# Patent

## Title
Rotor blade for a ninth phase of a compressor

## Abstract

The invention relates to a blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, the blade having a profile which can be identified by having a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, the blade also comprising a thickening, substantially parallel to a base portion of the blade itself, fixable to said rotor, said thickening being substantially situated half-way up the blade and being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

## Background
BACKGROUND OF THE INVENTION
The present invention relates to a blade of a rotor of a ninth phase of a compressor.
DESCRIPTION
More specifically, the invention relates to a blade of a rotor having a high aerodynamic efficiency of a ninth phase of a compressor.
Compressors normally pressurize in their interior air removed from the outside.
The fluid penetrates the compressor through a series of inlet ducts.
In these channels, the gas has low pressure and low temperature characteristics, whereas as it passes through the compressor, the gas is compressed and its temperature increases.
In order to increase the efficiency, the compressor is normally divided into various phases, each of which has a rotor and a stator respectively equipped with a series of blades.
In recent years, technologically advanced compressors have been further improved, obtaining an increased improvement in efficiency, operating in particular on the aerodynamic conditions.
The geometric configuration of the blades in fact significantly influences the aerodynamic efficiency.
This depends on the fact that the geometric characteristics of the blade cause a distribution of the relative velocities in the fluid, consequently influencing the distribution of the limit layers along the walls and, ultimately, losses due to friction.
In particular, in the case of rotor blades of a ninth phase of a compressor an extremely high efficiency is required, at the same time maintaining an appropriate aerodynamic and mechanical load.
In accordance with one exemplary aspect of the present invention, a blade of a rotor of a ninth phase of a compressor avoids or in any case reduces resonance problems due to flexural vibrations which reduce the life of the component, and at the same time allows a high aerodynamic efficiency.
In accordance with another exemplary aspect of the present invention, a rotor of a ninth phase of a compressor allows a high aerodynamic efficiency and at the same time allows a high reliability of the compressor to be obtained with a consequent increase in the power of the turbine itself with the same compressor dimensions.
These characteristics and others according to the present invention are achieved by providing a rotor blade of a ninth phase of a compressor as specified in the claims.



BRIEF DESCRIPTION OF THE DRAWINGS
The characteristics and advantages of a rotor blade of a ninth phase of a compressor according to the present invention will appear more evident from the following illustrative and non-limiting description, referring to the enclosed schematic drawings in which:
FIG. 1 is a raised view of a rotor blade of a compressor produced with an aerodynamic profile according to the present invention;
FIG. 2 is a raised view of the opposite side of the blade of FIG. 1; and
FIG. 3 is a diagram of the maximum thickness trend of a blade according to the present invention, with respect to its height.



DETAILED DESCRIPTION OF THE INVENTION
With reference to the figures, a blade 10 is provided of a rotor of a ninth phase of a compressor.
Said blade 10 is defined by means of coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, not shown.
The profile of the blade 10 is identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis.
The profile of said blade 10 comprises a first substantially concave surface 3, which is pressurized, and a second substantially convex surface 5 which is in depression and opposite the first.
The two surfaces 3, 5 are continuous and joined to each other, and together form the profile of said blade 10.
At a base portion 12, commonly called “foot” of the blade 10, according to the known art there is a connecting joint with the aerodynamic profile of the blade 10 itself, said base portion 12 being suitable for being fixed to said rotor of said compressor.
Said blade 10 comprises a thickening 30, i.e. a prolonged portion having a greater thickness with respect to the adjacent portions, which is substantially parallel to said base portion 12 so as to shift the resonance frequencies of said blade 10 outside a functioning frequency range of the rotor itself, thus reducing or in any case avoiding problems of instability and vibrations of the blade 10 and rotor.
This advantageously leads to an increase in both the useful life and reliability of the rotor and compressor itself.
Said thickening 30 relates to at least one section or closed curve, and is also situated half-way up the blade 10.
In other words, said thickening 30 confers a dynamic behaviour to said blade which is such as to have flexural frequencies which fall outside a functioning velocity range of the rotor of said compressor and consequently such that there is no intensification of the maximum flexural deformation of the blade during the functioning of the compressor.
This consequently leads to a higher performance of the compressor, of the rotor and a longer useful life of its components, as problems of resonance such as those described above are avoided.
The clearances and tolerances of the blade and stator can therefore be dimensioned so as to further increase the performances of the compressor itself.
This is possible as the blade 10 is prevented, upon deforming, from causing a contact and relative friction against the relative stator.
In particular, each closed curve has a maximum thickness determined by the maximum distance between said first surface 3 and said second surface 5.
Said maximum surface of each closed curve, along the height of the blade 10, moving towards a free end 14 of the blade 10, has first a decreasing and then an increasing trend, followed again by a decreasing and finally increasing trend, with two different slopes, said blade 10 comprising a further thickening substantially parallel to said base portion 12 and situated in particular close to said free end 14.
For example, the variation in the trend of the maximum thickness is shown in FIG. 3, in which it is compared with the maximum thickness trend of a blade according to the known art. In particular, in FIG. 3, the abscissa indicates the height of the blade 10, whereas the ordinate represents the maximum thickness of the blade 10, adimensionalized by putting the thickness in correspondence with the foot of the blade equal to 1. In the diagram shown in FIG. 3, the lower line represents the maximum thickness trend of a blade according to the known art, whereas the upper line shows the trend of the maximum thickness of the blade according to the present invention.
Along the height of the blade 10 in the direction of a free end 14 of the blade 10, said maximum thickness preferably has a trend which can be described by four different mathematical functions, identifying four different regions of the blade.
In the first region, that closest to the blade 10, up to a height equal to 45% of the height of the blade, the maximum thickness trend can be described by a polynomial function of the fourth degree (first decreasing and subsequently increasing) and in particular said polynomial function is:

