# Patent

## Title
Airfoil shape for a compressor

## Abstract

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

## Background
BACKGROUND OF THE INVENTION
The present invention is related to the following GE commonly assigned applications Ser. Nos. 11/586,060, 11/586,049, 11/586,050, 11/586,051, 11/586,052, 11/586,053, 11/586,046, 11/586,054, 11/586,085, 11/586,055, 11/586,088, 11/586,088, 11/586,086, 11/586,045, 11/586,087, 11/586,059, 11/586,090, 11/586,091 and 11/586,092 each filed on Oct. 25, 2006; and the following GE commonly assigned applications Ser. Nos.: 11/591,691, 11/591,695, 11/591,694, 11/591,693 and 11/591,692 each filed on Nov. 2, 2006.
The present invention relates to airfoils for a rotor blade of a gas turbine. In particular, the invention relates to compressor airfoil profiles for various stages of the compressor. In particular, the invention relates to compressor airfoil profiles for either inlet guide vanes, rotors, or stators at various stages of the compressor.
In a gas turbine, many system requirements should be met at each stage of a gas turbine's flow path section to meet design goals. These design goals include, but are not limited to, overall improved efficiency and airfoil loading capability. For example, and in no way limiting of the invention, a blade of a compressor stator should achieve thermal and mechanical operating requirements for that particular stage. Further, for example, and in no way limiting of the invention, a blade of a compressor rotor should achieve thermal and mechanical operating requirements for that particular stage.
BRIEF DESCRIPTION OF THE INVENTION
In accordance with one exemplary aspect of the instant invention, an article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
In accordance with another exemplary aspect of the instant invention, a compressor comprises a compressor wheel. The compressor wheel has a plurality of articles of manufacture. Each of the articles of manufacture includes an airfoil having an airfoil shape. The airfoil comprises a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
In accordance with yet exemplary another aspect of the instant invention, a compressor comprises a compressor wheel having a plurality of articles of manufacture. Each of the articles of manufacture includes an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.



BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a schematic exemplary representation of a compressor flow path through multiple stages of a gas turbine and illustrates an exemplary airfoil according to an embodiment of the invention;
FIGS. 2 and 3 are respective perspective exemplary views of a rotor blade according to an embodiment of the invention with the rotor blade airfoil illustrated in conjunction with its platform and its substantially or near axial entry dovetail connection;
FIGS. 4 and 5 are side elevational views of the rotor blade of FIG. 2 and associated platform and dovetail connection as viewed in a generally circumferential direction from the pressure and suction sides of the airfoil, respectively;
FIG. 6 is a cross-sectional view of the rotor blade airfoil taken generally about on line 6-6 in FIG. 5;
FIG. 7 is a perspective views of a rotor blade according to an exemplary embodiment of the invention with coordinate system superimposed thereon; and
FIG. 8 is a perspective view of a stator blade according to an exemplary embodiment of the invention with coordinate system superimposed thereon.



