Patent Grant
7785074
1. Field of the Invention
The field of the present invention relates to a blade of a rotor of a second stage of a compressor.
More specifically, the invention relates to a blade of a rotor having a high aerodynamic efficiency of a second stage of a compressor.
2. Related Art
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 stages, 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 second stage of a compressor an extremely high efficiency is required, at the same time maintaining an appropriate aerodynamic and mechanical load.
What is needed is:
A blade of a rotor of a second stage of a compressor which avoids, or in any case reduces, resonance problems due to the stimulation of natural frequencies and at the same time allows a high aerodynamic efficiency;
A blade of a rotor of a second stage of a compressor which avoids or in any case reduces resonance problems due to the stimulation of natural frequencies and which allows a useful life of the blade itself; and
A rotor of a second 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.
Embodiments of the present invention meet the needs referenced above and exhibit additional characteristics by providing a rotor blade of a second stage of a compressor.
Further characteristics of the invention are indicated in the subsequent claims.
The characteristics and advantages of a rotor blade of a second stage 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:
With reference to the figures, a blade 10 is provided of a rotor of a second stage 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 the 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 situated midway up the blade 10.
In other words, said thickening 30 confers a dynamic behaviour to said blade 10 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 consequently be dimensioned so as to further increase the performances of the compressor itself.
This is possible as the blade, upon deforming, is prevented 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 a decreasing trend whose slope varies three times, defining four regions. For example, the variation in the trend of the maximum thickness is shown in
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 according to a polynomial function of the sixth degree and in particular said polynomial function is
Tmax=−21.119*h6+70.467*h5−85.603*h4+44.523*h3−7.8323*h2−1.1541*h+0.997
wherein h represents the percentage of the height of the blade 10, and wherein Tmax is the maximum adimensionalized thickness relating to the closed curve corresponding to that percentage of the height of the blade 10.
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 1, whose values, expressed in millimeters, refer to an aerodynamic profile at room temperature, in particular 25° C.
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 1 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 1 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 second stage 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 second stage of a compressor according to the present invention achieves the objectives specified above.
The rotor blade of a second stage 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.
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| Number | Date | Country | |
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