# 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 smoothing 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: 11/586,060, 11/586,049, 11/586050, 11/586,051, 11/586,052, 11/586,046, 11/586,053, 11/586,054, 11/586,085, 11/586,055, 11/586,088, 11/586,086, 11/586,045, 11/586,087, 11/586,059, 11/586,092, 11/586,090, 11/586,089 and 11/586,091 each filed on Oct. 25, 2006; and the following GE commonly assigned applications: 11/591,695, 11/591,694, 11/591,693 and 11/691,692 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 combustor, 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 3rd stage airfoil variable stator blade. 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 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 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 3rd stage airfoil variable stator blade.









TABLE I





X-LOC
Y-LOC
Z-LOC

















2.08
−2.026
0.005


2.079
−2.028
0.005


2.077
−2.032
0.005


2.071
−2.039
0.005


2.06
−2.046
0.005


2.036
−2.047
0.005


2.005
−2.038
0.005


1.964
−2.024
0.005


1.913
−2.007
0.005


1.846
−1.985
0.005


1.77
−1.958
0.005


1.688
−1.93
0.005


1.596
−1.897
0.005


1.495
−1.86
0.005


1.384
−1.819
0.005


1.268
−1.774
0.005


1.147
−1.726
0.005


1.023
−1.674
0.005


0.893
−1.62
0.005


0.76
−1.561
0.005


0.623
−1.498
0.005


0.482
−1.43
0.005


0.337
−1.357
0.005


0.194
−1.281
0.005


0.053
−1.203
0.005


−0.087
−1.121
0.005


−0.224
−1.037
0.005


−0.36
−0.948
0.005


−0.494
−0.856
0.005


−0.625
−0.761
0.005


−0.753
−0.662
0.005


−0.878
−0.559
0.005


−1
−0.452
0.005


−1.119
−0.342
0.005


−1.231
−0.232
0.005


−1.335
−0.123
0.005


−1.432
−0.015
0.005


−1.522
0.092
0.005


−1.605
0.197
0.005


−1.683
0.3
0.005


−1.754
0.4
0.005


−1.816
0.495
0.005


−1.87
0.582
0.005


−1.915
0.661
0.005


−1.954
0.733
0.005


−1.985
0.796
0.005


−2.009
0.851
0.005


−2.029
0.898
0.005


−2.044
0.938
0.005


−2.055
0.971
0.005


−2.061
0.999
0.005


−2.063
1.02
0.005


−2.063
1.037
0.005


−2.061
1.05
0.005


−2.057
1.06
0.005


−2.051
1.066
0.005


−2.044
1.07
0.005


−2.034
1.071
0.005


−2.021
1.07
0.005


−2.006
1.066
0.005


−1.987
1.057
0.005


−1.963
1.045
0.005


−1.934
1.026
0.005


−1.901
1.002
0.005


−1.863
0.972
0.005


−1.818
0.937
0.005


−1.766
0.894
0.005


−1.707
0.843
0.005


−1.64
0.785
0.005


−1.566
0.719
0.005


−1.485
0.646
0.005


−1.396
0.566
0.005


−1.303
0.483
0.005


−1.207
0.396
0.005


−1.106
0.306
0.005


−1.001
0.213
0.005


−0.892
0.117
0.005


−0.779
0.017
0.005


−0.661
−0.085
0.005


−0.542
−0.186
0.005


−0.422
−0.285
0.005


−0.301
−0.383
0.005


−0.179
−0.48
0.005


−0.056
−0.576
0.005


0.068
−0.671
0.005


0.192
−0.765
0.005


0.317
−0.858
0.005


0.443
−0.95
0.005


0.57
−1.041
0.005


0.697
−1.131
0.005


0.821
−1.216
0.005


0.942
−1.298
0.005


1.059
−1.376
0.005


1.172
−1.449
0.005


1.282
−1.519
0.005


1.388
−1.585
0.005


1.49
−1.647
0.005


1.588
−1.706
0.005


1.678
−1.759
0.005


1.759
−1.806
0.005


1.831
−1.847
0.005


1.899
−1.886
0.005


1.958
−1.918
0.005


2.003
−1.944
0.005


2.04
−1.964
0.005


2.067
−1.979
0.005


2.081
−1.997
0.005


2.083
−2.01
0.005


2.082
−2.018
0.005


2.081
−2.022
0.005


2.08
−2.024
0.005


2.08
−2.025
0.005


2.198
−1.391
1.544


2.197
−1.392
1.544


2.195
−1.396
1.544


2.19
−1.402
1.544


2.179
−1.409
1.544


2.156
−1.41
1.544


2.126
−1.402
1.544


2.087
−1.39
1.544


2.038
−1.375
1.544


1.974
−1.355
1.544


1.9
−1.332
1.544


1.822
−1.307
1.544


1.734
−1.279
1.544


1.636
−1.248
1.544


1.528
−1.212
1.544


1.416
−1.175
1.544


1.3
−1.134
1.544


1.178
−1.092
1.544


1.053
−1.047
1.544


0.922
−0.999
1.544


0.788
−0.948
1.544


0.649
−0.893
1.544


0.506
−0.835
1.544


0.364
−0.775
1.544


0.223
−0.713
1.544


0.083
−0.649
1.544


−0.056
−0.582
1.544


−0.194
−0.513
1.544


−0.33
−0.441
1.544


−0.465
−0.366
1.544


−0.597
−0.287
1.544


−0.728
−0.206
1.544


−0.857
−0.121
1.544


−0.983
−0.032
1.544


−1.103
0.056
1.544


−1.215
0.145
1.544


−1.32
0.234
1.544


−1.419
0.323
1.544


−1.512
0.411
1.544


−1.598
0.498
1.544


−1.678
0.584
1.544


−1.748
0.665
1.544


−1.81
0.74
1.544


−1.863
0.81
1.544


−1.908