DETAILED DESCRIPTION OF THE INVENTION
Referring now to the drawings, FIG. 1 illustrates an axial compressor flow path 1 of a gas turbine compressor 2 that includes a plurality of compressor stages. The compressor stages are sequentially numbered in the Figure. The compressor flow path comprises any number of rotor stages and stator stages, such as eighteen. However, the exact number of rotor and stator stages is a choice of engineering design. Any number of rotor and stator stages can be provided in the compressor, as embodied by the invention. The seventeen rotor stages are merely exemplary of one turbine design. The eighteen rotor stages are not intended to limit the invention in any manner.
The compressor rotor blades impart kinetic energy to the airflow and therefore bring about a desired pressure rise across the compressor. Directly following the rotor airfoils is a stage of stator airfoils. Both the rotor and stator airfoils turn the airflow, slow the airflow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the airflow. The configuration of the airfoil (along with its interaction with surrounding airfoils), including its peripheral surface provides for stage airflow efficiency, enhanced aeromechanics, smooth laminar flow from stage to stage, reduced thermal stresses, enhanced interrelation of the stages to effectively pass the airflow from stage to stage, and reduced mechanical stresses, among other desirable aspects of the invention. Typically, multiple rows of rotor/stator stages are stacked in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Rotor and stator airfoils can be secured to rotor wheels or stator case by an appropriate attachment configuration, often known as a “root”, “base” or “dovetail” (see FIGS. 2-5).
A stage of the compressor 2 is exemplarily illustrated in FIG. 1. The stage of the compressor 2 comprises a plurality of circumferentially spaced rotor blades 22 mounted on a rotor wheel 51 and a plurality of circumferentially spaced stator blades 23 attached to a static compressor case 59. Each of the rotor wheels is attached to aft drive shaft 58, which is connected to the turbine section of the engine. The rotor blades and stator blades lie in the flow path 1 of the compressor. The direction of airflow through the compressor flow path 1, as embodied by the invention, is indicated by the arrow 60 (FIG. 1). This stage of the compressor 2 is merely exemplarily of the stages of the compressor 2 within the scope of the invention. The illustrated and described stage of the compressor 2 is not intended to limit the invention in any manner.
The rotor blades 22 are mounted on the rotor wheel 51 forming part of aft drive shaft 58. Each rotor blade 22, as illustrated in FIGS. 2-6, is provided with a platform 61, and substantially or near axial entry dovetail 62 for connection with a complementary-shaped mating dovetail, not shown, on the rotor wheel 51. An axial entry dovetail, however, may be provided with the airfoil profile, as embodied by the invention. Each rotor blade 22 comprises a rotor blade airfoil 63, as illustrated in FIGS. 2-6. Thus, each of the rotor blades 22 has a rotor blade airfoil profile 66 at any cross-section from the airfoil root 64 at a midpoint of platform 61 to the rotor blade tip 65 in the general shape of an airfoil (FIG. 6).
To define the airfoil shape of the rotor blade airfoil, a unique set or loci of points in space are provided. This unique set or loci of points meet the stage requirements so the stage can be manufactured. This unique loci of points also meets the desired requirements for stage efficiency and reduced thermal and mechanical stresses. The loci of points are arrived at by iteration between aerodynamic and mechanical loadings enabling the compressor to run in an efficient, safe and smooth manner.
The loci, as embodied by the invention, defines the rotor blade airfoil profile and can comprise a set of points relative to the axis of rotation of the engine. For example, a set of points can be provided to define a rotor blade airfoil profile.
A Cartesian coordinate system of X, Y and Z values given in the Table below defines a profile of a rotor blade airfoil at various locations along its length. The airfoil, as embodied by the invention, could find an application as a 1st stage airfoil variable stator vane. The coordinate values for the X, Y and Z coordinates are set forth in inches, although other units of dimensions may be used when the values are appropriately converted. These values exclude fillet regions of the platform. The Cartesian coordinate system has orthogonally-related X, Y and Z axes. The X axis lies parallel to the compressor blade's dovetail axis, which is at a angle to the engine's centerline, as illustrated in FIG. 7 for a rotor and FIG. 8 for a stator. A positive X coordinate value is axial toward the aft, for example the exhaust end of the compressor. A positive Y coordinate value directed normal to the dovetail axis. A positive Z coordinate value is directed radially outward toward tip of the airfoil, which is towards the static casing of the compressor for rotor blades, and directed radially inward towards the engine centerline of the compressor for stator blades.
For reference purposes only, there is established point-0 passing through the intersection of the airfoil and the platform along the stacking axis, as illustrated in FIG. 5. In the exemplary embodiment of the airfoil hereof, the point-0 is defined as the reference section where the Z coordinate of the table above is at 0.000 inches, which is a set predetermined distance from the engine or rotor centerline.
By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the profile section of the rotor blade airfoil, such as, but not limited to the profile section 66 in FIG. 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 profile section 66 at each distance Z can be fixed. The airfoil profiles of the various surface locations between the distances Z are determined by smoothly connecting the adjacent profile sections 66 to one another, thus forming the airfoil profile. These values represent the airfoil profiles at ambient, non-operating or non-hot conditions and are for an uncoated airfoil.
The table values are generated and shown to three decimal places for determining the profile of the airfoil. There are typical manufacturing tolerances as well as coatings, which should be accounted for in the actual profile of the airfoil. Accordingly, the values for the profile given are for a nominal airfoil. It will therefore be appreciated that +/−typical manufacturing tolerances, such as, +/−values, including any coating thicknesses, are additive to the X and Y values. Therefore, a distance of about +/−0.160 inches in a direction normal to any surface location along the airfoil profile defines an airfoil profile envelope for a rotor blade airfoil design and compressor. In other words, a distance of about +/−0.160 inches in a direction normal to any surface location along the airfoil profile defines a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points, at the same temperature, as embodied by the invention. The rotor blade airfoil design, as embodied by the invention, is robust to this range of variation without impairment of mechanical and aerodynamic functions.
The coordinate values given in TABLE 1 below provide the nominal profile envelope for an exemplary 1st stage airfoil variable stator vane.









