CA2579387C - Rotor blade for a ninth phase of a compressor - Google Patents
Rotor blade for a ninth phase of a compressor Download PDFInfo
- Publication number
- CA2579387C CA2579387C CA2579387A CA2579387A CA2579387C CA 2579387 C CA2579387 C CA 2579387C CA 2579387 A CA2579387 A CA 2579387A CA 2579387 A CA2579387 A CA 2579387A CA 2579387 C CA2579387 C CA 2579387C
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- CA
- Canada
- Prior art keywords
- blade
- rotor
- profile
- compressor
- thickening
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Measuring Or Testing Involving Enzymes Or Micro-Organisms (AREA)
Abstract
The invention relates to a blade (10) 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 (10) having a 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 (10) also comprising a thickening (30), substantially parallel to a base portion (12) of the blade (10) itself, fixable to said rotor, said thickening (30) being substantially situated half- way up the blade (10) and being suitable for shifting the natural resonance frequencies of the blade (10) itself outside a functioning frequency range of said rotor.
Description
ROTOR BLADE FOR A NINTH PHASE OF A COMPRESSOR
The present invention relates to a blade of a rotor of a ninth phase of a compressor.
More specifically, the invention relates to a blade of a rotor having a high aerody-namic 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 tempera-ture 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 aero-dynamic conditions.
The geometric configuration of the blades in fact significantly influences the aerody-namic efficiency.
This depends on the fact that the geometric characteristics of the blade cause a distri-bution 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.
An objective of the present invention is to provide a blade of a rotor of a ninth phase of a compressor which avoids or in any case reduces resonance problems due to flex-ural vibrations which reduce the life of the component, and at the same time allow a high aerodynamic efficiency.
A further objective of the present invention is to provide a rotor of a ninth phase of a compressor which 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.
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:
figure 1 is a raised view of a rotor blade of a compressor produced with an aerodynamic profile according to the present invention;
figure 2 is a raised view of the opposite side of the blade of figure 1; and figure 3 is a diagram of the maximum thickness trend of a blade according to the present invention, with respect to its height.
With reference to the figures, a blade 10 is provided of a rotor of a ninth phase of a compressor.
Said blade 10 is defmed 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.
The present invention relates to a blade of a rotor of a ninth phase of a compressor.
More specifically, the invention relates to a blade of a rotor having a high aerody-namic 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 tempera-ture 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 aero-dynamic conditions.
The geometric configuration of the blades in fact significantly influences the aerody-namic efficiency.
This depends on the fact that the geometric characteristics of the blade cause a distri-bution 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.
An objective of the present invention is to provide a blade of a rotor of a ninth phase of a compressor which avoids or in any case reduces resonance problems due to flex-ural vibrations which reduce the life of the component, and at the same time allow a high aerodynamic efficiency.
A further objective of the present invention is to provide a rotor of a ninth phase of a compressor which 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.
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:
figure 1 is a raised view of a rotor blade of a compressor produced with an aerodynamic profile according to the present invention;
figure 2 is a raised view of the opposite side of the blade of figure 1; and figure 3 is a diagram of the maximum thickness trend of a blade according to the present invention, with respect to its height.
With reference to the figures, a blade 10 is provided of a rotor of a ninth phase of a compressor.
Said blade 10 is defmed 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.
- 2 -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 or exactly 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 substantially or exactly 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 or exactly 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 figure 3, in which it is compared with the maximum thickness trend of a blade according to the known art. In particular, in figure 3, the abscissa indicates the height of the blade 10, whereas the
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 substantially or exactly 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 or exactly 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 figure 3, in which it is compared with the maximum thickness trend of a blade according to the known art. In particular, in figure 3, the abscissa indicates the height of the blade 10, whereas the
- 3 -ordinate represents the maximum thickness of the blade 10, non-dimensionalized by putting the thickness in correspondence with the foot of the blade equal to 1. In the diagram shown in figure 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 non-dimensionalized 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.
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 non-dimensionalized 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.