0.873
1.544


−1.945
0.929
1.544


−1.975
0.977
1.544


−1.998
1.019
1.544


−2.017
1.055
1.544


−2.031
1.086
1.544


−2.04
1.111
1.544


−2.044
1.131
1.544


−2.046
1.147
1.544


−2.045
1.16
1.544


−2.042
1.17
1.544


−2.037
1.176
1.544


−2.031
1.18
1.544


−2.022
1.183
1.544


−2.009
1.184
1.544


−1.994
1.182
1.544


−1.975
1.178
1.544


−1.95
1.17
1.544


−1.921
1.157
1.544


−1.886
1.139
1.544


−1.844
1.117
1.544


−1.796
1.09
1.544


−1.74
1.058
1.544


−1.677
1.019
1.544


−1.605
0.973
1.544


−1.525
0.922
1.544


−1.438
0.865
1.544


−1.342
0.802
1.544


−1.242
0.736
1.544


−1.138
0.668
1.544


−1.03
0.596
1.544


−0.918
0.522
1.544


−0.801
0.445
1.544


−0.681
0.365
1.544


−0.556
0.283
1.544


−0.431
0.201
1.544


−0.305
0.12
1.544


−0.179
0.04
1.544


−0.053
−0.04
1.544


0.074
−0.12
1.544


0.2
−0.199
1.544


0.327
−0.279
1.544


0.454
−0.358
1.544


0.581
−0.436
1.544


0.708
−0.514
1.544


0.836
−0.591
1.544


0.961
−0.665
1.544


1.081
−0.736
1.544


1.197
−0.804
1.544


1.309
−0.869
1.544


1.418
−0.93
1.544


1.522
−0.988
1.544


1.622
−1.044
1.544


1.718
−1.097
1.544


1.806
−1.145
1.544


1.885
−1.187
1.544


1.955
−1.225
1.544


2.021
−1.26
1.544


2.078
−1.29
1.544


2.122
−1.313
1.544


2.158
−1.332
1.544


2.184
−1.346
1.544


2.198
−1.363
1.544


2.201
−1.375
1.544


2.2
−1.383
1.544


2.199
−1.387
1.544


2.199
−1.389
1.544


2.198
−1.39
1.544


2.118
−0.761
3.082


2.117
−0.763
3.082


2.116
−0.767
3.082


2.111
−0.773
3.082


2.1
−0.78
3.082


2.078
−0.782
3.082


2.05
−0.774
3.082


2.012
−0.764
3.082


1.964
−0.751
3.082


1.902
−0.735
3.082


1.831
−0.715
3.082


1.756
−0.694
3.082


1.67
−0.669
3.082


1.576
−0.642
3.082


1.472
−0.612
3.082


1.364
−0.58
3.082


1.251
−0.546
3.082


1.133
−0.509
3.082


1.011
−0.47
3.082


0.885
−0.429
3.082


0.755
−0.385
3.082


0.62
−0.339
3.082


0.481
−0.288
3.082


0.343
−0.236
3.082


0.206
−0.182
3.082


0.069
−0.126
3.082


−0.066
−0.068
3.082


−0.2
−0.007
3.082


−0.333
0.056
3.082


−0.465
0.123
3.082


−0.595
0.192
3.082


−0.724
0.265
3.082


−0.85
0.341
3.082


−0.974
0.421
3.082


−1.092
0.501
3.082


−1.202
0.582
3.082


−1.306
0.663
3.082


−1.404
0.743
3.082


−1.495
0.824
3.082


−1.581
0.904
3.082


−1.66
0.984
3.082


−1.731
1.059
3.082


−1.792
1.129
3.082


−1.845
1.194
3.082


−1.89
1.253
3.082


−1.927
1.305
3.082


−1.956
1.351
3.082


−1.98
1.391
3.082


−2
1.425
3.082


−2.013
1.454
3.082


−2.022
1.478
3.082


−2.027
1.497
3.082


−2.029
1.512
3.082


−2.028
1.524
3.082


−2.025
1.534
3.082


−2.021
1.54
3.082


−2.015
1.544
3.082


−2.006
1.547
3.082


−1.995
1.549
3.082


−1.98
1.548
3.082


−1.962
1.544
3.082


−1.938
1.537
3.082


−1.909
1.526
3.082


−1.875
1.511
3.082


−1.834
1.491
3.082


−1.787
1.468
3.082


−1.733
1.438
3.082


−1.67
1.404
3.082


−1.6
1.364
3.082


−1.521
1.318
3.082


−1.435
1.268
3.082


−1.341
1.212
3.082


−1.243
1.154
3.082


−1.14
1.093
3.082


−1.034
1.03
3.082


−0.923
0.964
3.082


−0.808
0.896
3.082


−0.689
0.826
3.082


−0.566
0.753
3.082


−0.443
0.681
3.082


−0.319
0.609
3.082


−0.195
0.538
3.082


−0.071
0.466
3.082


0.053
0.395
3.082


0.176
0.323
3.082


0.3
0.252
3.082


0.424
0.181
3.082


0.548
0.11
3.082


0.673
0.039
3.082


0.797
−0.031
3.082


0.918
−0.098
3.082


1.035
−0.162
3.082


1.148
−0.224
3.082


1.257
−0.283
3.082


1.362
−0.339
3.082


1.463
−0.392
3.082


1.56
−0.443
3.082


1.653
−0.491
3.082


1.738
−0.535
3.082


1.815
−0.574
3.082


1.883
−0.608
3.082


1.947
−0.64
3.082


2.002
−0.668
3.082


2.045
−0.689
3.082


2.079
−0.706
3.082


2.104
−0.719
3.082


2.118
−0.735
3.082


2.121
−0.746
3.082


2.12
−0.754
3.082


2.119
−0.758
3.082


2.119
−0.759
3.082


2.119
−0.76
3.082


2.082
−0.346
4.621


2.081
−0.348
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−1.91
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10.776


−1.904
1.125
10.776


−1.895
1.126
10.776


−1.884
1.124
10.776


−1.871
1.12
10.776


−1.855
1.113
10.776


−1.834
1.103
10.776


−1.809
1.088
10.776


−1.78
1.069
10.776


−1.745
1.047
10.776


−1.704
1.02
10.776


−1.656
0.988
10.776


−1.601
0.951
10.776


−1.538
0.908
10.776


−1.468
