LP turbine blade airfoil profile
First Claim
1. A turbine blade 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 9 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 blade, 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.
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Abstract
A single stage low pressure turbine blade 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.
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Citations
15 Claims
- 1. A turbine blade 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 9 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 blade, 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.
- 8. A turbine blade for a gas turbine engine, the turbine blade 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 9 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 blade in the engine, the Z values are radial distances measured along the stacking line of the airfoil, 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.
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14. A turbine rotor for a gas turbine engine, comprising a plurality of blades extending from a rotor disc, each blade 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 9 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 blades, 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.
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15. A low pressure blade adapted to be mounted in a gaspath comprising a stacking line, the stacking line defining the position of the blade in the gaspath, an airfoil having a surface lying substantially on the points of Table 2, the airfoil extending between a platform and a shrouded tip, the platform being generally defined by an inner gaspath wall of Table 1, and wherein the shrouded tip is defined as a function of an outer gaspath wall of Table 1 in the vicinity of said stacking line.
Specification