An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+−.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.
1. A turbine blade having a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion,
wherein the airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 wherein the X, Y and Z are distances in millimeters and the Z is a distance representing a sectional height from a root of the airfoil profile portion, the contours represented by the X and Y at each section Z being joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.
2. The turbine blade according to claim 1 , wherein the blade is a first stage turbine blade.
3. The turbine blade according to claim 1 , wherein a divisional plane of a platform of the blade is formed approximately parallel to a direction of a turbine rotational axis.
4. A turbine blade having a non-coated reference airfoil contour portion represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7,
wherein an airfoil profile portion of the turbine blade has a reference contour represented in the Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 wherein the X, Y and Z are distances in millimeters and the Z is a distance representing a sectional height from a root of the airfoil profile portion, the contours represented by the X and Y at each section Z being joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion, the X, Y and Z being scalable upwardly and downwardly as a function of the same constant or number.
5. The turbine blade according to claim 4 , wherein the blade is a first stage turbine blade.
6. The turbine blade according to claim 4 , wherein a divisional plane of a platform of the blade is formed approximately parallel to a direction of a turbine rotational axis.
7. A turbine blade having an airfoil profile portion formed such that an inter-blade passage width of a blade-root cross-section of the blade substantially monotonously decreases from a vane inlet toward a vane outlet,
wherein the airfoil profile portion has a reference contour represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 wherein the X, Y and Z are distances in millimeters and the Z is a distance representing a sectional height from a root of the airfoil profile portion,
wherein contours represented by the X and Y at each section Z are joined smoothly with one another in a blade height direction to form a shape of the airfoil profile portion, and
wherein each point forming the airfoil profile portion is within a range of ±2.0 mm in a direction normal to any airfoil profile surface location of the reference airfoil contour.
8. A turbine rotating body of a first stage turbine blade formed by using a blade which has a blade airfoil profile shape in an envelope within a range of ±2.0 mm in a direction normal to any surface location of an airfoil profile portion,
wherein the airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 wherein the X, Y and Z are distances in millimeters and the Z is a distance representing a sectional height from a root of the airfoil profile portion, the contours represented by the X and Y at each section Z being joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion, and
wherein a root radius of the airfoil profile portion is 493.9 mm, a height of the airfoil profile portion of the blade from the root radius is 77.1 mm, each of the root radius and the height of the airfoil profile portion has a tolerance of ±2.0 mm, and the turbine rotating body of the first stage blade is formed of eighty-two blades.
9. A turbine rotating body of a first stage turbine blade formed by using a blade which has a non-coated reference airfoil contour portion represented in Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7,
wherein an airfoil profile portion of the turbine blade has a reference contour represented in the Cartesian coordinates of X, Y and Z set forth in Tables 1 through 7 wherein the X, Y and Z are distances in millimeters and the Z is a distance representing a sectional height from a root of the airfoil profile portion, contours represented by the X and Y at each section Z being joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion, the X, Y and Z being scalable upwardly and downwardly as a function of the same constant or number, and
wherein a root radius of the airfoil profile portion is 493.9 mm, a height of the airfoil profile portion of the blade from the root radius is 77.1 mm, each of the root radius and the height of the airfoil profile portion has a tolerance of ±2.0 mm, and the turbine rotating body of the first stage blade is formed of eighty-two blades.