0.861
10.776


−1.39
0.81
10.776


−1.305
0.754
10.776


−1.215
0.696
10.776


−1.121
0.637
10.776


−1.023
0.577
10.776


−0.92
0.515
10.776


−0.812
0.453
10.776


−0.7
0.39
10.776


−0.583
0.326
10.776


−0.466
0.264
10.776


−0.348
0.203
10.776


−0.229
0.144
10.776


−0.11
0.086
10.776


0.01
0.028
10.776


0.131
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10.776


0.251
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10.776


0.373
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10.776


0.494
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10.776


0.616
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10.776


0.739
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10.776


0.858
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10.776


0.973
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10.776


1.084
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10.776


1.191
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10.776


1.295
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10.776


1.395
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10.776


1.49
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10.776


1.582
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10.776


1.666
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10.776


1.741
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10.776


1.808
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10.776


1.871
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10.776


1.925
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10.776


1.967
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10.776


2.001
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10.776


2.026
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10.776


2.043
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10.776


2.048
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10.776


2.049
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10.776


2.049
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10.776


2.049
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10.776


2.048
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10.776


2.099
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12.314


2.098
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12.314


2.097
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12.314


2.092
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12.314


2.082
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12.314


2.062
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12.314


2.035
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12.314


1.999
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12.314


1.953
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12.314


1.895
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12.314


1.827
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12.314


1.754
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12.314


1.673
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12.314


1.583
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12.314


1.484
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12.314


1.381
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12.314


1.273
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12.314


1.161
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12.314


1.044
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12.314


0.924
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12.314


0.799
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12.314


0.671
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12.314


0.538
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12.314


0.407
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12.314


0.276
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12.314


0.146
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12.314


0.017
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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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0.773
12.314