- 4 -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 I
X Y Z -5.155 4.256255.999 -8.852 9.902 255.999 -4.688 3.638255.999 -8.847 9.904255.999 -4.190 3.006255.999 -8.835 9.905255.999 -3.660 2.364255.999 -8.812 9.901255.999 -3.096 1.711255.999 -8.771 9.880 255.999 -2.520 1.069255.999 -8.717 9.833 255.999 -1.933 0,30278 255.999 -8.632 9.734 255.999 -1.338 -0.189255.999 -8.533 9.594255.999 -0.735 -0.806 255.999 -8.410 9.400255.999 -0.126 -1.417255.999 -8.263 9.152255.999 0,33958 -2.023255.999 -8.080 = 1.108 -2.624255.999 -7.871 8.449255.999 1.732 -3.21 255.999 -7.643 8.050255.999 2.362 -3.809255.999 -7.382 7.603255.999 2.995 -4.395255.999 -7.086 7.110255.999 3.631 -4.978 255.999 -6.751 6.573-255.999 4.249 -5.538 255.999 -6.390 6.019255.999 4.849 -6.075255.999 -6.005- 5.448255.999 5.432 -6.588255.999
Table I
X Y Z -5.155 4.256255.999 -8.852 9.902 255.999 -4.688 3.638255.999 -8.847 9.904255.999 -4.190 3.006255.999 -8.835 9.905255.999 -3.660 2.364255.999 -8.812 9.901255.999 -3.096 1.711255.999 -8.771 9.880 255.999 -2.520 1.069255.999 -8.717 9.833 255.999 -1.933 0,30278 255.999 -8.632 9.734 255.999 -1.338 -0.189255.999 -8.533 9.594255.999 -0.735 -0.806 255.999 -8.410 9.400255.999 -0.126 -1.417255.999 -8.263 9.152255.999 0,33958 -2.023255.999 -8.080 = 1.108 -2.624255.999 -7.871 8.449255.999 1.732 -3.21 255.999 -7.643 8.050255.999 2.362 -3.809255.999 -7.382 7.603255.999 2.995 -4.395255.999 -7.086 7.110255.999 3.631 -4.978 255.999 -6.751 6.573-255.999 4.249 -5.538 255.999 -6.390 6.019255.999 4.849 -6.075255.999 -6.005- 5.448255.999 5.432 -6.588255.999
-5.593 4.860255.999 5.998 -7.077255.999
6.545 -7.543 255.999 9.561 -10.857 255.999
7.075 -7.986255.999 9.318 -10.711255.999 7.586 -8.405 255.999 9.034 -10.552 255.999
8.056 -8.784 255.999 8.697 -10.359 255.999 8.485 -9.124255.999 8.308 -10.137255.999 8.871 -9.424255.999 7.867 -9.884255.999
9.214 -9.685 255.999 7.376 -9.600 255.999 9.515 -9.908 255.999 6.835 -9.282 255.999 9.771 -10.093 255.999 6.245 -8.931 255.999 9.992 -10.249 255.999 5.633 -8.559 255.999
10.179 -10.379255.999 4.999 -8.165255.999 10.332 -10.485 255.999 4.344 -7.748 255.999 10.426 -10.600255.999 3.670 -7.305 255.999 10.461 -10.708255.999 2.977 -6.837 255.999 10.465 -10.793255.999 2.267 -6.341255.999 10.452 -10.864255.999 1.543 -5.816255.999 10.432 -10.917 255.999 0,57639 -5.280255.999 10.411 -10.955255.999 0,08958 -4.730255.999 10.385 -10.991255.999 -0.558 -4.165255.999 10.343 -11.034255.999 -1.230 -3.583 255.999 10.282 -11.077255.999 -1.886 -2.983 255.999 10.199 -11.110255.999 -2.526 -2.366255.999 10.081 -11.119255.999 -3.146 -1.727255.999 9.933 -11.073255.999 -3.744 -1.064255.999 9.765 -10.976 255.999 -4.317 -0.373 255.999 -4.864 0,24028 255.999 -8.658 9.770 258.001 -5.383 1.085255.999 -8.635 9.767 258.001 -5.861 1.816255.999 -8.593 9.746 258.001 -6.301 2.535 255.999 -8.538 9.700 258.001 -6.704 3.242 255.999 -8.452 9.604 258.001 -7.070 3.934 255.999 -8.349 9.465 258.001 -7.401 4.611255.999 -8.222 9.274258.001 -7.697 5.271 255.999 -8.069 9.031 