Envelope forged stationary blade for L-2C row

Claim 2

A stationary blade for mounting in a stream turbine stationary cylinder comprising: an airfoil portion having an inner diameter end and an outer diameter end; a portion of an inner ring corresponding to the airfoil portion being integrally formed at the inner diameter end of the airfoil portion; and a portion of an outer ring corresponding to the airfoil portion, being integrally formed at the outer diameter end of the airfoil and being connected to the stationary cylinder of the steam turbine, the airfoil, inner ring and outer ring portions being one piece, said blade having a first groove formed in an end surface of the outer ring portion and extending from side to side for receiving weld material when additional blades of the same configuration are grouped together with the outer and inner ring portions juxtaposed side-by-side so that the weld material interconnects the outer ring portions, said inner ring portion having a stepped end and including a first step surface and a second step surface, said blade further having second and third grooves formed respectively in the first and second stepped surfaces of the inner ring portion and extending from side to side for receiving weld material when the additional blades of the same configuration are grouped together so that the weld material interconnects the inner ring portions.

Claim 3

A stationary blade as recited in claim 1, wherein the airfoil portion is 8.45 inches long.

Claim 4

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to chord decreases from about 0.745 at the inner diameter sections to about 0.60 at the outer diameter section.

Claim 5

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to width increases from about 1.3 at the inner diameter section to about 1.4 at the outer diameter section.

Claim 6

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a stagger angle increases from about 55° at the inner diameter section to about 65° at the inner diameter section.

Claim 7

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a value of minimum moment of inertia (I MIN) and a value of maximum moment of inertia (I MAX) increase parabolically from the inner diameter section to the outer diameter section.

Claim 8

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter.

Claim 9

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a chord of each section increases from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 10

A stationary blade as recited in claim 1, wherein the airfoil portion if divided into five basic sections extending from the inner diameter end to the outer diameter end, wherein a value of minimum moment of inertia (I MIN) and a value of a maximum moment of inertia (I MAX) increase parabolically from the inner diameter section to the outer diameter section; wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter section; and wherein a chord of each section increase from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 11

A stationary blade as recited in claim 1, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to chord decreases from about 0.745 at the inner diameter sections to about 0.60 at the outer diameter section; wherein a ratio of pitch to width increases from about 1.3 at the inner diameter section to about 1.4 at the outer diameter section; wherein a stagger angle increases from about 55° at the inner diameter section to about 60° at the outer diameter section; wherein a value of minimum moment of inertia (I MIN) and a value of maximum moment of inertia ( I MAX) increase parabolically from the inner diameter section to the outer diameter section; wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter section; and wherein a chord of each section increases from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 12

A row of stationary blades for a low pressure steam turbine, said row including 84 blades and being third of plural stationary blade rows from a turbine exit, each blade comprising: an airfoil portion having an inner diameter end and an outer diameter end; a portion of an inner ring corresponding to the airfoil portion being integrally formed at the inner diameter end of the airfoil portion; and a portion of an outer ring corresponding to the airfoil portion, being integrally formed at the outer diameter end of the airfoil portion and being connected to a casing, the airfoil, inner ring and outer ring portions being one piece, said blade being arranged in a row with a plurality of substantially identical blades so that the inner and outer ring portions of the blades are juxtaposed side-by-side, and welded together through a first circumferential weld extending around the outer ring portions and second and third circumferential welds extending around the inner ring portions, and said second weld being an upstream weld and said third weld being a downstream weld which is lower than the second, upstream weld.

Claim 13

A row of stationary blades for a low pressure steam turbine, said row including 84 blades and being third of plural stationary blade rows from a turbine exit, each blade comprising: an airfoil portion having an inner diameter end and an outer diameter end; a portion of an inner ring corresponding to the airfoil portion being integrally formed at the inner diameter end of the airfoil portion; and a portion of an outer ring corresponding to the airfoil portion, being integrally formed at the outer diameter end of the airfoil portion and being connected to a casing, the airfoil, inner ring and outer ring portions being one piece, said blade being arranged in a row with a plurality of substantially identical blades so that the inner and outer ring portions of the blades are juxtaposed side-by-side, and welded together through a first circumferential weld extending around the outer ring portions and second and third circumferential welds extending around the inner ring portions, and said second weld being an upstream weld and said third weld being a downstream weld which is lower than the second, upstream weld.

Claim 14

A stationary blade as recited in claim 11, wherein the airfoil portion is 8.45 inches long.

Claim 15

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to chord decreases from about 0.745 at the inner diameter section to about 0.60 at the outer diameter section.

Claim 16

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to width increases from about 1.3 at the inner diameter section to about 1.4 at the outer diameter section.

Claim 17

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a stagger angle increases from about 55° at the inner diameter section to about 65° at the outer diameter section.

Claim 18

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a value of minimum moment of inertia (I MIN) and a value of maximum moment of inertia (I MAX) increase parabolically from the inner diameter section to the outer diameter section.

Claim 19

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter.

