TURBINE BLADE

• US 20080240924A1
• Filed: 01/23/2008
• Published: 10/02/2008
• Est. Priority Date: 02/28/2007
• Status: Active Grant

• Current Assignee: Mitsubishi Power Limited (Mitsubishi Heavy Industries, Ltd.)
• Original Assignee: Hitachi, Ltd.
• Inventors: Kizuka, Nobuaki, Murata, Hidetaro, Kuroki, Hidetoshi, Nanataki, Kenji
• Granted Patent: US 8,277,192 B2
• Time in Patent Office: Days
• US Class Current: 416/223R
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F05D 2220/3212 the first stage of a turbine
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: F05D 2250/74 given by a set or table of xyz-coordinates
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vain 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.

Claims

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 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 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 vain inlet toward a vain 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 eight-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 eight-two blades.