Information
-
Patent Grant
-
6761535
-
Patent Number
6,761,535
-
Date Filed
Monday, April 28, 200321 years ago
-
Date Issued
Tuesday, July 13, 200420 years ago
-
Inventors
-
Original Assignees
-
Examiners
Agents
-
CPC
-
US Classifications
Field of Search
US
- 416 97 R
- 416 223 A
- 416 243
-
International Classifications
-
Abstract
Second stage turbine buckets have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the bucket in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.039 inches in directions normal to any internal core surface location.
Description
BACKGROUND OF THE INVENTION
The present invention relates to a bucket of a stage of a gas turbine and particularly relates to a second stage turbine bucket internal core profile.
Many system requirements must be met for each stage of the hot gas path section of a gas turbine in order to meet design goals including overall improved efficiency and airfoil loading. Particularly, the buckets of the second stage of the turbine section must meet the operating requirements for that particular stage and also meet requirements for bucket cooling area and wall thickness. Internal cooling requirements must be optimized, necessitating a unique internal core profile to meet stage performance requirements enabling the turbine to operate in a safe, efficient and smooth manner.
BRIEF DESCRIPTION OF THE INVENTION
In accordance with a preferred embodiment of the present invention there is provided a unique internal core profile for a bucket of a gas turbine, preferably the second stage bucket, that enhances the performance of the gas turbine. It will be appreciated that the external airfoil shape of the second stage bucket airfoil improves the interaction between various stages of the turbine, and affords improved aerodynamic efficiency and mechanical loading. The external airfoil profile for the preferred bucket is set forth in a companion patent application Ser. No. 10/320,655, filed Dec. 17, 2002, titled “Airfoil Shape for a Turbine Bucket”, the disclosure of which is incorporated by reference. Concomitantly, the internal core shape is also significant for structural reasons as well as to optimize internal cooling with appropriate wall thickness.
The bucket internal core profile is defined by a unique loci of points which achieves the necessary structural and cooling requirements whereby improved turbine performance is obtained. This unique loci of points define the internal nominal core profile and are identified by the X, Y and Z Cartesian coordinates of Table I which follows. The 3700 points for the coordinate values shown in Table I are for a cold, i.e., room temperature bucket at various cross-sections of the bucket airfoil along its length. The positive X, Y and Z directions are axial toward the exhaust end of the turbine, tangential in the direction of engine rotation looking aft and radially outwardly toward the bucket tip, respectively. The X and Y coordinates are given, in distance dimensions, e.g., units of inches, and are joined smoothly at each Z location to form a smooth continuous internal core profile cross-section. The Z coordinates are given in non-dimensionalized form from 0 to 1. By multiplying the bucket height dimension, e.g., in inches, by the non-dimensional Z value of Table I, the internal core profile, of the bucket is obtained. Each defined internal core profile section in the X, Y plane is joined smoothly with adjacent profile sections in the z direction to form the complete internal bucket core profile.
The preferred second stage turbine bucket includes side wall surfaces with ribs extending internally between and formed integrally with the side walls. The ribs are spaced from one another and define with internal wall surfaces of the bucket side walls internal cooling passages, preferably serpentine in configuration, along the length of the bucket. The smooth continuing arcs or lines extending between the X, Y coordinates to define each profile section at each distance Z extend along the internal wall surfaces of the cooling passages and between adjacent passages along each of the side walls. Consequently, each internal core profile section has envelope portions which pass through the juncture between the ribs and each of the side walls as well as along the side walls of the cooling passages. These internal core profile sections are generally airfoil in shape at least in the airfoil portion of the bucket.
It will be appreciated that as each bucket heats up in use, the internal core profile will change as a result of mechanical loading and temperature. Thus, the cold or room temperature profile is given by the X, Y and Z coordinates for manufacturing purposes. Because a manufactured internal bucket core profile may be different from the nominal profile given by the following table, a distance of plus or minus 0.039 inches from the nominal profile in a direction normal to any surface location along the nominal profile defines a profile envelope for this internal bucket core profile. The profile is robust to this variation without impairment of the mechanical, cooling and aerodynamic functions of the bucket.
