Curvature steam turbine vane airfoil

• US 5,292,230 A
• Filed: 12/16/1992
• Issued: 03/08/1994
• Est. Priority Date: 12/16/1992
• Status: Expired due to Fees

• Current Assignee: Westinghouse Electric Company LLC (Brookfield Asset Management Incorporated)
• Original Assignee: Westinghouse Electric Company LLC (Brookfield Asset Management Incorporated)
• Inventors: Brown, Wilmott G.
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): Sgantzos, Mark
• Application Number:
  US07/991,799
• Time in Patent Office: 447 Days
• Field of Search: 416/223 A, 416/DIG. 2, 415/191, 415/192, 415/208.1, 415/208.2
• US Class Current: 416/223.00A
• 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 2230/25 by forging
• CPC Class Codes: F05D 2240/301 Cross-sectional characteristics
• CPC Class Codes: Y10S 416/02 Formulas of curves

Abstract

A high performance steam turbine vane having a novel airfoil shape. The pressure surface of the airfoil has a substantially straight region proximate the trailing edge that provides the airfoil with adequate thickness to prevent distortion during forging. The novel shape on the suction surface is such that a first region of the suction surface downstream of the gauging point is essentially straight. Traveling in the upstream direction, the first region is followed by a second region that has a large amount of curvature. The second region is followed by a third region that has a lower curvature than the second region. The third region is followed by a fourth region of constantly increasing curvature that increases to a curvature greater than the curvature of the second region. The fourth region is followed by a fifth region, ending at the leading edge, of essentially constant large curvature that includes the maximum curvature throughout the suction surface.

Claims

1. A steam turbine comprising:

a) a stationary cylinder for containing a steam flow, and a rotor enclosed by said cylinder;

b) a row of blades attached to the periphery of said rotor; and

c) a row of vanes supported on said cylinder and disposed upstream of said row of blades, each of said vanes having an airfoil portion having leading and trailing edges and forming a suction surface and a pressure surface between said leading and trailing edges, said airfoil portion having a width in the axial direction and having a cross-sectional shape that, in conjunction with said trailing edge of an adjacent one of said vanes in said row, defines a gauging point on said suction surface, said pressure surface having a cross-sectional shape in at least one radial location along said airfoil that has a substantially flat portion that extends upstream from said trailing edge by a distance of at least approximately 40% of said airfoil axial width, said suction surface having a cross-sectional shape in said at least one radial location along said airfoil that has;

(i) a substantially flat first portion forming all of said suction surface that is downstream of said gauging point,

(ii) a curved section portion upstream of said gauging point, said second portion having a first curvature,

(iii) a second curvature along a third portion upstream of said second portion, said second curvature being less than said first curvature, and

(iv) a third curvature along a fourth portion upstream of said third portion and ending at said leading edge, said third curvature being greater than said second curvature.

2. The steam turbine according to claim 1, wherein said third curvature is the maximum curvature on said suction surface.

3. The steam turbine according to claim 1, wherein said first portion of said suction surface comprises the downstream-most approximately 30% of said axial width of said airfoil.

4. The steam turbine according to claim 1, wherein said fourth portion of said suction surface has an upstream segment and a downstream segment, said downstream segment having a curvature that constantly increases as said downstream segment progresses in the upstream direction toward said upstream segment, and said upstream segment having a curvature that is substantially constant throughout said upstream segment.

5. The steam turbine according to claim 1, wherein said first portion of said suction surface comprises a region that is approximately the downstream-most 30% of said airfoil axial width, said second portion of said suction surface comprises a region that is approximately 5% of said airfoil axial width and is immediately upstream from said first portion, said third portion of said suction surface comprises a region that is approximately 5% of said airfoil axial width and is immediately upstream from said second portion, and said fourth portion comprises a region of approximately 60% of said airfoil axial width and that is immediately upstream of said third portion.

6. The steam turbine according to claim 1, wherein said airfoil suction surface shape is defined by coordinate locations expressed as distances from said trailing edge in the axial and transverse directions, respectively, as follows:

space="preserve" listing-type="tabular">______________________________________ Location No. Coordinates ______________________________________ 1 (0.00, 1.30) 2 (0.91, 1.93) 3 (1.83, 3.71) 4 (2.74, 5.51) 5 (3.66, 7.32) 6 (4.57, 9.12) 7 (5.03, 9.96) 8 (5.49, 10.64) 9 (5.94, 11.28) 10 (6.40, 11.84) 11 (7.32, 12.83) 12 (8.20, 13.64) 13 (9.14, 14.25) 14 (10.06, 14.68) 15 (10.97, 14.94) 16 (11.86, 15.06) 17 (12.78, 15.04) 18 (13.69, 14.88) 19 (14.61, 14.61) 20 (15.52, 14.12) 21 (15.98, 13.82) ______________________________________