Tmax=−34.522*h4+36.4*h3−8.4113*h2−0.7259*h+0.9961

    
    
        wherein h represents the percentage of the height of the blade 10, and wherein Tmax is the maximum adimensionalized thickness relating to that closed curve corresponding to that percentage of the height of the blade 10.
    
    


In the subsequent region, ranging from 45% to 58% of the height of the blade 10, the thickness varies according to the linear function (decreasing):

Tmax=−1.3509*h+1.4459

Therefore, between 58% and 86% of the height of the blade 10, the thickness trend is represented by the linear function (increasing):

Tmax=0.2074*h+0.5443

Finally, between 86% and the free end 14 of the blade, the maximum thickness varies according to the linear function (increasing):

Tmax=0.9058*h−0.0518

The profile of each blade 10 was also suitably shaped to be able to maintain the same efficiency at high levels.
The aerodynamic profile of each blade 10 is preferably defined by means of a series of closed curves whose coordinates are defined with respect to a Cartesian reference system X, Y, Z, wherein the axis Z is a radial axis intersecting the central axis of the turbine, and said closed curves lying at distances Z from the central axis are defined according to Table I, whose values, expressed in millimeters, refer to an aerodynamic profile at room temperature, in particular 25° C.









TABLE 1





X
Y
Z

















−8.852
9.902
255.999


−8.847
9.904
255.999


−8.835
9.905
255.999


−8.812
9.901
255.999


−8.771
9.880
255.999


−8.717
9.833
255.999


−8.632
9.734
255.999


−8.533
9.594
255.999


−8.410
9.400
255.999


−8.263
9.152
255.999


−8.080
8.826
255.999


−7.871
8.449
255.999


−7.643
8.050
255.999


−7.382
7.603
255.999


−7.086
7.110
255.999


−6.751
6.573
255.999


−6.390
6.019
255.999


−6.005
5.448
255.999


−5.593
4.860
255.999


−5.155
4.256
255.999


−4.688
3.638
255.999


−4.190
3.006
255.999


−3.660
2.364
255.999


−3.096
1.711
255.999


−2.520
1.069
255.999


−1.933
0.30278
255.999


−1.338
−0.189
255.999


−0.735
−0.806
255.999


−0.126
−1.417
255.999


0.33958
−2.023
255.999


1.108
−2.624
255.999


1.732
−3.219
255.999


2.362
−3.809
255.999


2.995
−4.395
255.999


3.631
−4.978
255.999


4.249
−5.538
255.999


4.849
−6.075
255.999


5.432
−6.588
255.999


5.998
−7.077
255.999


6.545
−7.543
255.999


7.075
−7.986
255.999


7.586
−8.405
255.999


8.056
−8.784
255.999


8.485
−9.124
255.999


8.871
−9.424
255.999


9.214
−9.685
255.999


9.515
−9.908
255.999


9.771
−10.093
255.999


9.992
−10.249
255.999


10.179
−10.379
255.999


10.332
−10.485
255.999


10.426
−10.600
255.999


10.461
−10.708
255.999


10.465
−10.793
255.999


10.452
−10.864
255.999


10.432
−10.917
255.999


10.411
−10.955
255.999


10.385
−10.991
255.999


10.343
−11.034
255.999


10.282
−11.077
255.999


10.199
−11.110
255.999


10.081
−11.119
255.999


9.933
−11.073
255.999


9.765
−10.976
255.999


9.561
−10.857
255.999


9.318
−10.717
255.999


9.034
−10.552
255.999


8.697
−10.359
255.999


8.308
−10.137
255.999


7.867
−9.884
255.999


7.376
−9.600
255.999


6.835
−9.282
255.999


6.245
−8.931
255.999


5.633
−8.559
255.999


4.999
−8.165
255.999


4.344
−7.748
255.999


3.670
−7.305
255.999


2.977
−6.837
255.999