It will also be appreciated that the bucket can be scaled up or scaled down geometrically for introduction into similar turbine designs. Consequently, the X and Y coordinates in inches and the non-dimensional Z coordinates, when converted to inches, of the internal nominal core profile given below may be a function of the same constant or number. That is, the X, Y and Z coordinate values in inches may be multiplied or divided by the same constant or number to provide a scaled up or scaled down version of the internal bucket core profile while retaining the core profile section shape.
In a preferred embodiment according to the present invention, there is provided a turbine bucket including an airfoil, a platform, a shank and a dovetail having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form the bucket internal core profile.
In a further preferred embodiment according to the present invention, there is provided a turbine bucket including an airfoil, a platform, a shank and a dovetail, the bucket having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each Z distance along the bucket, the profile sections at the Z distances being joined smoothly with one another to form the bucket internal core profile, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile.
In a further preferred embodiment according to the present invention, there is provided a turbine comprising a turbine wheel having a plurality of buckets, each of the buckets including an airfoil, a platform, a shank and a dovetail, each bucket having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form the bucket internal core profile.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1
is a schematic representation of a hot gas path through multiple stages of a gas turbine and illustrates a second stage bucket airfoil;
FIG. 2
is a perspective view of a bucket according to a preferred embodiment of the present invention with the bucket illustrated in conjunction with its platform, shank and dovetail;
FIG. 3
is a radial inward view of the bucket of FIG.
2
and associated airfoil and platform;
FIGS. 4
,
5
and
6
are cross-sectional views taken at about 85% span, pitch and 5% span locations, respectively, along the height of the airfoil illustrating the cooling passages and representative internal core profile sections of the bucket;
FIGS. 7 and 8
are respective external side elevational views of the bucket having the external surfaces illustrated by dashed lines and the internal core profile illustrated by the full lines; and
FIGS. 9 and 10
are respective perspective views of the bucket with its external surface illustrated by the dashed lines and the internal core profile illustrated by the full lines.
DETAILED DESCRIPTION OF THE INVENTION
Referring now to the drawings, particularly to
FIG. 1
, there is illustrated a hot gas path, generally designated
10
, of a gas turbine
12
including a plurality of turbine stages. Three stages are illustrated. For example, the first stage comprises a plurality of circumferentially spaced nozzles
14
and buckets
16
. The nozzles are circumferentially spaced one from the other and fixed about the axis of the rotor. The first stage buckets
16
, of course, are mounted on the turbine rotor
17
. A second stage of the turbine
12
is also illustrated, including a plurality of circumferentially spaced nozzles
18
and a plurality of circumferentially spaced buckets
20
mounted on the rotor
17
. The third stage is also illustrated including a plurality of circumferentially spaced nozzles
22
and buckets
24
mounted on rotor
17
. It will be appreciated that the nozzles and buckets lie in the hot gas path
10
of the turbine
12
, the direction of flow of the hot gas through the hot gas path
10
being indicated by the arrow
26
.
Referring to
FIG. 2
, it will be appreciated that the buckets, for example, the buckets
20
of the second stage are mounted on a rotor wheel, not shown, forming part of rotor
17
and include platforms
30
, shanks
37
and dovetails
34
. Thus, each bucket
20
is provided with a substantially or near axial entry dovetail
34
for connection with a complementary-shaped mating dovetail, not shown, on the rotor wheel
17
. An axial entry dovetail, however, may be provided. It will also be appreciated that each bucket
20
has an airfoil
32
as illustrated in
FIG. 2-3
. Thus, each of the buckets
20
has an external bucket airfoil profile at any cross-section from the bucket root
31
to the bucket tip
33
in the shape of an airfoil
32
as illustrated in
FIGS. 4-6
. In this preferred embodiment of a second stage turbine bucket, there are sixty (60) bucket airfoils. While not forming part of the present invention, the second stage bucket airfoil
32
includes a plurality of internal, generally serpentine-shaped, cooling passages
35
(
FIGS. 4-6
) forming one or more air cooling circuits. These air cooling circuits exhaust r from the airfoil
32
into the hot gas path at exit locations, not shown, along the airfoil
32
.
More particularly, the airfoil
32
includes convex and concave external wall surfaces, i.e., pressure and suction surfaces
42
and
44
, respectively (FIG.
3
), which, with an internal core profile
40
(FIGS.