258.001 -7.962 5.912255.999 -7.877 8.711258.001 -8.194 6.533 255.999 -7.657 8.340 258.001 -8.387 7.104255.999 -7.419 7.941258.001 -8.547 7.623 255.999 -7.147 7.508 258.001 -8.675 8.088255.999 -6.840 7.022258.001 -8.783 8.528 255.999 -6.494 6.493 258.001 -8.864 8.911255.999 -6.123 5.948258.001 -8.914 9.209 255.999 -5.726 5.38c258.001 -8.940 9.449 255.999 -5.304 4.805258.001 -8.945 9.630255.999 -4.855 4.211258.001 -8.932 9.765 255.999 -4.377 3.601 258.001 -8.911 9.837255.999 -3.871 2.978258.001 -8.887 9.878 255.999 -3.333 2.342 258.001 -8.869 9.894 255.999 -2.766 1.694258.001 -8.858 9.900 255.999 -2.187 1.055258.001 -8.675 9.767258.001 -1.600 0,29514258.001 -8.669 9.769258.001 -1.004 -0.198258.001 -0.402 -0.814 258.001 10.731 -10.780 258.001 0,14236 -1.425258.001 10.749 -10.863258.001 0,56736 -2.031 258.001 10.744 -10.934258.001 1.433 -2.634258.001 10.727 -10.988258.001 2.053 -3.232258.001 10.707 -11.026258.001 2.677 -3.827 258.001 10.680 -11.062258.001 3.304 -4.418258.001 10.636 -11.102258.001 3.933 -5.006258.001 10.570 -11.137258.001 4.545 -5.571258.001 10.482 -11.152258.001 5.139 -6.113258.001 10.366 -11.127258.001 5.715 -6.632 258.001 10.233 -11.049258.001 6.274 -7.127258.001 10.067 -10.949258.001 6.815 -7.600258.001 9.866 -10.828258.001 7.337 -8.049258.001 9.626 -10.684258.001 7.841 -8.476258.001' 9.346 -10.517258.001 8.305 -8.861 258.001 9.013 -10.321 258.001 8.728 -9.206258.001 8.629 -10.094258.001 9.109 -9.512258.001 8.194 -9.837258.001 9.448 -9.778 258.001 7.710 -9.547 258.001 9.744 -10.005258.001 7.176 -9.224258.001 9.997 -10.194258.001 6.594 -8.867258.001 10.215 -10.354258.001 5.990 -8.489258.001 10.399 -10.486 258.001 5.364 -8.089 258.001 10.552 -10.594258.001 4.718 -7.666258.001 10.671 -10.684258.001 4.052 -7.219258.001 3.368 -6.746 258.001 -8.559 8.404 258.001 2.667 -6.245 258.001 -8.653 8.782 258.001 1.952 -5.716 258.001 -8.713 9.076 258.001 1.247 -5.175258.001 -8.746 9.313258.001 0,38472 -4.623258M01 -8.757 9.493258.001 -0.127 -4.057 258.001 -8.749 9.627 258.001 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- 35 -0,15417 -4.168275.374 -8.194 8.647275.374 -0.362 -3.518275.374 -8.184 8.693 275.374 -0.935 -2.860 275.374 -8.172 8.713 275.374 -1.499 -2.194275.374 -8.163 8.721275.374 -2.054 -1.518275.374 -8.263 8.345 279.583 -2.597 -0.833 275.374 -8.257 8.348 279.583 -3.129 -0.138275.374 -8.245 8.350279.583 -3.651 0,39444 275.374 -8.222 8.348 279.583 -4.144 1.259275.374 -8.178 8.329 279.583 -4.610 1.936275.374 -8.117 8.286 279.583 -5.050 2.597 275.374 -8.021 8.194 279.583 -5.462 3.240275.374 -7.904 8.061 279.583 -5.849 3.864 275.374 -7.757 7.876 279.583 -6.211 4.470 275.374 -7.579 7.639 279.583 -6.548 5.056 275.374 -7.353 7.328 279.583 -6.862 5.621275.374 -7.095 6.968279.583 -7.139 6.140275.374 -6.819 6.583279.583 -7.380 6.610 275.374 -6.510 6.150279.583 -7.588 7.032 275.374 -6.166 5.668 279.583 -7.776 7.431275.374 -5.787 5.139279.583 -7.932 7.780 275.374 -5.390 4.587 279.583 -8.044 8.052 275.374 -4.973 4.013279.583 -8.122 8.273 275.374 -4.537 3.416 279.583 -8.170 8.443 275.374 -4.080 2.797 279.583 -8.192 8.574 275.374 -3.603 2.157279.583