TABLE 1





X-LOC
Y-LOC
Z-LOC

















3.117
−2.448
0.093


3.116
−2.451
0.093


3.114
−2.457
0.093


3.106
−2.467
0.093


3.09
−2.477
0.093


3.057
−2.476
0.093


3.012
−2.467
0.093


2.952
−2.454
0.093


2.878
−2.438
0.093


2.782
−2.415
0.093


2.672
−2.387
0.093


2.555
−2.355
0.093


2.424
−2.317
0.093


2.281
−2.271
0.093


2.124
−2.218
0.093


1.961
−2.159
0.093


1.794
−2.094
0.093


1.62
−2.022
0.093


1.442
−1.943
0.093


1.258
−1.858
0.093


1.07
−1.764
0.093


0.877
−1.661
0.093


0.68
−1.55
0.093


0.486
−1.433
0.093


0.294
−1.311
0.093


0.107
−1.184
0.093


−0.076
−1.052
0.093


−0.255
−0.915
0.093


−0.429
−0.773
0.093


−0.599
−0.625
0.093


−0.763
−0.472
0.093


−0.924
−0.314
0.093


−1.079
−0.15
0.093


−1.229
0.02
0.093


−1.37
0.189
0.093


−1.5
0.357
0.093


−1.62
0.522
0.093


−1.73
0.684
0.093


−1.832
0.842
0.093


−1.925
0.997
0.093


−2.011
1.148
0.093


−2.084
1.288
0.093


−2.148
1.417
0.093


−2.2
1.535
0.093


−2.244
1.641
0.093


−2.279
1.734
0.093


−2.306
1.813
0.093


−2.327
1.882
0.093


−2.342
1.94
0.093


−2.353
1.988
0.093


−2.359
2.028
0.093


−2.36
2.058
0.093


−2.357
2.081
0.093


−2.351
2.1
0.093


−2.343
2.112
0.093


−2.334
2.12
0.093


−2.324
2.124
0.093


−2.309
2.125
0.093


−2.291
2.121
0.093


−2.272
2.113
0.093


−2.247
2.097
0.093


−2.218
2.074
0.093


−2.184
2.043
0.093


−2.143
2.003
0.093


−2.096
1.954
0.093


−2.042
1.896
0.093


−1.979
1.827
0.093


−1.907
1.747
0.093


−1.825
1.656
0.093


−1.734
1.554
0.093


−1.633
1.442
0.093


−1.523
1.319
0.093


−1.407
1.191
0.093


−1.286
1.058
0.093


−1.159
0.921
0.093


−1.026
0.779
0.093


−0.887
0.634
0.093


−0.741
0.484
0.093


−0.59
0.331
0.093


−0.437
0.178
0.093


−0.284
0.027
0.093


−0.13
−0.124
0.093


0.025
−0.273
0.093


0.182
−0.421
0.093


0.34
−0.567
0.093


0.499
−0.712
0.093


0.66
−0.854
0.093


0.824
−0.993
0.093


0.989
−1.13
0.093


1.157
−1.264
0.093


1.323
−1.391
0.093


1.485
−1.51
0.093


1.644
−1.622
0.093


1.799
−1.726
0.093


1.952
−1.823
0.093


2.101
−1.913
0.093


2.245
−1.996
0.093


2.385
−2.072
0.093


2.514
−2.138
0.093


2.631
−2.195
0.093


2.736
−2.244
0.093


2.835
−2.288
0.093


2.922
−2.325
0.093


2.989
−2.353
0.093


3.043
−2.375
0.093


3.083
−2.391
0.093


3.109
−2.409
0.093


3.117
−2.425
0.093


3.118
−2.437
0.093


3.118
−2.442
0.093


3.117
−2.445
0.093


3.117
−2.447
0.093


3.246
−1.589
2.144


3.245
−1.592
2.144


3.243
−1.597
2.144


3.236
−1.607
2.144


3.22
−1.616
2.144


3.189
−1.615
2.144


3.147
−1.606
2.144


3.091
−1.592
2.144


3.022
−1.576
2.144


2.932
−1.554
2.144


2.828
−1.527
2.144


2.718
−1.498
2.144


2.594
−1.464
2.144


2.456
−1.425
2.144


2.305
−1.381
2.144


2.148
−1.334
2.144


1.985
−1.282
2.144


1.816
−1.225
2.144


1.641
−1.162
2.144


1.461
−1.094
2.144


1.275
−1.019
2.144


1.085
−0.938
2.144


0.891
−0.849
2.144