4
-
6
), define an airfoil wall thickness “t.” The airfoil
32
also includes a plurality of ribs
46
extending between or projecting from opposite side walls
48
of the airfoil. Ribs
46
are spaced from one another between leading and trailing edges
52
and
54
of the bucket, respectively, to define, with internal wall surface portions
49
of bucket side walls
48
, the plurality of internal generally serpentine-shaped cooling passages
35
.
To define the internal core shape of each second stage bucket, there is a unique set or loci of points in space that meet the stage requirements, bucket cooling area and wall thickness and can be manufactured. This unique loci of points, which defines the internal bucket core profile
40
, comprises a set of 3700 points relative to the axis of rotation of the turbine. A Cartesian coordinate system of X, Y and Z values given in Table 1 below defines this internal core profile
40
of the bucket airfoil
32
at various locations along its length. The coordinate values for the X and Y coordinates are set forth in inches in Table I although other units of dimensions may be used when the values are appropriately converted. The Z values are set forth in Table I in non-dimensional form from 0 to 1. To convert the Z value to a Z coordinate value, e.g., in inches, the non-dimensional Z value given in the table is multiplied by the height of the bucket in inches. The height of the bucket extends from the root of the dovetail
34
connection to the tip cap
33
of the airfoil. The Cartesian coordinate system has orthogonally-related X, Y and Z axes and the X axis lies parallel to the turbine rotor centerline, i.e., the rotary axis and a positive X coordinate value is axial toward the aft, i.e., exhaust end of the turbine. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor, looking aft, and the positive Z coordinate value is radially outwardly toward the bucket tip.
By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the internal core profile
40
of the bucket, e.g., the bucket airfoil portion, is illustrated by the dashed lines in
FIGS. 4-6
, at each Z distance along the length of the airfoil can be ascertained. By connecting the X and Y values with smooth continuing arcs, each internal core profile section
40
at each distance Z is fixed. The internal core profiles of the various internal locations between the distances Z are determined by smoothly connecting the adjacent profile sections
40
to one another to form the core profile. These values represent the internal core profiles at ambient, non-operating or non-hot conditions.
The smooth continuing arcs extending between the X, Y coordinates to define each profile section
40
at each distance Z extend along the internal wall surface portions
49
and between adjacent passages
35
along each of the side walls
48
. Thus, each internal core profile
40
has envelope portions which pass through the juncture between the ribs
46
and the side walls
48
as well as along the side walls of the cooling passages. The internal core profile
40
for the bucket
20
is illustrated by the heavy lines in
FIGS. 7-10
and extends into the airfoil
32
, platform
30
and dovetail
34
. The coordinate values of X, Y and Z of Table I are for the internal core profile of the bucket including the airfoil
32
, platform
30
, and dovetail
34
.
The Table I values are generated and shown to three decimal places for determining the internal core profile of the airfoil. There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual internal profile of the airfoil. Accordingly, the values for the profile given in Table I are for a nominal core profile. It will therefore be appreciated that ± typical manufacturing tolerances, i.e., ± values, including any coating thicknesses, are additive to the X and Y values given in Table I below. Accordingly, a distance of ±0.039 inches in a direction normal to any surface location along the internal core profile defines an internal core profile envelope for this particular bucket design and turbine, i.e., a range of variation between measured points on the actual internal core profile at nominal cold or room temperature and the ideal position of those points as given in the Table below at the same temperature. The internal core profile
40
is robust to this range of variation without impairment of mechanical and cooling functions.
The coordinate values given in Table I below provide the preferred nominal internal core profile envelope for bucket
20
.