- 36 --3.104 1.497279.583 9.404 -13.319279.583 -2.583 0,56597 279.583 9.634 -13.549 279.583 -2.041 0,07847 279.583 9.832 -13.744 279.583 -1.496 -0.587 279.583 10.000 -13.907 279.583 -0.948 -1.285279.583 10.138 -14.041 279.583 -0.399 -1.982 279.583 10.249 -14.147 279.58 0,10625 -2.677 279.583 10.330 -14.233 279.583 0,49236 -3.369 279.583 10.360 -14.317 279.583 1.266 -4.059279.583 10.358 -14.392279.583 1.826 -4.747279.583 10.336 -14.448279.583 2.389 -5.433 279.583 10.310 -14.486279.583 2.954 -6.117279.583 10.277 -14.516279.583 3.524 -6.797279.583 10.223 -14.544279.583 4.097 -7.474279.583 10.149 -14.555279.583 4.655 -8.125 279.583 10.061 -14.531 279.583 5.198 -8.751 279.583 9.967 -14.457 279.583 5.724 -9.351279.583 9.850 -14.354279.583 6.235 -9.926 279.583 9.703 -14.226 279.583 6.729 -10.476279.583 9.524 -14.071 279.583 7.207 -11.001279.583 9.311 -13.886279.583 7.668 -11.501279.583 9.061 -13.671279.583 8.092 -11.955279.583 8.765 -13.417279.583 8.478 -12.363279.583 8.424 -13.123279.583 8.826 -12.727 279.583 8.038 -12.790279.583 9.134 -13.045279.583 7.608 -12.417279.583
- 37 -7.135 -12.001279.583 -6.311 3.978279.583 6.618 -11.544279.583 -6.648 4.581279.583 6.083 -11.063279.583 -6.962 5.163 279.583 5.529 -10.558279.583 -7.240 5.696279.583 4.959 -10.028 279.581 -7.483 6.179279.583 4.372 -9.473 279.583 -7.691 6.612 279.583 3.771 -8.891 279.583 -7.880 7.021 279.583 3.155 -8.282 279.583 -8.038 7.379 279.583 2.526 -7.644 279.583 -8.151 7.657 279.583 1.906 -6.998 279.583 -8.231 7.884279.583 1.295 -6.344 279.583 -8.278 8.058 279.583 0,48125 -5.682 279.583 -8.300 8.192279.583 0,07014 -5.011 279.583 -8.300 8.267 279.583 -0.481 -4.331 279.583 -8.289 8.313279.583 -1.053 -3.642279.583 -8.277 8.334 279.583 -1.615 -2.944 279.583 -8.268 8.342 279.583 -2.168 -2.238 279.583 -8.384 8.472 283.792 -2.709 -1.521 279.583 -8.378 8.475 283.792 -3.241 -0.796 279.583 -8.366 8.477 283.792 -3.761 -0.060 279.583 -8.341 8.475 283.792 -4.254 0,45694279.583 -8.296 8.454283.792 -4.718 1.360279.583 -8.235 8.408 283.792 -5.155 2.043279.583 -8.138 8.310283.792 -5.565 2.708 279.583 -8.020 8.170 283.792 -5.950 3.353 279.583 -7.872 7.976 283.792,
- 38 --7.692 7.728 283.792 3.974 -8.188283.792 -7.465 7.402 283.792 4.532 -8.876 283.792 -7.205 7.025 283.792 5.075 -9.537 283.792 -6.929 6.622283.792 5.602 -10.172283.792 -6.619 6.167283.792 6.113 -10.781283.792 -6.276 5.661 283.792 6.607 -11.363 283.79/
-5.898 5.105283.792 7.085 -11.920283.792 -5.502 4.525 283.792 7.546 -12.450 283.792 -5.087 3.920283.792 7.970 -12.932283.792 -4.653 3.292283.792 8.356 -13.365283.792 -4.198 2.640283.792 8.705 -13.751 283.792 -3.722 1.966 283.792 9.014 -14.089 283.792 -3.225 1.269283.792 9.285 -14.380 283.792 -2.707 0,38194283.792 9.516 -14.624283.792 -2.167 -0.191283.792 9.715 -14.831283.792 -1.625 -0.929 283.792 9.884 -15.004283.792 -1.079 -1.666283.792 10.023 -15.145283.792 -0.530 -2.400283.792 10.135 -15.258 283.792 0.022 -3.132283.792 10.217 -15.348283.792 0,40069 -3.862 283.792 10.249 -15.434283.792 1.136 -4.588283.792 10.245 -15.510283.792 1.697 -5.313283.792 10.223 -15.567283.792 2.261 -6.036 283.792 10.196 -15.605 283.792 2.829 -6.756283.792 10.160 -15.635 283.792 3.399 -7.473283.792 10.104 -15.662283.792
