CN219282082U - Centrifugal compressor diffuser and centrifugal compressor - Google Patents
Centrifugal compressor diffuser and centrifugal compressor Download PDFInfo
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Abstract
The utility model provides a centrifugal compressor diffuser and a centrifugal compressor, wherein the centrifugal compressor diffuser comprises: the device comprises a shell and blades, wherein the blades are arranged on the inner wall of the shell, a single blade is used as a reference, the flow direction of air flow in the shell is taken as an x axis, the front edge of each blade is taken as an O point, and the direction perpendicular to the x axis is taken as a y axis to establish an xy axis coordinate system; and a blade camber line installation angle beta is clamped between a tangent line of each position on the middle camber line and the y axis, and the blade camber line installation angle follows a cubic function along the flow direction distribution rule: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And is less than or equal to 1. According to the utility model, the air on the suction surface is not separated in the downstream flowing process, the suction surface is not generated in a low Mach number area, the backflow of the hub position on the suction surface of the diffuser is eliminated, and the impact loss of air flow is reduced.
Description
Technical Field
The utility model relates to the technical field of compressors, in particular to a centrifugal compressor diffuser and a centrifugal compressor.
Background
As a key component of the air cycle machine and an upstream component of a turbine component in the air cycle machine, the compressor can reduce the speed and boost the pressure of incoming low-pressure air and drive high-pressure air to further flow into the turbine so as to finish the expansion work process. It can be seen that the supercharging capacity of the compressor directly affects the power capability of the turbine, and thus the system performance of the air cycle machine. The compressor impeller directly acts on the total pressure rise of the gas, and the diffuser at the downstream of the impeller plays a role of reducing speed and diffusing pressure, so that the diffuser and the compressor impeller are required to be well matched, and the compressor has higher efficiency and pressure ratio under the whole-stage redesign working condition.
As the hub position of the suction surface of the diffuser in the prior art has the technical problems of large airflow impact loss, large entropy increase and the like, the utility model designs the diffuser of the centrifugal compressor and the centrifugal compressor.
Disclosure of Invention
Therefore, the utility model aims to overcome the defect that the hub position of the suction surface of the diffuser in the prior art has backflow, and further provides the diffuser of the centrifugal compressor and the centrifugal compressor.
In order to solve the above problems, the present utility model provides a centrifugal compressor diffuser comprising:
the device comprises a shell and blades, wherein the blades are arranged on the inner wall of the shell, the single blade is used as a reference, the flow direction of air flow in the shell is used as an x axis, the front edge of each blade is used as an O point, and the direction perpendicular to the x axis is used as a y axis to establish an xy axis coordinate system;
the blade further comprises a tail edge, a pressure surface and a suction surface, wherein a camber line of the blade is a camber line segment connecting the front edge and the tail edge of the blade, and the minimum distance between each point on the camber line and the pressure surface is equal to the minimum distance between each point on the camber line and the suction surface;
and an included angle is clamped between the tangent line of each position on the middle arc line and the y axis, namely the blade middle arc line installation angle beta, and the blade middle arc line installation angle follows a cubic function along the flow direction distribution rule: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And the angle is less than or equal to 1, and beta is the camber line installation angle of the blade corresponding to the position.
In some embodiments, a 1 ＝76.288±0.006，B 1 ＝-59.586±0.058，C 1 ＝113.578±0.137，D 1 ＝-65.873±0.091。
In some embodiments, the chord length of the blade is a straight line segment connecting the leading edge and the trailing edge of the blade, denoted by C, and the thickness h of the blade is a distance between the pressure surface and the suction surface at any position on the blade along the direction of the perpendicular to the chord length of the blade;
the distribution law of the thickness of the blade follows a cubic function: h=a 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And h is less than or equal to 1 and is the thickness of the blade corresponding to the position.
In some embodiments, a 2 ＝0.389±0.004，B 2 ＝8.688±0.003，C 2 ＝1.743±0.007，D 2 ＝-10.298±0.004。
In some embodiments, the minimum distance between two adjacent vanes at any one location is the throat distance at that location, the throat area S being the throat distance multiplied by the vane height; and has the following components:
the throat area S follows a five-order function along the flow direction distribution rule: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And S is equal to or less than 1, and the throat area corresponding to the position is S.
In some embodiments, a 3 ＝37.426±0.377，B 3 ＝-301.008±4.455，C 3 ＝1154.700±20.081，D 3 ＝-2052.157±43.322，E 3 ＝1679.370±44.920，F 3 ＝-478.755±17.983。
In some embodiments, the spacing between the trailing edges of two adjacent blades along the y-axis is the pitch L, the consistency of the blades δ=c/L.
In some embodiments, the number of vanes is 13, diffuser outlet total pressure/inlet total pressure
＝0.985±0.02。
The utility model also provides a centrifugal compressor, which comprises the centrifugal compressor diffuser.