TABLE I
|
|
X
Y
Z
X
Y
Z
X
Y
Z
|
|
|
13.299
0.221
0.111
14.033
−0.051
0.278
14.809
0.040
0.611
|
13.089
0.144
0.111
14.078
0.432
0.306
14.567
0.445
0.611
|
13.385
0.210
0.028
13.978
0.506
0.333
14.909
−0.496
0.611
|
13.232
0.229
0.056
14.393
−0.087
0.306
14.541
−0.125
0.611
|
13.096
0.094
0.111
14.136
−0.058
0.278
14.999
−0.625
0.611
|
13.250
0.226
0.000
14.187
−0.063
0.278
15.073
−0.531
0.611
|
13.405
0.026
0.028
13.971
−0.055
0.333
14.877
−0.455
0.611
|
13.148
0.226
0.000
14.088
0.526
0.333
15.113
−0.802
0.611
|
13.287
0.041
0.111
14.076
−0.053
0.306
14.986
−0.340
0.611
|
13.132
0.217
0.056
14.025
0.426
0.306
15.085
−0.757
0.611
|
13.149
0.058
0.056
13.982
−0.048
0.278
15.149
−0.806
0.611
|
13.149
0.058
0.056
14.308
−0.072
0.333
14.761
0.134
0.611
|
13.149
0.058
0.083
14.420
0.489
0.333
14.812
−0.372
0.611
|
13.107
0.192
0.111
14.144
0.532
0.333
14.785
0.087
0.611
|
13.104
0.080
0.028
14.235
−0.064
0.306
14.711
0.226
0.611
|
13.334
0.216
0.056
14.473
−0.107
0.333
15.028
−0.669
0.611
|
13.180
0.234
0.083
14.252
−0.064
0.333
14.499
0.524
0.611
|
13.199
0.233
0.000
14.341
−0.078
0.306
14.844
−0.413
0.611
|
13.196
0.233
0.111
14.036
0.325
0.278
15.057
−0.713
0.611
|
13.405
0.026
0.083
14.242
0.318
0.278
15.008
−0.388
0.611
|
13.236
0.047
0.111
14.444
0.276
0.278
14.623
−0.190
0.611
|
13.089
0.147
0.000
14.088
0.326
0.278
14.970
−0.582
0.611
|
13.283
0.222
0.083
14.028
−0.053
0.333
14.899
−0.150
0.611
|
13.131
0.062
0.000
14.293
0.312
0.278
15.177
−0.772
0.611
|
13.149
0.058
0.083
14.312
0.520
0.333
14.453
−0.068
0.611
|
13.233
0.047
0.000
13.973
0.418
0.306
14.498
−0.096
0.611
|
13.350
0.214
0.111
14.395
0.402
0.306
15.095
−0.579
0.611
|
13.334
0.216
0.083
13.921
0.551
0.361
14.336
0.656
0.611
|
13.149
0.057
0.028
14.417
−0.096
0.361
14.583
−0.157
0.611
|
13.200
0.051
0.083
13.896
−0.065
0.361
14.964
−0.293
0.611
|
13.303
0.039
0.056
14.378
0.571
0.361
14.921
−0.197
0.611
|
13.180
0.234
0.056
13.560
0.363
0.361
13.404
0.433
0.722
|
13.284
0.041
0.000
13.814
0.506
0.361
13.391
0.380
0.694
|
13.094
0.096
0.000
14.187
−0.058
0.361
13.395
0.330
0.694
|
13.438
0.022
0.000
13.659
0.425
0.361
13.440
0.533
0.750
|
13.088
0.128
0.083
14.245
−0.064
0.361
13.411
0.426
0.694
|
13.386
0.028
0.000
13.781
−0.082
0.361
13.407
0.384
0.722
|
13.354
0.032
0.083
14.013
0.056
0.361
13.417
0.489
0.750
|
13.404
0.207
0.000
14.679
0.354
0.389
13.437
0.470
0.694
|
13.334
0.216
0.028
14.485
0.524
0.361
13.425
0.290
0.694
|
13.385
0.210
0.056
14.715
0.308
0.389
13.431
0.545
0.778
|
13.180
0.234
0.028
14.623
0.418
0.361
13.444
0.600
0.806
|
13.104
0.080
0.083
14.534
0.492
0.361
13.420
0.441
0.750
|
13.200
0.051
0.028
14.846
0.117
0.389
13.425
0.478
0.722
|
13.283
0.222
0.056
14.749
0.262
0.389
13.431
0.498
0.778
|
13.354
0.032
0.028
14.815
0.166
0.389
13.440
0.553
0.806
|
13.338
0.034
0.111
14.707
−0.249
0.389
13.435
0.343
0.722
|
13.405
0.026
0.056
14.843
0.146
0.361
13.599
0.486
0.806
|
13.303
0.038
0.028
14.956
−0.428
0.361
13.863
0.882
0.806
|
13.146
0.226
0.111
14.685
−0.209
0.361
13.454
0.456
0.778
|
13.088
0.128
0.028
14.659
−0.217
0.389
13.825
0.416
0.806
|
13.251
0.045
0.056
14.511
0.513
0.389
13.514
0.663
0.778
|
13.335
0.034
0.000
14.557
0.478
0.389
13.705
0.809
0.778
|
13.200
0.051
0.056
14.809
0.194
0.361
13.504
0.491
0.806
|
13.099
0.178
0.083
14.875
0.098
0.361
13.689
0.420
0.778
|
13.401
0.208
0.111
14.580
0.457
0.361
13.842
0.853
0.778
|
13.104
0.080
0.056
14.740
0.288
0.361
13.682
0.827
0.806
|
13.247
0.227
0.111
14.968
−0.477
0.389
13.602
0.776
0.806
|
13.441
0.022
0.111
14.557
−0.161
0.389
13.551
0.489
0.806
|
13.302
0.220
0.000
14.914
−0.387
0.361
13.816
0.875
0.806
|
13.354