-5.898 5.105283.792 7.085 -11.920283.792 -5.502 4.525 283.792 7.546 -12.450 283.792 -5.087 3.920283.792 7.970 -12.932283.792 -4.653 3.292283.792 8.356 -13.365283.792 -4.198 2.640283.792 8.705 -13.751 283.792 -3.722 1.966 283.792 9.014 -14.089 283.792 -3.225 1.269283.792 9.285 -14.380 283.792 -2.707 0,38194283.792 9.516 -14.624283.792 -2.167 -0.191283.792 9.715 -14.831283.792 -1.625 -0.929 283.792 9.884 -15.004283.792 -1.079 -1.666283.792 10.023 -15.145283.792 -0.530 -2.400283.792 10.135 -15.258 283.792 0.022 -3.132283.792 10.217 -15.348283.792 0,40069 -3.862 283.792 10.249 -15.434283.792 1.136 -4.588283.792 10.245 -15.510283.792 1.697 -5.313283.792 10.223 -15.567283.792 2.261 -6.036 283.792 10.196 -15.605 283.792 2.829 -6.756283.792 10.160 -15.635 283.792 3.399 -7.473283.792 10.104 -15.662283.792
- 39 -10.027 -15.670283.792 -0.689 -4.837283.792 9.938 -15.641 283.792 -1.256 -4.108 283.792 9.843 -15.561283.792 -1.813 -3.369283.792 9.724 -15.453283.792 -2.359 -2.621 283.792 9.574 -15.319283.792 -2.893 -1.864283.792 9.391 -15.155283.792 -3.417 -1.098283.792 9.174 -14.961283.792 -3.931 -0.324283.792 8.919 -14.734283.792 -4.416 0,30139283.792 8.617 -14.467 283.792 -4.875 1.173283.792 8.269 -14.158283.792 -5.307 1.891283.792 7.876 -13.807283.792 -5.713 2.589283.792 7.438 -13.412 283.792 -6.093 3.265 283.792 6.957 -12.974 283.792 -6.450 3.920 283.792 6.433 -12.490283.792 -6.784 4.551 283.792 5.891 -11.981283.792 -7.094 5.160283.792 5.331 -11.445283.792 -7.370 5.716283.792 4.755 -10.883 283.792 -7.611 6.221 283.792 4.164 -10.293283.792 -7.818 6.672283.792 3.558 -9.675 283.792 -8.006 7.099 283.792 2.940 -9.028283.792 -8.163 7.471 283.792 2.310 -8.351283.792 -8.276 7.760283.792 1.689 -7.666 283.792 -8.355 7.995 283.792 1.079 -6.972 283.792 -8.402 8.176283.792 0,33264 -6.270 283.792 -8.423 8.314283.792 -0.110 -5.558 283.792 -8.423 8.391 283.792
- 40 --8.411 8.440 283.792 -2.741 0,39514285.054 -8.398 8.461283.792 -2.202 -0.185285.054 -8.389 8.469 283.792 -1.660 -0.937 285.054 -8.429 8.614 285.054 -1.113 -1.686285.054 -8.423 8.617285.054 -0.565 -2.433285.054 -8.411 8.620 285.054 -0.013 -3.177285.054 -8.386 8.617 285.054 0,37639 -3.920 285.054 -8.340 8.597 285.054 1.100 -4.660 285.054 -8.278 8.550 285.054 1.661 -5.398 285.054 -8.179 8.452 285.054 2.224 -6.135285.054 -8.061 8.309285.054 2.789 -6.869 285.054 -7.911 8.113 285.054 3.358 -7.601 285.054 -7.730 7.862 285.054 3.931 -8.330 285.054 -7.502 7.532 285.054 4.487 -9.032285.054 -7.241 7.148285.054 5.028 -9.707 285.054 -6.964 6.739 285.054 5.553 -10.356 285.054 -6.654 6.277285.054 6.062 -10.977285.054 -6.311 5.764 285.054 6.555 -11.572285.054 -5.932 5.199285.054 7.031 -12.141285.054 -5.535 4.609 285.054 7.490 -12.683 285.054 -5.120 3.995285.054 7.914 -13.175285.054 -4.685 3.357 285.054 8.299 -13.617285.054 -4.230 2.695285.054 8.647 -14.011 285.054 -3.755 2.009285.054 8.956 -14.356285.054 -3.259 1.30d285.054 9.227 -14.653 285.054