7. The steam turbine according to claim 6, wherein said airfoil suction surface shape has a curvature, expressed as cm^-1, at said locations, as follows:

space="preserve" listing-type="tabular">______________________________________ Location No. Curvature ______________________________________ 1 0.0 2 0.0 3 0.0 4 0.0 5 0.0 6 0.0 7 0.100 8 0.073 9 0.048 10 0.056 11 0.082 12 0.120 13 0.147 14 0.160 15 0.162 16 0.161 17 0.163 18 0.160 19 0.157 20 0.150 21 0.141 ______________________________________

8. A row of stationary vanes for a steam turbine, each of said vanes comprising an airfoil portion having leading and trailing edges and forming a suction surface and a pressure surface between said leading and trailing edges, said airfoil portion having a cross-sectional shape that, in conjunction with said trailing edge of an adjacent one of said vanes in said row, defines a gauging point on said suction side, said pressure surface having a cross-sectional shape in at least one radial location along said airfoil that has a substantially flat region proximate said trailing edge and a curved region upstream of said flat region, said flat region extending tangentially from said curved region, said suction surface having a cross-sectional shape in said at least one radial location along said airfoil that has:

a) a substantially flat first portion forming all of said suction surface that is downstream of said gauging point;

b) a first curvature along a second portion of said suction side upstream of said gauging point;

c) a second curvature along a third portion of said suction surface upstream of said second portion, said second curvature being less than said first curvature; and

d) a third curvature along a fourth portion of said suction surface upstream of said third portion, said third curvature being greater than said second curvature.

9. The steam turbine vane according to claim 8, wherein said third curvature is greater than said first curvature.

10. The steam turbine vane according to claim 8, wherein said airfoil suction surface shape is defined by coordinate locations expressed as distances from said trailing edge in the axial and transverse directions, respectively, as follows:

space="preserve" listing-type="tabular">______________________________________ Location No. Coordinates ______________________________________ 1 (0.00, 1.30) 2 (0.91, 1.93) 3 (1.83, 3.71) 4 (2.74, 5.51) 5 (3.66, 7.32) 6 (4.57, 9.12) 7 (5.03, 9.96) 8 (5.49, 10.64) 9 (5.94, 11.28) 10 (6.40, 11.84) 11 (7.32, 12.83) 12 (8.20, 13.64) 13 (9.14, 14.25) 14 (10.06, 14.68) 15 (10.97, 14.94) 16 (11.86, 15.06) 17 (12.78, 15.04) 18 (13.69, 14.88) 19 (14.61, 14.61) 20 (15.52, 14.12) 21 (15.98, 13.82) ______________________________________

11. The steam turbine vane according to claim 10, wherein said airfoil pressure surface shape is defined by coordinate locations expressed as distances from said trailing edge in the axial and transverse directions, respectively, as follows:

space="preserve" listing-type="tabular">______________________________________ Location No. Coordinates ______________________________________ 22 (0.18, 0.05) 23 (1.07, 1.60) 24 (1.96, 2.92) 25 (2.84, 4.17) 26 (3.73, 5.36) 27 (4.62, 6.50) 28 (5.08, 7.06) 29 (5.54, 7.57) 30 (5.97, 8.08) 31 (6.43, 8.59) 32 (7.32, 9.47) 33 (8.20, 10.26) 34 (9.09, 10.95) 35 (9.98, 11.53) 36 (10.87, 12.01) 37 (11.78, 12.40) 38 (12.67, 12.73) 39 (13.56, 12.98) 40 (14.45, 13.16) 41 (15.34, 13.23) 42 (15.80, 13.26) ______________________________________

12. A stationary vane for a steam turbine, comprising an airfoil portion having leading and trailing edges and forming a suction surface and a pressure surface between said leading and trailing edges, said airfoil having a width in the axial direction, and said suction surface having a cross-sectional shape in at least one radial location along said airfoil that has:

a) a substantially downstream-most first portion that is substantially flat;

b) a second portion immediately upstream of said first portion having a maximum curvature in the range of approximately 0.08 to 0.10 cm^-1 ;

c) a third portion immediately upstream of said second portion having a minimum curvature in the range of approximately 0.05 to 0.06 cm^-1 ; and

d) a fourth portion immediately upstream of said third portion and extending to said leading edge and having a maximum curvature in the range of approximately 0.15 to 0.17 cm^-1.

13. The steam turbine vane according to claim 12, wherein said fourth portion has first and second segments, said first segment being immediately upstream of said third portion and having a radius of curvature that constantly increases as said suction surfaces progresses in the upstream direction to a maximum curvature in the range of approximately 0.15 to 0.17 cm^-1.

14. The steam turbine vane according to claim 13, wherein said second segment of said fourth portion is immediately upstream of said first segment of said fourth portion and has a radius of curvature that is in the range of approximately 0.15 to 0.17 cm^-1 throughout said second segment.

15. The steam turbine vane according to claim 12, wherein said first portion comprises approximately 30% of said airfoil width in the axial direction.

16. The steam turbine vane according to claim 15, wherein said second portion comprises approximately 5% of said airfoil width in the axial direction.

17. The steam turbine vane according to claim 16, wherein said third portion comprises approximately 5% of said airfoil width in the axial direction, and wherein said fourth portion comprises approximately 60% of said airfoil width in the axial direction.