0.032
0.056
14.755
−0.282
0.389
13.496
0.434
0.778
|
13.149
0.057
0.028
14.905
0.017
0.389
13.781
0.434
0.806
|
13.437
0.203
0.028
14.735
−0.238
0.361
13.483
0.626
0.778
|
13.437
0.204
0.083
14.664
0.376
0.361
13.662
0.786
0.778
|
13.252
0.045
0.083
14.966
−0.052
0.361
13.462
0.512
0.806
|
13.390
0.028
0.111
14.872
−0.347
0.361
13.545
0.433
0.778
|
13.231
0.229
0.028
14.783
0.214
0.389
13.565
0.746
0.806
|
13.134
0.061
0.111
14.906
0.048
0.361
13.504
0.491
0.806
|
13.232
0.229
0.083
14.936
−0.002
0.361
13.725
0.847
0.806
|
13.185
0.053
0.111
14.876
0.067
0.389
13.737
0.451
0.806
|
13.099
0.178
0.056
14.933
−0.033
0.389
13.455
0.587
0.778
|
13.181
0.053
0.000
14.600
0.439
0.389
13.641
0.803
0.806
|
13.252
0.045
0.028
14.609
−0.187
0.389
13.622
0.760
0.778
|
13.132
0.217
0.083
14.929
−0.434
0.389
13.593
0.432
0.778
|
13.283
0.222
0.028
14.641
0.397
0.389
13.641
0.428
0.778
|
13.196
0.233
0.111
14.961
−0.084
0.389
13.828
0.380
0.778
|
13.132
0.217
0.028
14.802
−0.316
0.389
13.531
0.713
0.806
|
13.353
0.214
0.000
14.847
−0.353
0.389
13.692
0.467
0.806
|
13.437
0.203
0.056
14.504
−0.139
0.389
13.583
0.730
0.778
|
13.088
0.128
0.056
14.889
−0.393
0.389
13.795
0.843
0.778
|
13.109
0.194
0.000
15.246
−0.848
0.389
13.782
0.396
0.778
|
13.303
0.039
0.083
15.246
−0.628
0.361
13.499
0.677
0.806
|
13.099
0.178
0.028
15.294
−0.824
0.389
13.770
0.863
0.806
|
13.385
0.210
0.083
15.186
−0.555
0.389
13.646
0.479
0.806
|
13.712
0.170
0.000
15.006
−0.521
0.389
13.874
0.364
0.778
|
13.539
0.191
0.028
15.155
−0.413
0.361
13.869
0.398
0.806
|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
14.308
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
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|
13.214
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|
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|
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|
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|
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|
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|
13.748
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|
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|
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|
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|
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|
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|
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|
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|
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14.771
−0.533
0.972
|
13.969
−0.051
0.306
14.599
0.403
0.611
14.793
−0.345
0.972
|
14.139
0.326
0.278
14.663
−0.224
0.611
14.794
−0.480
1.000
|
14.367
0.507
0.333
14.685
0.271
0.611
14.692
−0.107
0.972
|
14.022
−0.052
0.306
15.137
−0.675
0.611
14.804
−0.522
0.972
|
14.131
0.435
0.306
14.742
−0.294
0.611
14.695
−0.428
0.972
|
14.472
0.467
0.333
14.461
0.561
0.611
14.758
−0.297
1.000
|
14.291
0.426
0.306
14.832
−0.007
0.611
|
14.257
0.529
0.333
14.629
0.360
0.611
|
14.140
−0.155
0.333
14.362
−0.016
0.611
|
14.182
−0.059
0.306
|
|
It will also be appreciated that the internal bucket core profile disclosed in the above Table may be scaled up or down geometrically for use in other similar turbine designs. Consequently, the coordinate values set forth in Table 1 may be scaled upwardly or downwardly such that the core profile shape remains unchanged. A scaled version of the coordinates in Table 1 would be represented by X, Y and Z coordinate values of Table 1, with the non-dimensional Z coordinate value converted to inches, multiplied or divided by a constant number.