2.267
−6.341
255.999


1.543
−5.816
255.999


0.57639
−5.280
255.999


0.08958
−4.730
255.999


−0.558
−4.165
255.999


−1.230
−3.583
255.999


−1.886
−2.983
255.999


−2.526
−2.366
255.999


−3.146
−1.727
255.999


−3.744
−1.064
255.999


−4.317
−0.373
255.999


−4.864
0.24028
255.999


−5.383
1.085
255.999


−5.861
1.816
255.999


−6.301
2.535
255.999


−6.704
3.242
255.999


−7.070
3.934
255.999


−7.401
4.611
255.999


−7.697
5.271
255.999


−7.962
5.912
255.999


−8.194
6.533
255.999


−8.387
7.104
255.999


−8.547
7.623
255.999


−8.675
8.088
255.999


−8.783
8.528
255.999


−8.864
8.911
255.999


−8.914
9.209
255.999


−8.940
9.449
255.999


−8.945
9.630
255.999


−8.932
9.765
255.999


−8.911
9.837
255.999


−8.887
9.878
255.999


−8.869
9.894
255.999


−8.858
9.900
255.999


−8.675
9.767
258.001


−8.669
9.769
258.001


−8.658
9.770
258.001


−8.635
9.767
258.001


−8.593
9.746
258.001


−8.538
9.700
258.001


−8.452
9.604
258.001


−8.349
9.465
258.001


−8.222
9.274
258.001


−8.069
9.031
258.001


−7.877
8.711
258.001


−7.657
8.340
258.001


−7.419
7.947
258.001


−7.147
7.508
258.001


−6.840
7.022
258.001


−6.494
6.493
258.001


−6.123
5.948
258.001


−5.726
5.385
258.001


−5.304
4.805
258.001


−4.855
4.211
258.001


−4.377
3.601
258.001


−3.871
2.978
258.001


−3.333
2.342
258.001


−2.766
1.694
258.001


−2.187
1.055
258.001


−1.600
0.29514
258.001


−1.004
−0.198
258.001


−0.402
−0.814
258.001


0.14236
−1.425
258.001


0.56736
−2.031
258.001


1.433
−2.634
258.001


2.053
−3.232
258.001


2.677
−3.827
258.001


3.304
−4.418
258.001


3.933
−5.006
258.001


4.545
−5.571
258.001


5.139
−6.113
258.001


5.715
−6.632
258.001


6.274
−7.127
258.001


6.815
−7.600
258.001


7.337
−8.049
258.001


7.841
−8.476
258.001


8.305
−8.861
258.001


8.728
−9.206
258.001


9.109
−9.512
258.001


9.448
−9.778
258.001


9.744
−10.005
258.001


9.997
−10.194
258.001


10.215
−10.354
258.001


10.399
−10.486
258.001


10.552
−10.594
258.001


10.671
−10.684
258.001


10.731
−10.780
258.001


10.749
−10.863
258.001


10.744
−10.934
258.001


10.727
−10.988
258.001


10.707
−11.026
258.001


10.680
−11.062
258.001


10.636
−11.102
258.001


10.570
−11.137
258.001


10.482
−11.152
258.001


10.366
−11.127
258.001


10.233
−11.049
258.001


10.067
−10.949
258.001


9.866
−10.828
258.001


9.626
−10.684
258.001


9.346
−10.517
258.001


9.013
−10.321
258.001


8.629
−10.094
258.001


8.194
−9.837
258.001


7.710
−9.547
258.001


7.176
−9.224
258.001


6.594
−8.867
258.001


5.990
−8.489
258.001


5.364
−8.089
258.001


4.718
−7.666
258.001


4.052
−7.219
258.001


3.368
−6.746
258.001


2.667
−6.245
258.001


1.952
−5.716
258.001


1.247
−5.175
258.001


0.38472
−4.623
258.001


−0.127
−4.057
258.001


−0.794
−3.477
258.001


−1.448
−2.882
258.001


−2.087
−2.272
258.001


−2.710
−1.644
258.001


−3.314
−0.995
258.001


−3.895
−0.323
258.001


−4.454
0.25903
258.001


−4.991
1.094
258.001


−5.485
1.807
258.001


−5.940
2.511
258.001


−6.356
3.203
258.001


−6.736
3.884
258.001


−7.080
4.549
258.001


−7.389
5.198
258.001


−7.668
5.828
258.001


−7.915
6.439
258.001


−8.123
7.002
258.001


−8.297
7.513
258.001


−8.438
7.971
258.001


−8.559
8.404
258.001


−8.653
8.782
258.001


−8.713