- 41 -9.458 -14.902285.054 6.336 -12.736285.054 9.658 -15.113285.054 5.788 -12.219285.054 9.827 -15.289285.054 5.222 -11.675285.054 9.966 -15.434285.054 4.640 -11.104285.054 10.079 -15.549 285.054 4.043 -10.504 285.054 10.162 -15.639 285.054 3.433 -9.876285.054 10.196 -15.727285.054 2.811 -9.217285.054 10.192 -15.805285.054 2.177 -8.528285.054 10.170 -15.863 285.054 1.554 -7.831 285.054 10.142 -15.901285.054 0,65417 -7.124285.054 10.106 -15.932285.054 0,23681 -6.409 285.054 10.048 -15.959285.054 -0.249 -5.684 285.054 9.970 -15.966285.054 -0.826 -4.950 285.054 9.881 -15.935285.054 -1.392 -4.208 285.054 9.786 -15.853285.054 -1.948 -3.456285.054 9.664 -15.743285.054 -2.491 -2.695285.054 9.513 -15.607285.054 -3.023 -1.924285.054 9.328 -15.441285.054 -3.543 -1.144285.054 9.109 -15.243 285.054 -4.051 -0.355 285.054 8.851 -15.013285.054 -4.532 0,28889 285.054 8.546 -14.742 285.054 -4.986 1.170285.054 8.194 -14.429285.054 -5.413 1.903285.054 7.796 -14.072 285.054 -5.815 2.616 285.054 7.353 -13.672285.054 -6.191 3.306285.054 6.866 -13.227285.054 -6.544 3.974 285.054
- 42 --6.873 4.618285.054 -7.612 7.962288.000 -7.179 5.239285.054 -7.354 7.564288.000 -7.450 5.807 285.054 -7.079 7.138288.000 -7.686 6.321 285.054 -6.772 6.659288.000 -7.890 6.782285.054 -6.432 6.125288.000 -8.073 7.216 285.054 -6.057 5.538288.000 -8.226 7.596285.054 -5.664 4.925288.000 -8.335 7.891 285.054 -5.253 4.286 288.00 -8.411 8.131 285.054 -4.824 3.622 288.000 -8.455 8.314285.054 -4.374 2.933 288.000 -8.473 8.455 285.054 -3.905 2.219 288.000 -8.470 8.533 285.054 -3.415 1.480288.000 -8.457 8.582 285.054 -2.905 0,49792 288.000 -8.443 8.603285.054 -2.373 -0.0691288.000 -8.434 8.611 285.054 -1.838 -0.853 288.000 -8.544 9.086 288.000 -1.300 -1.635288.000 -8.538 9.088 288.000 -0.758 -2.415288.000 -8.525 9.091 288.000 -0.214 -3.194288.000 -8.500 9.088 288.000 0,23125 -3.970 288.000 -8.454 9.066 288.000 0,61319 -4.743 288.000 -8.391 9.018288.000 1.435 -5.516288.000 -8.291 8.915288.000 1.990 -6.286 288.000 -8.172 8.768 288.000 2.547 -7.055 288.000 -8.021 8.564 288.000 3.107 -7.822 288.000 -7.840 8.305 288.000 3.671 -8.585288.000
- 43 -4.220 -9.321 288.000 9.573 -16.528288.000 4.754 -10.028288.000 9.477 -16.442288.000 5.273 -10.707288.000 9.354 -16.328288.000 5.776 -11.358288.000 9.199 -16.186288.000 6.263 -11.982 288.000 9.011 -16.014 288.000 6.735 -12.577 288.000 8.788 -15.810288.000 7.190 -13.145288.000 8.525 -15.571288.000 7.611 -13.660288.000 8.215 -15.289288.000 7.994 -14.123288.000 7.857 -14.963288.000 8.341 -14.535288.000 7.453 -14.593288.000 8.649 -14.896288.000 7.003 -14.177288.000 8.919 -15.206288.000 6.510 -13.713288.000 9.151 -15.466288.000 5.973 -13.202288.000 9.351 -15.686288.000 5.417 -12.662288.000 9.521 -15.869288.000 4.845 -12.094288.000 9.662 -16.020 288.000 4.258 -11.498288.000 9.775 -16.139 288.000 3.657 -10.872 288.000 9.860 -16.232 288.000 3.043 -10.215288.000 9.896 -16.321 288.000 2.418 -9.527288.000 9.893 -16.401288.000 1.784 -8.807288.000 9.869 -16.461 288.000 1.161 -8.078 288.000 9.840 -16.500288.000 0,38194 -7.339288.000 9.803 -16.531288.000 -0.048 -6.591288.000 9.744 -16.558 288.000 -0.632 -5.833 288.000 9.663 -16.563288.000 -1.203 -5.065288.000
