Stationary blade design for L-OC row

Blading for an L-OC row of a turbine in accordance with the following table:

• ______________________________________ SECTION F-F E-E D-D ______________________________________ RADIUS (IN) 28.92 33.00 38.00 (mm) 734.44 838.2 965.2 PITCH 3.03 3.46 3.98 WIDTH (IN) 3.77 4.143 4.60 (mm) 95.78 105.27 116.79 CHORD (IN) 5.17 5.91 6.83 (mm) 131.30 150.21 173.55 PITCH/WIDTH .81 .83 .87 PITCH/CHORD .59 .58 .58 STAGGER ANGLE (DEG) 42.44 44.95 47.25 MAXIMUM THICKNESS (IN) .85 .88 1.0 (mm) 21.58 22.37 25.30 MAXIMUM THICKNESS/CHORD .16 .15 .15 EXIT OPENING (IN) 1.06 1.18 1.32 (mm) 26.87 30.03 35.58 EXIT OPENING ANGLE (DEG) 21.65 21.10 20.38 INLET ANGLE (DEG) 68.5 70.01 83. EXIT ANGLE (DEG) 20.29 19.74 19.26 INLET INCL. ANGLE (DEG) 29.03 33.96 37.96 EXIT INCL. ANGLE (DEG) 1.37 1.55 1.42 AREA (IN**2) 2.42 2.85 3.60 [ALPHA] FLOW ANGLE (DEG) 42.54 45.11 47.34 I MIN (IN**4) .32 .40 .58 I MAX (IN**4) 3.10 4.82 7.92 ______________________________________ SECTION C-C B-B A-A ______________________________________ RADIUS (IN) 42.25 47.16 55.31 (mm) 1073.15 1197.86 1404.84 PITCH 4.42 4.94 5.79 WIDTH (IN) 4.99 5.43 6.18 (mm) 126.65 138.02 156.89 CHORD (IN) 7.62 8.53 10.06 (mm) 193.57 216.77 255.45 PITCH/WIDTH .89 .91 .94 PITCH/CHORD .58 .58 .58 STAGGER ANGLE (DEG) 48.77 50.16 51.89 MAXIMUM THICKNESS (IN) 1.12 1.20 1.50 (mm) 28.33 30.49 38.23 MAXIMUM THICKNESS/CHORD 15 .14 .15 EXIT OPENING (IN) 1.41 1.43 1.41 (mm) 35.82 36.29 35.72 EXIT OPENING ANGLE (DEG) 19.51 17.66 14.75 INLET ANGLE (DEG) 89.37 81. 77.99 EXIT ANGLE (DEG) 18.18 16.11 13.19 INLET INCL. ANGLE (DEG) 43.27 45.97 49.85 EXIT INCL. ANGLE (DEG) 1.56 1.47 1.36 AREA (IN**2) 4.34 5.27 7.82 [ALPHA] FLOW ANGLE (D 48.56 49.90 51.53 I MIN (IN**4) .84 1.34 2.98 I MAX (IN**4) 11.63 17.68 35.49 ______________________________________

A stationary blade of a steam turbine having a rotor and an inner cylinder for mounting the stationary blade in a row with plural identical stationary blades, comprising:

• an airfoil portion having a leading edge, a trailing edge, a pressure-side concave surface and suction-side convex surface extending between the leading and trailing edges, and having a stagger angle being defined as an angle of a chord between the leading and trailing edges to a longitudinal axis of the rotor;
• an outer ring for connecting an outer end of the airfoil portion to the inner cylinder;
• an inner ring connected to an inner end of the airfoil portion;
• and
• a seal assembly carried by the inner ring and sealingly engaging the rotor;
• wherein the stagger angle ranges from about 42.degree. at the inner end of the airfoil portion to about 52.degree. at the outer end;
• wherein the airfoil portion is divided into six basic sections extending from the inner end to the outer end;
• wherein a value of minimum moment of inertia increases as follows:
• 0.32 inches at the inner end of the blade, 0.40 inch at 4.08 inches from the inner end, 0.58 inch at 9.08 inches from the inner end, 0.84 inch at 13.33 inches from the inner end, 1.34 inch at 18.24 inches from the inner end, and 2.98 inches at 26.39 inches from the inner end;
• and
• wherein values of an inlet included angle at the six basic sections, proceeding from the inner end to the outer end, are as follows:
• 29.degree., 33.degree., 37.degree., 43.degree., 45.degree. and 49.degree..