9.076
258.001


−8.746
9.313
258.001


−8.757
9.493
258.001


−8.749
9.627
258.001


−8.731
9.700
258.001


−8.708
9.742
258.001


−8.691
9.759
258.001


−8.680
9.765
258.001


−8.508
9.651
259.194


−8.503
9.652
259.194


−8.491
9.654
259.194


−8.468
9.651
259.194


−8.427
9.631
259.194


−8.371
9.586
259.194


−8.283
9.491
259.194


−8.177
9.355
259.194


−8.046
9.168
259.194


−7.887
8.929
259.194


−7.688
8.614
259.194


−7.459
8.249
259.194


−7.212
7.863
259.194


−6.931
7.429
259.194


−6.615
6.950
259.194


−6.261
6.428
259.194


−5.882
5.888
259.194


−5.480
5.331
259.194


−5.052
4.757
259.194


−4.598
4.166
259.194


−4.117
3.561
259.194


−3.607
2.941
259.194


−3.069
2.307
259.194


−2.502
1.660
259.194


−1.925
1.022
259.194


−1.339
0.27222
259.194


−0.745
−0.231
259.194


−0.144
−0.847
259.194


0.32083
−1.458
259.194


1.073
−2.064
259.194


1.687
−2.667
259.194


2.304
−3.266
259.194


2.925
−3.862
259.194


3.549
−4.454
259.194


4.175
−5.044
259.194


4.784
−5.611
259.194


5.374
−6.155
259.194


5.946
−6.677
259.194


6.501
−7.176
259.194


7.037
−7.652
259.194


7.555
−8.105
259.194


8.055
−8.535
259.194


8.515
−8.924
259.194


8.933
−9.273
259.194


9.311
−9.582
259.194


9.646
−9.851
259.194


9.940
−10.081
259.194


10.190
−10.273
259.194


10.406
−10.435
259.194


10.588
−10.570
259.194


10.739
−10.679
259.194


10.860
−10.766
259.194


10.943
−10.845
259.194


10.975
−10.924
259.194


10.978
−10.996
259.194


10.963
−11.052
259.194


10.943
−11.090
259.194


10.915
−11.125
259.194


10.868
−11.161
259.194


10.798
−11.187
259.194


10.709
−11.185
259.194


10.603
−11.133
259.194


10.472
−11.052
259.194


10.309
−10.951
259.194


10.110
−10.828
259.194


9.873
−10.683
259.194


9.595
−10.513
259.194


9.266
−10.314
259.194


8.886
−10.085
259.194


8.456
−9.824
259.194


7.977
−9.531
259.194


7.449
−9.204
259.194


6.873
−8.842
259.194


6.275
−8.460
259.194


5.655
−8.057
259.194


5.015
−7.630
259.194


4.355
−7.180
259.194


3.678
−6.705
259.194


2.985
−6.205
259.194


2.278
−5.676
259.194


1.581
−5.137
259.194


0.62222
−4.586
259.194


0.15417
−4.023
259.194


−0.440
−3.446
259.194


−1.088
−2.855
259.194


−1.722
−2.249
259.194


−2.340
−1.626
259.194


−2.941
−0.984
259.194


−3.522
−0.322
259.194


−4.082
0.25139
259.194


−4.622
1.069
259.194


−5.124
1.773
259.194


−5.588
2.470
259.194


−6.014
3.155
259.194


−6.405
3.828
259.194


−6.760
4.486
259.194


−7.084
5.127
259.194


−7.377
5.750
259.194


−7.640
6.353
259.194


−7.864
6.909
259.194


−8.053
7.413
259.194


−8.209
7.866
259.194


−8.345
8.294
259.194


−8.451
8.668
259.194


−8.521
8.959
259.194


−8.563
9.195
259.194


−8.580
9.374
259.194


−8.577
9.509
259.194


−8.562
9.582
259.194


−8.540
9.625
259.194


−8.524
9.642
259.194


−8.514
9.648
259.194


−8.337
9.565
260.388


−8.331
9.567
260.388


−8.320
9.569
260.388


−8.297
9.566
260.388


−8.255
9.547
260.388


−8.198
9.503
260.388


−8.109
9.409
260.388


−8.001
9.275
260.388


−7.867
9.090
260.388


−7.705
8.854
260.388


−7.499
8.543
260.388


−7.264
8.183
260.388


−7.010
7.801
260.388


−6.723
7.373
260.388


−6.401
6.899
260.388


−6.041
6.381
260.388


−5.658
5.845
260.388


−5.252
5.291
260.388


−4.820
4.720
260.388


−4.364