0.698
−0.755
2.144


0.509
−0.656
2.144


0.322
−0.551
2.144


0.14
−0.442
2.144


−0.038
−0.326
2.144


−0.211
−0.204
2.144


−0.379
−0.078
2.144


−0.545
0.052
2.144


−0.707
0.186
2.144


−0.867
0.324
2.144


−1.023
0.465
2.144


−1.171
0.606
2.144


−1.31
0.746
2.144


−1.441
0.885
2.144


−1.564
1.022
2.144


−1.68
1.158
2.144


−1.788
1.29
2.144


−1.887
1.419
2.144


−1.975
1.54
2.144


−2.051
1.651
2.144


−2.117
1.753
2.144


−2.172
1.844
2.144


−2.218
1.924
2.144


−2.256
1.994
2.144


−2.286
2.053
2.144


−2.309
2.105
2.144


−2.326
2.148
2.144


−2.338
2.183
2.144


−2.345
2.211
2.144


−2.347
2.232
2.144


−2.345
2.25
2.144


−2.34
2.263
2.144


−2.332
2.271
2.144


−2.323
2.275
2.144


−2.309
2.276
2.144


−2.293
2.273
2.144


−2.274
2.265
2.144


−2.25
2.251
2.144


−2.221
2.23
2.144


−2.187
2.202
2.144


−2.145
2.168
2.144


−2.097
2.125
2.144


−2.042
2.074
2.144


−1.976
2.015
2.144


−1.9
1.946
2.144


−1.814
1.868
2.144


−1.717
1.781
2.144


−1.61
1.686
2.144


−1.492
1.582
2.144


−1.367
1.475
2.144


−1.237
1.365
2.144


−1.1
1.251
2.144


−0.957
1.135
2.144


−0.808
1.015
2.144


−0.652
0.893
2.144


−0.489
0.769
2.144


−0.325
0.646
2.144


−0.159
0.525
2.144


0.007
0.406
2.144


0.175
0.288
2.144


0.343
0.171
2.144


0.511
0.053
2.144


0.678
−0.065
2.144


0.847
−0.182
2.144


1.015
−0.298
2.144


1.185
−0.413
2.144


1.356
−0.526
2.144


1.522
−0.634
2.144


1.683
−0.737
2.144


1.841
−0.833
2.144


1.993
−0.924
2.144


2.142
−1.009
2.144


2.285
−1.088
2.144


2.424
−1.162
2.144


2.558
−1.231
2.144


2.68
−1.291
2.144


2.791
−1.344
2.144


2.891
−1.39
2.144


2.984
−1.433
2.144


3.065
−1.468
2.144


3.128
−1.496
2.144


3.179
−1.517
2.144


3.216
−1.533
2.144


3.24
−1.552
2.144


3.246
−1.568
2.144


3.247
−1.579
2.144


3.247
−1.584
2.144


3.246
−1.587
2.144


3.246
−1.588
2.144


3.201
−0.63
4.195


3.2
−0.632
4.195


3.198
−0.637
4.195


3.191
−0.647
4.195


3.177
−0.656
4.195


3.147
−0.657
4.195


3.106
−0.649
4.195


3.053
−0.638
4.195


2.986
−0.625
4.195


2.899
−0.607
4.195


2.799
−0.586
4.195


2.693
−0.564
4.195


2.573
−0.538
4.195


2.44
−0.507
4.195


2.294
−0.473
4.195


2.142
−0.435
4.195


1.983
−0.394
4.195


1.819
−0.348
4.195


1.65
−0.297
4.195


1.475
−0.241
4.195


1.294
−0.178
4.195


1.11
−0.108
4.195


0.921
−0.031
4.195


0.734
0.052
4.195


0.551
0.141
4.195


0.37
0.237
4.195


0.194
0.338
4.195


0.021
0.444
4.195


−0.149
0.554
4.195


−0.316
0.667
4.195


−0.48
0.784
4.195


−0.642
0.904
4.195


−0.801
1.028
4.195


−0.958
1.155
4.195


−1.106
1.281
4.195


−1.247
1.407
4.195


−1.38
1.531
4.195


−1.506
1.654
4.195


−1.624
1.776
4.195


−1.735
1.895
4.195


−1.839
2.012
4.195


−1.931
2.122
4.195


−2.012
2.223
4.195


−2.081
2.315
4.195


−2.14
2.398
4.195


−2.19
2.471
4.195


−2.231
2.534
4.195


−2.265
2.588
4.195


−2.291
2.635
4.195


