dependencies are inferred from the claim text.