4.133
260.388


−3.880
3.529
260.388


−3.370
2.911
260.388


−2.831
2.278
260.388


−2.265
1.632
260.388


−1.689
0.69028
260.388


−1.105
0.25278
260.388


−0.514
−0.259
260.388


0.084
−0.876
260.388


0.47708
−1.489
260.388


1.294
−2.096
260.388


1.906
−2.701
260.388


2.520
−3.301
260.388


3.139
−3.898
260.388


3.760
−4.492
260.388


4.384
−5.083
260.388


4.990
−5.651
260.388


5.578
−6.197
260.388


6.147
−6.720
260.388


6.699
−7.221
260.388


7.232
−7.699
260.388


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−15.966
285.054


9.881
−15.935
285.054


9.786
−15.853
285.054


9.664
−15.743
285.054


9.513
−15.607
285.054


9.328
−15.441
285.054


9.109
−15.243
285.054


8.851
−15.013
285.054


8.546
−14.742
285.054


8.194
−14.429
285.054


7.796
−14.072
285.054


7.353
−13.672
285.054


6.866
−13.227
285.054


6.336
−12.736
285.054


5.788
−12.219
285.054


5.222
−11.675
285.054


4.640
−11.104
285.054


4.043
−10.504
285.054


3.433
−9.876
285.054


2.811
−9.217
285.054


2.177
−8.528
285.054


1.554
−7.831
285.054


0.65417
−7.124
285.054


0.23681
−6.409
285.054


−0.249
−5.684
285.054


−0.826
−4.950
285.054


−1.392
−4.208
285.054


−1.948
−3.456
285.054


−2.491
−2.695
285.054


−3.023
−1.924
285.054


−3.543
−1.144
285.054


−4.051
−0.355
285.054


−4.532
0.28889
285.054


−4.986
1.170
285.054


−5.413
1.903
285.054


−5.815
2.616
285.054


−6.191
3.306
285.054


−6.544
3.974
285.054


−6.873
4.618
285.054


−7.179
5.239
285.054


−7.450
5.807
285.054


−7.686
6.321
285.054


−7.890
6.782
285.054


−8.073
7.216
285.054


−8.226
7.596
285.054


−8.335
7.891
285.054


−8.411
8.131
285.054


−8.455
8.314
285.054


−8.473
8.455
285.054


−8.470
8.533
285.054


−8.457
8.582
285.054


−8.443
8.603
285.054


−8.434
8.611
285.054


−8.544
9.086
288.000


−8.538
9.088
288.000


−8.525
9.091
288.000


−8.500
9.088
288.000


−8.454
9.066
288.000


−8.391
9.018
288.000


−8.291
8.915
288.000


−8.172
8.768
288.000


−8.021
8.564
288.000


−7.840
8.305
288.000


−7.612
7.962
288.000


−7.354
7.564
288.000


−7.079
7.138
288.000


−6.772
6.659
288.000


−6.432
6.125
288.000


−6.057
5.538
288.000


−5.664
4.925
288.000


−5.253
4.286
288.000


−4.824
3.622
288.000


−4.374
2.933
288.000


−3.905
2.219
288.000


−3.415
1.480
288.000


−2.905
0.49792
288.000


−2.373
−0.069
288.000


−1.838
−0.853
288.000


−1.300
−1.635
288.000


−0.758
−2.415
288.000


−0.214
−3.194
288.000


0.23125
−3.970
288.000


0.61319
−4.743
288.000


1.435
−5.516
288.000


1.990
−6.286
288.000


2.547
−7.055
288.000


3.107
−7.822
288.000


3.671
−8.585
288.000


4.220
−9.321
288.000


4.754
−10.028
288.000


5.273
−10.707
288.000


5.776
−11.358
288.000


6.263
−11.982
288.000


6.735
−12.577
288.000


7.190
−13.145
288.000


7.611
−13.660
288.000


7.994
−14.123
288.000


8.341
−14.535
288.000


8.649
−14.896
288.000


8.919
−15.206
288.000


9.151
−15.466
288.000


9.351
−15.686
288.000


9.521
−15.869
288.000


9.662
−16.020
288.000


9.775
−16.139
288.000


9.860
−16.232
288.000


9.896
−16.321
288.000


9.893
−16.401
288.000


9.869
−16.461
288.000


9.840
−16.500
288.000


9.803
−16.531
288.000


9.744
−16.558
288.000


9.663
−16.563
288.000


9.573
−16.528
288.000


9.477
−16.442
288.000


9.354
