A single stage low pressure turbine vane includes an airfoil having 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 co
A single stage low pressure turbine vane includes an airfoil having 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.
대표청구항▼
The invention claimed is: 1. A turbine vane for a gas turbine engine comprising an airfoil having an intermediate portion defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 8 set forth in Table 2, wherein the point of origin of
The invention claimed is: 1. A turbine vane for a gas turbine engine comprising an airfoil having an intermediate portion defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 8 set forth in Table 2, wherein the point of origin of the 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 are coordinate values defining the profile at each distance Z. 2. The turbine vane as defined in claim 1 forming part of a low pressure turbine stage of the gas turbine engine. 3. The turbine vane as defined in claim 2, wherein the vane forms part of a single stage low pressure turbine. 4. The turbine vane as defined in claim 1, wherein the X and Y values are scalable as a function of the same constant or number. 5. The turbine vane as defined in claim 1, wherein the X and Y coordinate values have a manufacturing tolerance of ±0.003. 6. The turbine vane as defined in claim 5, wherein the nominal profile defining the intermediate portion is for an uncoated airfoil. 7. The turbine vane as defined in claim 1, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the intermediate portion. 8. A turbine vane for a gas turbine engine having an intermediate airfoil portion at least partly defined by a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 8 set forth in Table 2, wherein the point of origin of the 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 are coordinate values defining the profile at each distance Z, and wherein the X and Y values are scalable as a function of the same constant or number. 9. The airfoil as defined in claim 8 forming part of a vane of a low pressure turbine stage of the gas turbine engine. 10. The turbine vane as defined in claim 9, wherein the vane is part of a single stage low pressure turbine. 11. The turbine vane as defined in claim 8, wherein the X and Y coordinate values have a manufacturing tolerance ±0.003 inches. 12. The turbine vane as defined in claim 11, wherein the nominal profile defining the intermediate portion is for an uncoated airfoil. 13. The turbine vane as defined in claim 8, wherein X and Y values define a set of points for each Z value which when connected by smooth continuing arcs define an airfoil profile section, the profile sections at the Z distances being joined smoothly with one another to form an airfoil shape of the intermediate portion. 14. A 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 substantially in accordance with Cartesian coordinate values of X, Y, and Z of Sections 3 to 8 set forth in Table 2, wherein the point of origin of the 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 are coordinate values defining the profile at each distance Z. 15. A low pressure turbine vane comprising at least one airfoil having a surface lying substantially on the points of Table 2, the airfoil extending between platforms defined generally by Table 1, wherein a fillet radius is applied around the airfoil between the airfoil and platforms, and wherein the values of Table 2 are subject to relevant tolerance.
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