−2.311
2.675
4.195


−2.325
2.707
4.195


−2.335
2.733
4.195


−2.339
2.753
4.195


−2.339
2.77
4.195


−2.336
2.784
4.195


−2.33
2.792
4.195


−2.321
2.796
4.195


−2.308
2.796
4.195


−2.292
2.793
4.195


−2.274
2.785
4.195


−2.251
2.772
4.195


−2.223
2.752
4.195


−2.189
2.727
4.195


−2.149
2.694
4.195


−2.101
2.655
4.195


−2.047
2.608
4.195


−1.982
2.553
4.195


−1.907
2.489
4.195


−1.821
2.418
4.195


−1.725
2.339
4.195


−1.619
2.252
4.195


−1.501
2.158
4.195


−1.377
2.061
4.195


−1.247
1.962
4.195


−1.111
1.86
4.195


−0.968
1.755
4.195


−0.819
1.648
4.195


−0.664
1.539
4.195


−0.502
1.428
4.195


−0.338
1.32
4.195


−0.174
1.213
4.195


−0.008
1.108
4.195


0.159
1.005
4.195


0.328
0.904
4.195


0.497
0.805
4.195


0.667
0.706
4.195


0.837
0.607
4.195


1.007
0.508
4.195


1.177
0.409
4.195


1.347
0.312
4.195


1.513
0.218
4.195


1.673
0.13
4.195


1.829
0.046
4.195


1.98
−0.034
4.195


2.126
−0.108
4.195


2.267
−0.178
4.195


2.402
−0.244
4.195


2.533
−0.305
4.195


2.652
−0.358
4.195


2.76
−0.406
4.195


2.857
−0.447
4.195


2.948
−0.485
4.195


3.026
−0.517
4.195


3.087
−0.542
4.195


3.136
−0.562
4.195


3.172
−0.576
4.195


3.195
−0.594
4.195


3.201
−0.609
4.195


3.202
−0.619
4.195


3.202
−0.625
4.195


3.201
−0.627
4.195


3.201
−0.628
4.195


3.11
0.141
6.246


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1.722
14.45


−1.185
1.646
14.45


−1.059
1.567
14.45


−0.928
1.487
14.45


−0.792
1.405
14.45


−0.65
1.322
14.45


−0.507
1.24
14.45


−0.364
1.159
14.45


−0.219
1.08
14.45


−0.074
1.003
14.45


0.073
0.929
14.45


0.221
0.856
14.45


0.37
0.786
14.45


0.52
0.718
14.45


0.67
0.651
14.45


0.821
0.585
14.45


0.972
0.52
14.45


1.119
0.459
14.45


1.262
0.402
14.45


1.4
0.348
14.45


1.534
0.298
14.45


1.664
0.253
14.45


1.788
0.21
14.45


1.909
0.171
14.45


2.024
0.136
14.45


2.13
0.105
14.45


2.225
0.079
14.45


2.31
0.057
14.45


2.39
0.037
14.45


2.46
0.021
14.45


2.513
0.009
14.45


2.556
−0.001
14.45


2.589
−0.008
14.45


2.61
−0.02
14.45


2.617
−0.032
14.45


2.618
−0.04
14.45


2.618
−0.045
14.45


2.618
−0.047
14.45


2.618
−0.048
14.45


2.454
−0.505
16.501


2.453
−0.507
16.501


2.452
−0.511
16.501


2.448
−0.519
16.501


2.438
−0.529
16.501


2.414
−0.533
16.501


2.381
−0.531
16.501


2.337
−0.528
16.501


2.283
−0.523
16.501


2.212
−0.516
16.501


2.13
−0.508
16.501


2.043
−0.497
16.501


1.946
−0.485
16.501


1.838
−0.469
16.501


1.719
−0.45
16.501


1.595
−0.428
16.501


1.466
−0.402
16.501


1.333
−0.373
16.501


1.195
−0.339
16.501


1.053
−0.301
16.501


0.907
−0.258
16.501


0.758
−0.209
16.501


0.605
−0.155
16.501


0.455
−0.095
16.501


0.306
−0.031
16.501


0.159
0.037
16.501


0.013
0.11
16.501


−0.131
0.187
16.501


−0.273
0.267
16.501


−0.414
0.351
16.501


−0.553
0.437
16.501


−0.69
0.526
16.501


−0.825
0.618