−16.328
288.000


9.199
−16.186
288.000


9.011
−16.014
288.000


8.788
−15.810
288.000


8.525
−15.571
288.000


8.215
−15.289
288.000


7.857
−14.963
288.000


7.453
−14.593
288.000


7.003
−14.177
288.000


6.510
−13.713
288.000


5.973
−13.202
288.000


5.417
−12.662
288.000


4.845
−12.094
288.000


4.258
−11.498
288.000


3.657
−10.872
288.000


3.043
−10.215
288.000


2.418
−9.527
288.000


1.784
−8.807
288.000


1.161
−8.078
288.000


0.38194
−7.339
288.000


−0.048
−6.591
288.000


−0.632
−5.833
288.000


−1.203
−5.065
288.000


−1.762
−4.287
288.000


−2.309
−3.501
288.000


−2.843
−2.705
288.000


−3.364
−1.899
288.000


−3.873
−1.084
288.000


−4.370
−0.260
288.000


−4.838
0.37847
288.000


−5.280
1.331
288.000


−5.695
2.096
288.000


−6.084
2.840
288.000


−6.448
3.560
288.000


−6.788
4.257
288.000


−7.103
4.929
288.000


−7.396
5.576
288.000


−7.654
6.168
288.000


−7.877
6.705
288.000


−8.068
7.184
288.000


−8.240
7.637
288.000


−8.380
8.033
288.000


−8.480
8.340
288.000


−8.547
8.589
288.000


−8.585
8.779
288.000


−8.597
8.924
288.000


−8.591
9.004
288.000


−8.575
9.053
288.000


−8.559
9.074
288.000


−8.549
9.082
288.000









At the same time, each blade 10 therefore has an aerodynamic profile which allows a high conversion efficiency and a high useful life to be maintained.
Furthermore, the aerodynamic profile of the blade 10 according to the invention is obtained with the values of Table I by piling up the series of closed curves and grouping them so as to obtain a continuous aerodynamic profile.
In order to take into account the dimensional variability of each blade 10, the profile of each blade 10 can have a tolerance of +/−2 mm in a normal direction with respect to the profile of the blade 10 itself.
The profile of each blade 10 can also comprise a coating, applied subsequently and which varies the profile itself.
Said antiwear coating preferably has a thickness defined in a normal direction at each surface of the blade 10 and ranging from 0 to 0.5 mm.
It is evident, moreover, that the values of the coordinates of Table I can be multiplied or divided by a corrective constant to obtain a profile in a greater or smaller scale, maintaining the same form.
According to another aspect of the present invention, a rotor of a ninth phase of a compressor is provided, which comprises a series of blades 10 of the type described above, each of which having a shaped aerodynamic profile, which are fixed to an outer surface of said rotor so as to be uniformly distanced thereon, and also oriented so as to confer a high efficiency to the compressor in which said rotor is preferably inserted.
According to another aspect of the present invention, a compressor is provided, comprising a rotor of the type described above.
It can thus be seen that a blade of a rotor of a ninth phase of a compressor according to the present invention achieves the objectives specified above.
The rotor blade of a ninth phase of a compressor of the present invention thus conceived, can undergo numerous modifications and variants, all included in the same inventive concept.
Furthermore, in practice, the materials used, as also the dimensions and components, can vary according to technical requirements.