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0.786
12.314


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0.797
12.314


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0.807
12.314


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0.813
12.314


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0.816
12.314


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0.815
12.314


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0.811
12.314


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0.806
12.314


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0.797
12.314


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0.785
12.314


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0.768
12.314


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12.314


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0.722
12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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12.314


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0.341
12.314


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12.314


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0.212
12.314


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12.314


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0.08
12.314


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12.314


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12.314


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12.314


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12.314


−0.213
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12.314


−0.093
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12.314


0.028
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12.314


0.15
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12.314


0.272
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12.314


0.395
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12.314


0.518
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12.314


0.642
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12.314


0.766
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12.314


0.887
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12.314


1.003
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12.314


1.116
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12.314


1.225
−0.891
12.314


1.33
−0.931
12.314


1.432
−0.97
12.314


1.529
−1.005
12.314


1.622
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12.314


1.708
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12.314


1.784
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12.314


1.852
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12.314


1.916
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12.314


1.972
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12.314


2.015
−1.174
12.314


2.049
−1.186
12.314


2.075
−1.194
12.314


2.093
−1.203
12.314


2.099
−1.213
12.314


2.1
−1.22
12.314


2.1
−1.223
12.314


2.1
−1.225
12.314


2.099
−1.226
12.314


2.213
−1.677
13.853


2.212
−1.679
13.853


2.211
−1.682
13.853


2.205
−1.688
13.853


2.194
−1.692
13.853


2.173
−1.689
13.853


2.145
−1.682
13.853


2.108
−1.672
13.853


2.061
−1.66
13.853


2.001
−1.644
13.853


1.931
−1.626
13.853


1.857
−1.606
13.853


1.773
−1.582
13.853


1.681
−1.556
13.853


1.579
−1.527
13.853


1.473
−1.495
13.853


1.362
−1.462
13.853


1.247
−1.426
13.853


1.128
−1.387
13.853


1.005
−1.346
13.853


0.878
−1.302
13.853


0.747
−1.254
13.853


0.612
−1.203
13.853


0.477
−1.15
13.853


0.344
−1.094
13.853


0.212
−1.036
13.853


0.081
−0.976
13.853


−0.049
−0.913
13.853


−0.177
−0.846
13.853


−0.304
−0.777
13.853


−0.429
−0.705
13.853


−0.552
−0.63
13.853


−0.672
−0.552
13.853


−0.791
−0.471
13.853


−0.903
−0.39
13.853


−1.009
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13.853


−1.109
−0.228
13.853


−1.203
−0.148
13.853


−1.292
−0.068
13.853


−1.376
0.011
13.853


−1.454
0.088
13.853


−1.524
0.161
13.853


−1.586
0.229
13.853


−1.64
0.291
13.853


−1.686
0.346
13.853


−1.725
0.395
13.853


−1.758
0.437
13.853


−1.785
0.474
13.853


−1.807
0.505
13.853


−1.825
0.531
13.853


−1.838
0.552
13.853


−1.847
0.569
13.853


−1.853
0.582
13.853


−1.857
0.594
13.853


−1.858
0.603
13.853


−1.856
0.61
13.853


−1.849
0.612
13.853


−1.84
0.61
13.853


−1.83
0.605
13.853


−1.817
0.598
13.853


−1.802
0.587
13.853


−1.782
0.573
13.853


−1.758
0.554
13.853


−1.729
0.531