16.501


−0.958
0.712
16.501


−1.086
0.804
16.501


−1.207
0.896
16.501


−1.323
0.986
16.501


−1.434
1.074
16.501


−1.539
1.161
16.501


−1.638
1.246
16.501


−1.732
1.329
16.501


−1.817
1.406
16.501


−1.892
1.478
16.501


−1.958
1.543
16.501


−2.015
1.602
16.501


−2.063
1.654
16.501


−2.104
1.699
16.501


−2.137
1.738
16.501


−2.165
1.771
16.501


−2.186
1.799
16.501


−2.202
1.823
16.501


−2.214
1.841
16.501


−2.221
1.856
16.501


−2.226
1.869
16.501


−2.228
1.88
16.501


−2.225
1.888
16.501


−2.218
1.891
16.501


−2.207
1.889
16.501


−2.195
1.885
16.501


−2.18
1.878
16.501


−2.162
1.867
16.501


−2.139
1.852
16.501


−2.111
1.832
16.501


−2.077
1.807
16.501


−2.037
1.777
16.501


−1.99
1.743
16.501


−1.934
1.702
16.501


−1.87
1.654
16.501


−1.797
1.601
16.501


−1.715
1.542
16.501


−1.624
1.478
16.501


−1.525
1.407
16.501


−1.42
1.335
16.501


−1.31
1.259
16.501


−1.196
1.182
16.501


−1.077
1.102
16.501


−0.953
1.021
16.501


−0.823
0.937
16.501


−0.689
0.852
16.501


−0.554
0.768
16.501


−0.418
0.685
16.501


−0.28
0.605
16.501


−0.142
0.526
16.501


−0.002
0.45
16.501


0.139
0.376
16.501


0.281
0.304
16.501


0.425
0.235
16.501


0.569
0.167
16.501


0.713
0.101
16.501


0.859
0.036
16.501


1
−0.025
16.501


1.138
−0.081
16.501


1.271
−0.133
16.501


1.401
−0.182
16.501


1.526
−0.226
16.501


1.647
−0.267
16.501


1.763
−0.303
16.501


1.876
−0.336
16.501


1.978
−0.365
16.501


2.071
−0.389
16.501


2.153
−0.409
16.501


2.231
−0.426
16.501


2.299
−0.441
16.501


2.351
−0.452
16.501


2.393
−0.46
16.501


2.424
−0.466
16.501


2.445
−0.477
16.501


2.452
−0.488
16.501


2.454
−0.496
16.501


2.454
−0.5
16.501


2.454
−0.503
16.501


2.454
−0.504
16.501


2.275
−0.975
18.552


2.275
−0.977
18.552


2.274
−0.981
18.552


2.27
−0.989
18.552


2.26
−0.998
18.552


2.237
−1.002
18.552


2.206
−1
18.552


2.164
−0.996
18.552


2.111
−0.992
18.552


2.043
−0.985
18.552


1.964
−0.976
18.552


1.881
−0.966
18.552


1.787
−0.953
18.552


1.683
−0.937
18.552


1.569
−0.917
18.552


1.45
−0.894
18.552


1.326
−0.867
18.552


1.198
−0.836
18.552


1.066
−0.801
18.552


0.931
−0.761
18.552


0.792
−0.716
18.552


0.65
−0.666
18.552


0.505
−0.61
18.552


0.361
−0.55
18.552


0.22
−0.484
18.552


0.081
−0.415
18.552


−0.056
−0.341
18.552


−0.192
−0.265
18.552


−0.327
−0.185
18.552


−0.46
−0.102
18.552


−0.592
−0.017
18.552


−0.722
0.071
18.552


−0.85
0.162
18.552


−0.977
0.254
18.552


−1.097
0.346
18.552


−1.212
0.436
18.552


−1.322
0.525
18.552


−1.426
0.612
18.552


−1.525
0.698
18.552


−1.619
0.781
18.552


−1.707
0.863
18.552


−1.787
0.939
18.552


−1.857
1.009
18.552


−1.92
1.073
18.552


−1.974
1.131
18.552


−2.019
1.181
18.552


−2.057
1.225
18.552


−2.089
1.262
18.552


−2.116
1.294
18.552


−2.136
1.322
18.552


−2.152
1.344
18.552


−2.163
1.362
18.552