-44 --1.762 -4.287288.000 -8.597 8.924288.000 -2.309 -3.501 288.000 -8.591 9.004288.000 -2.843 -2.705288.000 -8.575 9.053288.000 -3.364 -1.899288.000 -8.559 9.074 288.000 -3.873 -1.084288.000 -8.549 9.082 288.000 -4.370 -0.260288.000 -4.838 0,37847288.000 -5.280 1.331 288.000 -5.695 2.096288.000 -6.084 2.840288.000 -6.448 3.560 288.000 -6.788 4.257288.000 -7.103 4.929288.000 -7.396 5.576288.000 -7.654 6.168 288.000 -7.877 6.705 288.000 -8.068 7.184288.000 -8.240 7.637 288.000 -8.380 8.033 288.000 -8.480 8.340288.000 -8.547 8.589288.000 -8.585 8.779288.000 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
Furthermore, the aerodynamic profile of the blade 10 according to the invention is
- 45 -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 in-serted.
According to another aspect of the present invention, a compressor is provided, com-prising 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 con-ceived, can undergo numerous modifications and variants, all included in the same in-ventive concept.
Furthermore, in practice, the materials used, as also the dimensions and components, can vary according to technical requirements.
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 in-serted.
According to another aspect of the present invention, a compressor is provided, com-prising 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 con-ceived, can undergo numerous modifications and variants, all included in the same in-ventive concept.
Furthermore, in practice, the materials used, as also the dimensions and components, can vary according to technical requirements.
-46 -
Claims (19)
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, parallel to said base portion, said first thickening being situated halfway up the blade, and a further thickening, 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.
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, parallel to said base portion, said first thickening being situated halfway up the blade, and a further thickening, 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 concave surface, which is pressurized, and a second 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.
the aerodynamic profile identified by a first concave surface, which is pressurized, and a second 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 non-dimensionalized 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%.
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, parallel to said base portion, said first thickening being situated halfway up the blade, a further thickening, 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.