13.853


−1.695
0.502
13.853


−1.655
0.469
13.853


−1.608
0.43
13.853


−1.554
0.384
13.853


−1.493
0.333
13.853


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0.276
13.853


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0.214
13.853


−1.261
0.147
13.853


−1.171
0.079
13.853


−1.077
0.009
13.853


−0.978
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13.853


−0.873
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13.853


−0.764
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13.853


−0.65
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13.853


−0.53
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13.853


−0.409
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13.853


−0.288
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13.853


−0.165
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13.853


−0.042
−0.642
13.853


0.082
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13.853


0.207
−0.775
13.853


0.332
−0.84
13.853


0.458
−0.904
13.853


0.584
−0.967
13.853


0.711
−1.028
13.853


0.839
−1.089
13.853


0.962
−1.146
13.853


1.082
−1.201
13.853


1.198
−1.252
13.853


1.31
−1.301
13.853


1.418
−1.347
13.853


1.522
−1.391
13.853


1.623
−1.432
13.853


1.719
−1.47
13.853


1.807
−1.504
13.853


1.886
−1.534
13.853


1.956
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13.853


2.023
−1.585
13.853


2.08
−1.606
13.853


2.125
−1.622
13.853


2.16
−1.635
13.853


2.187
−1.644
13.853


2.206
−1.653
13.853


2.213
−1.662
13.853


2.214
−1.67
13.853


2.214
−1.673
13.853


2.214
−1.675
13.853


2.213
−1.676
13.853


2.238
−2.038
15.392


2.238
−2.04
15.392


2.236
−2.043
15.392


2.23
−2.049
15.392


2.218
−2.052
15.392


2.196
−2.047
15.392


2.167
−2.038
15.392


2.128
−2.027
15.392


2.08
−2.014
15.392


2.018
−1.995
15.392


1.946
−1.973
15.392


1.869
−1.949
15.392


1.783
−1.921
15.392


1.688
−1.889
15.392


1.584
−1.853
15.392


1.475
−1.814
15.392


1.362
−1.772
15.392


1.245
−1.727
15.392


1.124
−1.678
15.392


0.999
−1.626
15.392


0.871
−1.57
15.392


0.738
−1.51
15.392


0.602
−1.445
15.392


0.468
−1.378
15.392


0.334
−1.309
15.392


0.202
−1.237
15.392


0.071
−1.163
15.392


−0.059
−1.087
15.392


−0.187
−1.007
15.392


−0.313
−0.926
15.392


−0.437
−0.841
15.392


−0.56
−0.753
15.392


−0.68
−0.663
15.392


−0.797
−0.569
15.392


−0.908
−0.475
15.392


−1.013
−0.381
15.392


−1.111
−0.289
15.392


−1.204
−0.197
15.392


−1.29
−0.107
15.392


−1.371
−0.019
15.392


−1.446
0.067
15.392


−1.513
0.148
15.392


−1.573
0.223
15.392


−1.624
0.291
15.392


−1.668
0.352
15.392


−1.706
0.405
15.392


−1.737
0.451
15.392


−1.762
0.491
15.392


−1.783
0.525
15.392


−1.8
0.553
15.392


−1.812
0.576
15.392


−1.82
0.594
15.392


−1.826
0.608
15.392


−1.829
0.62
15.392


−1.831
0.63
15.392


−1.828
0.637
15.392


−1.821
0.638
15.392


−1.812
0.634
15.392


−1.802
0.628
15.392


−1.789
0.62
15.392


−1.774
0.608
15.392


−1.755
0.591
15.392


−1.731
0.569
15.392


−1.703
0.542
15.392


−1.67
0.51
15.392


−1.632
0.472
15.392


−1.586
0.427
15.392


−1.534
0.376
15.392


−1.474
0.317
15.392


−1.407
0.253
15.392


−1.331
0.182
15.392


−1.248
0.106
15.392


−1.16
0.027
15.392


−1.067
−0.053
15.392


−0.97
−0.135
15.392


−0.867
−0.219
15.392


−0.759
−0.304
15.392


−0.646
−0.39
15.392


−0.527
−0.477
15.392


−0.407
−0.562
15.392


−0.285
−0.645
15.392


−0.163
−0.726
15.392


−0.039
−0.806
15.392


0.085
−0.885
15.392


0.21
−0.964
15.392


0.335
−1.041
15.392


0.46
−1.118
15.392


0.586
−1.194
15.392


0.713
−1.268
15.392


0.841
−1.342
15.392


0.964
−1.412
15.392


1.085
−1.478
15.392


1.202
−1.54
15.392


1.315
−1.599
15.392


1.424
−1.654
15.392


1.53
−1.706
15.392


1.632
−1.755
15.392


1.73
−1.801
15.392


1.82
−1.841
15.392


1.901
−1.877
15.392


1.973
−1.908
15.392


2.041
−1.936
15.392


2.1
−1.96
15.392


2.146
−1.979
15.392


2.183
−1.993
15.392


2.21
−2.004
15.392


2.23
−2.013
15.392


2.238
−2.022
15.392


2.239
−2.03
15.392


2.239
−2.034
15.392


2.239
−2.036
15.392


2.239
−2.037
15.392









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 according to claim 5, wherein the article of manufacture comprises an airfoil variable stator vane.

7. 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 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.

8. A compressor according to claim 7, wherein the article of manufacture comprises an airfoil variable stator vane.

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