−2.17
1.376
18.552


−2.175
1.388
18.552


−2.177
1.398
18.552


−2.175
1.406
18.552


−2.167
1.408
18.552


−2.157
1.407
18.552


−2.146
1.402
18.552


−2.132
1.395
18.552


−2.115
1.384
18.552


−2.092
1.37
18.552


−2.066
1.35
18.552


−2.034
1.325
18.552


−1.996
1.296
18.552


−1.951
1.262
18.552


−1.899
1.221
18.552


−1.838
1.174
18.552


−1.77
1.121
18.552


−1.692
1.062
18.552


−1.607
0.997
18.552


−1.513
0.927
18.552


−1.414
0.854
18.552


−1.311
0.779
18.552


−1.203
0.701
18.552


−1.091
0.622
18.552


−0.974
0.54
18.552


−0.851
0.456
18.552


−0.724
0.371
18.552


−0.596
0.288
18.552


−0.467
0.206
18.552


−0.337
0.125
18.552


−0.205
0.047
18.552


−0.073
−0.03
18.552


0.061
−0.105
18.552


0.196
−0.177
18.552


0.332
−0.248
18.552


0.469
−0.317
18.552


0.606
−0.384
18.552


0.745
−0.449
18.552


0.879
−0.51
18.552


1.01
−0.566
18.552


1.138
−0.618
18.552


1.262
−0.666
18.552


1.382
−0.71
18.552


1.498
−0.75
18.552


1.61
−0.785
18.552


1.718
−0.817
18.552


1.816
−0.844
18.552


1.905
−0.866
18.552


1.985
−0.885
18.552


2.06
−0.901
18.552


2.125
−0.915
18.552


2.176
−0.925
18.552


2.216
−0.932
18.552


2.246
−0.937
18.552


2.266
−0.948
18.552


2.273
−0.958
18.552


2.275
−0.966
18.552


2.275
−0.97
18.552


2.275
−0.973
18.552


2.275
−0.974
18.552


2.096
−1.385
20.603


2.096
−1.387
20.603


2.095
−1.391
20.603


2.091
−1.399
20.603


2.082
−1.408
20.603


2.059
−1.411
20.603


2.028
−1.408
20.603


1.987
−1.404
20.603


1.935
−1.399
20.603


1.868
−1.392
20.603


1.791
−1.383
20.603


1.708
−1.373
20.603


1.616
−1.36
20.603


1.513
−1.346
20.603


1.401
−1.328
20.603


1.283
−1.307
20.603


1.161
−1.283
20.603


1.035
−1.255
20.603


0.904
−1.221
20.603


0.77
−1.183
20.603


0.632
−1.138
20.603


0.491
−1.086
20.603


0.347
−1.027
20.603


0.207
−0.962
20.603


0.07
−0.892
20.603


−0.064
−0.817
20.603


−0.196
−0.738
20.603


−0.324
−0.655
20.603


−0.451
−0.569
20.603


−0.576
−0.48
20.603


−0.698
−0.387
20.603


−0.819
−0.292
20.603


−0.937
−0.194
20.603


−1.054
−0.093
20.603


−1.165
0.007
20.603


−1.27
0.105
20.603


−1.37
0.202
20.603


−1.463
0.297
20.603


−1.552
0.39
20.603


−1.635
0.481
20.603


−1.713
0.569
20.603


−1.783
0.652
20.603


−1.845
0.727
20.603


−1.899
0.796
20.603


−1.946
0.857
20.603


−1.986
0.911
20.603


−2.02
0.957
20.603


−2.047
0.996
20.603


−2.07
1.03
20.603


−2.088
1.058
20.603


−2.102
1.081
20.603


−2.111
1.1
20.603


−2.118
1.114
20.603


−2.122
1.126
20.603


−2.123
1.136
20.603


−2.121
1.143
20.603


−2.114
1.145
20.603


−2.104
1.141
20.603


−2.093
1.135
20.603


−2.081
1.126
20.603


−2.065
1.114
20.603


−2.045
1.097
20.603


−2.021
1.075
20.603


−1.992
1.048
20.603


−1.958
1.015
20.603


−1.919
0.977
20.603


−1.872
0.931
20.603


−1.818
0.878
20.603


−1.757
0.819
20.603


−1.688
0.753
20.603


−1.612
0.68
20.603