Claim 20

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections extending from the inner diameter end to the outer diameter end, and wherein a chord of each section increases from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 21

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections, extending from the inner diameter end to the outer diameter end, and wherein a value of minimum moment of inertia (I MIN) and a value of maximum moment of inertia (I MAX) increase parabolically from the inner diameter section to the outer diameter section; wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter section; and wherein a chord of each section increases from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 22

A stationary blade as recited in claim 11, wherein the airfoil portion is divided into five basic sections, extending from the inner diameter end to the outer diameter end, and wherein a ratio of pitch to chord decreases from about 0.745 at the inner diameter section to about 0.60 at the outer diameter section; wherein a ratio of pitch to width increases from about 1.3 at the inner diameter section to about 1.4 at the outer diameter section; wherein a stagger angle increases from about 55° at the inner diameter section to about 65° at the outer diameter section; wherein a value of minimum moment of inertia and a value of maximum moment of inertia increase at an increasing rate from the inner diameter section to the outer diameter sectional; wherein a ratio of maximum thickness to chord for each section decreases from about 0.15 at the inner diameter section to about 0.13 at the outer diameter section; and wherein a chord of each section increases from about 3 inches at the inner diameter section to about 4.82 inches at the outer diameter section.

Claim 23

Blading for an L-2C row of a BB72 steam turbine formed in accordance with the following table: __________________________________________________________________________ SECTION E-E D-D C-C B-B A-A __________________________________________________________________________ RADIUS (IN) 29.9400 31.9400 34.1630 36.4400 38.3875 (mm) 760.476 811.276 867.740 925.576 975.042 PITCH 2.2395 2.3981 2.5554 2.7257 2.8714 WIDTH (IN) 1.71426 1.78185 1.85713 1.93401 2.00003 (mm) 43.542 45.258 47.171 49.123 50.800 CHORD (IN) 3.0042 3.42199 3.89786 4.39290 4.82024 PITCH/WIDTH 1.30640 1.34080 1.37599 1.40935 1.43566 PITCH/CHORD .74540 .69816 .65559 .62048 .59569 STAGGER ANGLE (DEG) 54.56409 58.02105 61.00489 63.37520 64.99626 MAXIMUM THICKNESS .44793 .46287 .50189 .55821 .61890 MAXIMUM THICKNESS/CHORD .14909 .13526 .12876 .12707 .12840 EXIT OPENING (IN) .67198 .63777 .60295 .57674 .55710 (mm) 17.068 16.199 15.314 14.649 14.150 EXIT OPENING ANGLE 26.60294 23.28277 20.34495 18.66529 17.34476 INLET INCL. ANGLE 62.75663 59.63185 55.92893 50.14567 47.17303 EXIT INCL. ANGLE 6.05101 6.68777 6.34746 6.30626 8.10422 AREA (IN**2) .75121 .91433 1.14569 1.43819 1.73475 ALPHA (DEG) 55.84176 59.51541 62.44364 64.49169 66.04618 I MIN (IN**4) .01511 .01861 .02481 .03421 .04615 I MAX (IN**4) .34856 .56503 .92310 1.45221 2.11677 GAUGING .672 .638 .603 .577 .557 INLET ANGLE 86.12 92.13 103.2 115.3 122.3 EXIT ANGLE 17.5 15.47 13.71 12.45 11.43 __________________________________________________________________________ said dimensions from above being within normal tolerances.

Claim 24

Blading for an L-2C row of a BB72 steam turbine formed in accordance with the following table: __________________________________________________________________________ SECTION E-E D-D C-C B-B A-A __________________________________________________________________________ RADIUS (IN) 29.9400 31.9400 34.1630 36.4400 38.3875 (mm) 760.476 811.276 867.740 925.576 975.042 PITCH 2.2395 2.3981 2.5554 2.7257 2.8714 WIDTH (IN) 1.71426 1.78185 1.85713 1.93401 2.00003 (mm) 43.542 45.258 47.171 49.123 50.800 CHORD (IN) 3.0042 3.42199 3.89786 4.39290 4.82024 PITCH/WIDTH 1.30640 1.34080 1.37599 1.40935 1.43566 PITCH/CHORD .74540 .69816 .65559 .62048 .59569 STAGGER ANGLE (DEG) 54.56409 58.02105 61.00489 63.37520 64.99626 MAXIMUM THICKNESS .44793 .46287 .50189 .55821 .61890 MAXIMUM THICKNESS/CHORD .14909 .13526 .12876 .12707 .12840 EXIT OPENING (IN) .67198 .63777 .60295 .57674 .55710 (mm) 17.068 16.199 15.314 14.649 14.150 EXIT OPENING ANGLE 26.60294 23.28277 20.34495 18.66529 17.34476 INLET INCL. ANGLE 62.75663 59.63185 55.92893 50.14567 47.17303 EXIT INCL. ANGLE 6.05101 6.68777 6.34746 6.30626 8.10422 AREA (IN**2) .75121 .91433 1.14569 1.43819 1.73475 ALPHA (DEG) 55.84176 59.51541 62.44364 64.49169 66.04618 I MIN (IN**4) .01511 .01861 .02481 .03421 .04615 I MAX (IN**4) .34856 .56503 .92310 1.45221 2.11677 GAUGING .672 .638 .603 .577 .557 INLET ANGLE 86.12 92.13 103.2 115.3 122.3 EXIT ANGLE 17.5 15.47 13.71 12.45 11.43 __________________________________________________________________________ said dimensions from above being within normal tolerances.