## Claims

1. A blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having an aerodynamic profile which can be identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising:
a base portion fixable to said rotor,
the aerodynamic profile extending from a foot at said base portion to a free end distal from said base portion,
a first thickening, substantially parallel to said base portion, said first thickening being substantially situated halfway up the blade, and
a further thickening, substantially parallel to said base portion and situated close to said free end, said further thickening having a maximum thickness less than a thickness of the blade at said foot,
said first thickening and said further thickening being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

2. The blade according to claim 1, wherein said blade further comprises:
the aerodynamic profile identified by a first substantially concave surface, which is pressurized, and a second substantially convex surface which is in depression and which is opposite to the first,
said two surfaces being continuous and joined to each other to form the aerodynamic profile of said blade.

3. The blade according to claim 2, wherein each closed curve has a maximum thickness determined by the maximum distance between said first surface and said second surface, said maximum thickness of each closed curve, along the height of the blade in the direction of a free end of the blade, first having a decreasing and then an increasing trend, followed again by a decreasing and finally increasing trend, with a discontinuity point of the slope.

4. The blade according to claim 3, wherein along the height of the blade in the direction of its free end, said maximum thickness has a trend according to the following equations, wherein h represents the height of the blade, expressed as a percentage of the total height of the blade, and wherein Tmax is the maximum adimensionalized thickness relating to the closed curve corresponding to the height:


Tmax=−34.522*h4+36.4*h3−8.4113*h2−0.7259*h+0.9961

for height values ranging from 0 to 45%;


Tmax=−1.3509*h+1.4459


for a height ranging from 45% to 58%;


Tmax=0.2074*h+0.5443


for a height ranging from 58% to 86%;


Tmax=0.9058*h−0.0518


for a height ranging from 86% to 100%.

5. A blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having an aerodynamic profile which can be identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising:
a base portion fixable to said rotor,
the aerodynamic profile having a surface extending from a foot at said base portion to a free end distal from said base portion,
a first thickening, substantially parallel to said base portion, said first thickening being substantially situated halfway up the blade,
a further thickening, substantially parallel to said base portion and situated close to said free end, said further thickening having a maximum thickness less than a thickness of the blade at said foot, and
said first thickening and said further thickening being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor;
wherein said closed curves are defined according to Table I, whose values, expressed in millimeters, refer to a profile at room temperature.

6. The blade according to claim 5, wherein the profile of said blade has a tolerance of +/−2 mm in a normal direction with respect to the profile of the blade itself.

7. The blade according to claim 6, further comprising an antiwear coating on the surface.

8. The blade according to claim 7, wherein said coating has a thickness ranging from 0 to 0.5 mm.

9. A rotor of a ninth phase of a compressor, comprising a series of blades according to claim 1.

10. The rotor according to claim 9, wherein said series of blades is constrained to an outer surface of said rotor and said series of blades is also uniformly distributed thereon in order to maximize the efficiency of the rotor itself.

11. A compressor characterized in that it comprises a rotor according to claim 9.

12. A blade of a rotor of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, said blade having a profile defining the surface of the blade which can be identified by means of a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, said blade comprising said closed curves defined according to Table I, whose values, expressed in millimeters, refer to a profile at room temperature.

13. The blade according to claim 12, wherein the profile of said blade has a tolerance of +/−2 mm in a normal direction with respect to the profile of the blade itself.

14. The blade according to claim 13, further comprising an antiwear coating on the blade surface.

15. The blade according to claim 14, wherein said coating has a thickness ranging from 0 to 0.5 mm.

16. The blade according to claim 12 wherein the values of the coordinates of Table 1 are multiplied by a corrective constant to obtain a scaled profile maintaining the same form.

17. A rotor of a ninth phase of a compressor, the rotor comprising a series of blades according to claim 12.

18. The rotor according to claim 12, wherein said series of blades is constrained to an outer surface of said rotor and said series of blades is also uniformly distributed thereon in order to maximize the efficiency of the rotor itself.

19. A compressor that comprises a rotor according to claim 12.