−1.527
0.601
20.603


−1.438
0.52
20.603


−1.345
0.436
20.603


−1.247
0.35
20.603


−1.144
0.262
20.603


−1.037
0.171
20.603


−0.924
0.08
20.603


−0.806
−0.014
20.603


−0.686
−0.105
20.603


−0.566
−0.195
20.603


−0.443
−0.283
20.603


−0.32
−0.368
20.603


−0.195
−0.451
20.603


−0.069
−0.53
20.603


0.059
−0.607
20.603


0.189
−0.681
20.603


0.32
−0.751
20.603


0.453
−0.819
20.603


0.587
−0.884
20.603


0.718
−0.944
20.603


0.847
−0.998
20.603


0.972
−1.048
20.603


1.095
−1.093
20.603


1.214
−1.134
20.603


1.329
−1.17
20.603


1.44
−1.203
20.603


1.547
−1.232
20.603


1.644
−1.257
20.603


1.732
−1.278
20.603


1.811
−1.296
20.603


1.885
−1.312
20.603


1.949
−1.325
20.603


1.998
−1.335
20.603


2.038
−1.343
20.603


2.067
−1.349
20.603


2.087
−1.359
20.603


2.094
−1.37
20.603


2.096
−1.377
20.603


2.096
−1.381
20.603


2.096
−1.383
20.603


2.096
−1.384
20.603









It will also be appreciated that the exemplary airfoil(s) disclosed in the above Table 1 may be scaled up or down geometrically for use in other similar compressor designs. Consequently, the coordinate values set forth in the Table 1 may be scaled upwardly or downwardly such that the airfoil 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 multiplied or divided by a constant.
While various embodiments are described herein, it will be appreciated from the specification that various combinations of elements, variations or improvements therein may be made by those skilled in the art, and are within the scope of the invention.

## Claims

1. An article of manufacture, the article having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

2. An article of manufacture according to claim 1, wherein the article comprises an airfoil.

3. An article of manufacture according to claim 2, wherein said article shape lies in an envelope within ±0.160 inches in a direction normal to any article surface location.

4. An article of manufacture according to claim 1, wherein the article comprises an airfoil variable stator vane.

5. A compressor comprising a compressor wheel having a plurality of articles of manufacture, each of said articles of manufacture including an airfoil having an airfoil shape, said airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define the airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

6. A compressor comprising a compressor wheel having a plurality of articles of manufacture, each of said articles of manufacture including an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1, wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape, the X and Y distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down rotor blade airfoil.

7. A compressor according to claim 6, wherein said airfoil shape lies in an envelope within ±0.160 inches in a direction normal to any airfoil surface location.