While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.
Claims
- 1. A turbine bucket including an airfoil, a platform, a shank and a dovetail having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.
- 2. A turbine bucket according to claim 1 wherein said bucket has side walls and ribs extending therebetween, said ribs being spaced from one another between leading and trailing edges of the bucket and defining with internal wall surfaces of said side walls internal cooling passages along the length of the bucket, said smooth continuing arcs extending along the internal wall surfaces of the cooling passages and between adjacent passages along said side walls.
- 3. A turbine bucket according to claim 2 wherein said smooth continuing arcs pass through junctures between the ribs and each of the side walls.
- 4. A turbine bucket according to claim 1 wherein said bucket airfoil has an external airfoil shape, said internal core profile sections including generally airfoil-shaped portions within the bucket airfoil and generally conforming to profile sections of said external airfoil shape of the bucket airfoil less a wall thickness therebetween.
- 5. A turbine bucket according to claim 1 forming part of a second stage of a turbine.
- 6. A turbine bucket according to claim 1 wherein said internal core profile lies in an envelope within ±0.039 inches in a direction normal to any internal core surface location therealong.
- 7. A turbine bucket including an airfoil, a platform, a shank and a dovetail, said bucket having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each Z distance along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile.
- 8. A turbine bucket according to claim 7 wherein said bucket has side walls and ribs extending therebetween, said ribs being spaced from one another between leading and trailing edges of the bucket and defining with internal wall surfaces of said side walls internal cooling passages along the length of the bucket, said smooth continuing arcs extending along the internal wall surfaces of the cooling passages and between adjacent passages along said side walls.
- 9. A turbine bucket according to claim 7 wherein said smooth continuing arcs pass through junctures between the ribs and each of the side walls.
- 10. A turbine bucket according to claim 7 wherein said bucket airfoil has an external airfoil shape, said internal core profile sections including generally airfoil-shaped portions within the bucket airfoil and generally conforming to profile sections of said external airfoil shape of the bucket airfoil less a wall thickness therebetween.
- 11. A turbine bucket according to claim 7 wherein said integral core shape lies in an envelope within ±0.039 inches in a direction normal to any internal core surface location therealong.
- 12. A turbine comprising a turbine wheel having a plurality of buckets, each of said buckets including an airfoil, a platform, a shank and a dovetail, each bucket having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile.
- 13. A turbine according to claim 12 wherein each said bucket has side walls and ribs extending therebetween, said ribs being spaced from one another between leading and trailing edges of the bucket and defining with internal wall surfaces of said side walls internal cooling passages along the length of the bucket, said smooth continuing arcs extending along the internal wall surfaces of the cooling passages and between adjacent passages along said side walls.
- 14. A turbine according to claim 12 wherein said smooth continuing arcs pass through junctures between the ribs and each of the side walls.
- 15. A turbine according to claim 12 wherein each said bucket has an external airfoil shape, said internal core profile sections including generally airfoil-shaped portions within the bucket airfoil and generally conforming to profile sections of said external airfoil shape of the bucket airfoil less a wall thickness therebetween.
- 16. A turbine according to claim 12 wherein the turbine wheel comprises a second stage of the turbine.
- 17. A turbine according to claim 12 wherein the turbine wheel has 60 buckets and X represents a distance parallel to the turbine axis of rotation.
- 18. A turbine according to claim 12 wherein the X, Y and Z distances are scalable as a function of the same constant or number to provide scaled-up or scaled-down internal core profile.
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Number |
Name |
Date |
Kind |
5980209 |
Barry et al. |
Nov 1999 |
A |
6450770 |
Wang et al. |
Sep 2002 |
B1 |
6461109 |
Wedlake et al. |
Oct 2002 |
B1 |