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, parallel to said base portion, said first thickening being situated halfway up the blade, a further thickening, 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 of up 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 of up 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 17, 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 17.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IT000341A ITMI20060341A1 (en) | 2006-02-27 | 2006-02-27 | SHOVEL OF A ROTOR OF A NON-STAGE OF A COMPRESSOR |
| ITMI2006A000341 | 2006-02-27 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2579387A1 CA2579387A1 (en) | 2007-08-27 |
| CA2579387C true CA2579387C (en) | 2015-10-20 |
Family
ID=38051867
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2579387A Expired - Fee Related CA2579387C (en) | 2006-02-27 | 2007-02-22 | Rotor blade for a ninth phase of a compressor |
Country Status (8)
| Country | Link |
|---|---|
| EP (1) | EP1826413B1 (en) |
| JP (1) | JP5314852B2 (en) |
| KR (1) | KR101433373B1 (en) |
| CN (1) | CN101029647B (en) |
| AT (1) | ATE531944T1 (en) |
| CA (1) | CA2579387C (en) |
| IT (1) | ITMI20060341A1 (en) |
| NO (1) | NO20071076L (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102009036406A1 (en) * | 2009-08-06 | 2011-02-10 | Mtu Aero Engines Gmbh | airfoil |
| IT1401661B1 (en) * | 2010-08-25 | 2013-08-02 | Nuova Pignone S R L | FORM OF AODINAMIC PROFILE BY COMPRESSOR. |
| EP3051142B1 (en) | 2015-01-28 | 2017-10-11 | MTU Aero Engines GmbH | Gas turbine axial compressor |
| US10294957B2 (en) * | 2015-10-16 | 2019-05-21 | Hamilton Sundstrand Corporation | Fan rotor blade having an optimized blade root |
| US9995144B2 (en) | 2016-02-18 | 2018-06-12 | General Electric Company | Turbine blade centroid shifting method and system |
| CN107829985B (en) * | 2017-09-28 | 2019-09-10 | 中国航发动力股份有限公司 | A kind of modification method of aeroengine fan blades intrinsic frequency |
| CN113217418B (en) * | 2021-06-29 | 2022-07-19 | 中国科学院工程热物理研究所 | Pneumatic appearance structure of multistage axial compressor |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4108573A (en) * | 1977-01-26 | 1978-08-22 | Westinghouse Electric Corp. | Vibratory tuning of rotatable blades for elastic fluid machines |
| US4318672A (en) * | 1978-11-06 | 1982-03-09 | Nordisk Ventilator Co. A/S | Particle erosion resistant covering for fan blade leading edge |
| JPH03206400A (en) * | 1990-01-08 | 1991-09-09 | Hitachi Ltd | Device for removing matter sticking to blade surface of turbomachinery |
| JP2002048095A (en) | 2000-08-03 | 2002-02-15 | Hitachi Ltd | Blade for axial flow compressor |
| US6471482B2 (en) * | 2000-11-30 | 2002-10-29 | United Technologies Corporation | Frequency-mistuned light-weight turbomachinery blade rows for increased flutter stability |
| US6428269B1 (en) * | 2001-04-18 | 2002-08-06 | United Technologies Corporation | Turbine engine bearing support |
| US6857853B1 (en) * | 2003-08-13 | 2005-02-22 | General Electric Company | Conical tip shroud fillet for a turbine bucket |
| GB0325215D0 (en) * | 2003-10-29 | 2003-12-03 | Rolls Royce Plc | Design of vanes for exposure to vibratory loading |
| US7186090B2 (en) * | 2004-08-05 | 2007-03-06 | General Electric Company | Air foil shape for a compressor blade |
| CN1755123A (en) * | 2004-09-27 | 2006-04-05 | 乐金电子(天津)电器有限公司 | Compressor impeller structure |
| US20060073022A1 (en) * | 2004-10-05 | 2006-04-06 | Gentile David P | Frequency tailored thickness blade for a turbomachine wheel |
-
2006
- 2006-02-27 IT IT000341A patent/ITMI20060341A1/en unknown
-
2007
- 2007-02-22 CA CA2579387A patent/CA2579387C/en not_active Expired - Fee Related
- 2007-02-26 KR KR1020070019107A patent/KR101433373B1/en active IP Right Grant
- 2007-02-26 NO NO20071076A patent/NO20071076L/en not_active Application Discontinuation
- 2007-02-27 JP JP2007047168A patent/JP5314852B2/en not_active Expired - Fee Related
- 2007-02-27 AT AT07103096T patent/ATE531944T1/en active
- 2007-02-27 CN CN200710084354.9A patent/CN101029647B/en not_active Expired - Fee Related
- 2007-02-27 EP EP07103096A patent/EP1826413B1/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN101029647A (en) | 2007-09-05 |
| KR101433373B1 (en) | 2014-08-26 |
| JP2007231946A (en) | 2007-09-13 |
| ITMI20060341A1 (en) | 2007-08-28 |
| EP1826413A3 (en) | 2010-09-22 |
| ATE531944T1 (en) | 2011-11-15 |
| KR20070089080A (en) | 2007-08-30 |
| NO20071076L (en) | 2007-08-28 |
| EP1826413A2 (en) | 2007-08-29 |
| EP1826413B1 (en) | 2011-11-02 |
| CA2579387A1 (en) | 2007-08-27 |
| JP5314852B2 (en) | 2013-10-16 |
| CN101029647B (en) | 2014-11-26 |
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