The centrifugal compressor diffuser and the centrifugal compressor provided by the utility model have the following beneficial effects:
the utility model follows a cubic function by setting the camber line installation angle of the blade to be distributed along the flow direction: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 In particular A 1 ＝76.288±0.006，B 1 ＝-59.586±0.058，C 1 ＝113.578±0.137，D 1 The method has the advantages that the method comprises the following steps that = -65.873 +/0.091, in an optimized diffuser flow passage, the air flow at the inlet position of the diffuser is attached to the blades to enter the flow passage, the air of the suction surface is not separated in the downstream flowing process, the suction surface is not generated in a low Mach number area, and the hub position of the suction surface of the original diffuser is effectively eliminatedThe back flow is arranged, so that the impact loss of the air flow is reduced; and the utility model follows the distribution rule of the thickness of the blade to a cubic function: h=a 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 In particular A 2 ＝0.389±0.004，B 2 ＝8.688±0.003，C 2 ＝1.743±0.007，D 2 = -10.298 ±0.004, the throat area S follows a five-order function along the flow direction distribution law: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 In particular A 3 ＝37.426±0.377，
B 3 ＝-301.008±4.455，C 3 ＝1154.700±20.081，D 3 ＝-2052.157±43.322，E 3 ＝1679.370±44.920，F 3 The internal entropy value of the optimized diffuser flow channel is obviously lower than that of the original design scheme, a high entropy area does not exist in the flow channel, and a relatively high entropy value is only generated on the surface of the blade and in the wake area; therefore, the diffuser can ensure that the incoming air is attached to the surface of the blade and enters the flow passage, suction surface separation is not generated in the downstream flowing process, unnecessary loss in the flow passage is restrained, entropy increase is controlled in the boundary layer of the blade surface, and no obvious loss exists in the flow passage.
Drawings
FIG. 1 is a block diagram of a centrifugal compressor diffuser of the present utility model;
FIG. 2 is a block diagram of the assembly of a centrifugal compressor diffuser and a volute of the present utility model;
FIG. 3 is a schematic view of a vane configuration of a centrifugal compressor diffuser of the present utility model;
FIG. 4 is a graph of the distribution of blade mounting angles along the flow direction of the present utility model;
FIG. 5 is a graph of the blade thickness profile along the flow direction of the present utility model;
FIG. 6 is a graph of the throat area distribution along the flow direction of a diffuser of the present utility model;
FIG. 7 is a Mach number distribution plot (as opposed to prior art schemes) within an optimized diffuser flow path of the present utility model;
FIG. 8 is an entropy distribution diagram (in contrast to prior art schemes) within an optimized diffuser flow path of the present utility model.
The reference numerals are expressed as:
1. a housing; 2. a blade; 21. a leading edge; 22. a trailing edge; 23. a pressure surface; 24. a suction surface; 25. a mean camber line; 3. a throat; 4. and a volute.
Detailed Description
As shown in fig. 1-8, the present utility model provides a centrifugal compressor diffuser comprising:
the device comprises a shell 1 and blades 2, wherein the blades 2 are arranged on the inner wall of the shell 1, the single blades 2 are used as references, the flow direction of air flow in the shell 1 is used as an x axis, the front edge 21 of each blade 2 is used as an O point, and the direction perpendicular to the x axis is used as a y axis to establish an xy axis coordinate system;
the blade 2 further comprises a trailing edge 22, a pressure surface 23 and a suction surface 24, wherein a camber line 25 of the blade is a camber line connecting the leading edge 21 and the trailing edge 22 of the blade 2, and the minimum distance between each point on the camber line 25 and the pressure surface 23 and the suction surface 24 is equal;
and an included angle is formed between the tangent line of each position on the camber line 25 and the y-axis, namely a blade camber line installation angle beta, and the blade camber line installation angle follows a cubic function along the flow direction distribution rule: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And the angle is less than or equal to 1, and beta is the camber line installation angle of the blade corresponding to the position.
The utility model follows a cubic function by setting the camber line installation angle of the blade to be distributed along the flow direction: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 In particular A 1 ＝76.288±0.006，B 1 ＝-59.586±0.058，C 1 ＝113.578±0.137，D 1 In the optimized diffuser flow channel, the air flow at the inlet position of the diffuser is attached to the blades to enter the flow channel, the air at the suction surface is not separated in the downstream flowing process, no low Mach number area is generated on the suction surface, and backflow at the hub position of the suction surface of the original diffuser is effectively eliminated, so that the impact loss of the air flow is reduced.
The utility model solves the following technical problems:
1. the utility model eliminates the backflow of the hub position of the suction surface of the original diffuser (because the suction surface air is not separated in the downstream flow process, the suction surface has no low Mach number zone);
2. the air flow at the inlet of the diffuser is attached to the blades to enter the flow channel, so that the impact loss of the air flow is reduced;
3. the utility model controls the entropy increase in the boundary layer of the leaf surface, and no obvious loss exists in the flow channel.
In some embodiments, a 1 ＝76.288±0.006，B 1 ＝-59.586±0.058，C 1 ＝113.578±0.137，D 1 ＝-65.873±0.091。
FIG. 3 is a schematic illustration of some of the geometric design parameters of a diffuser blade, including the mounting angle and pitch of the diffuser, the arc length, and the flow direction, as determined by the following design method.
Diffuser inlet design:
1. determining total parameters of the inlet gas state of the diffuser, such as total temperature, total pressure and the like;
2. giving the radius of the inlet of the diffuser, and calculating to obtain the tangential speed of the inlet of the diffuser by using the conservation of angular momentum theorem;
3. the airflow angle of the inlet of the diffuser is calculated by utilizing a flow function, so that the installation angle beta of the inlet of the blade can be determined;
4. after the calculation is completed, the flow direction speed component of the inlet of the diffuser can be determined, and then the static gas state parameter of the inlet can be obtained.
Diffuser outlet design:
5. giving the outlet mounting angle of the diffuser blades;
6. giving the ratio of the radius of the diffuser outlet to the inlet;
7. calculating the arc length, equivalent expansion angle, consistency and the like of the diffuser blade, determining whether the equivalent expansion angle and consistency are in a reasonable range, if so, pushing out a design flow, and if not, returning to the step 5 for new iterative design.
After the geometric parameters are determined, the three-dimensional modeling design of the blade can be unfolded, namely the distribution of the installation angle and the thickness of the blade in the flow direction is determined. As shown in fig. 4, the diffuser vane camber line mounting angle follows a cubic function along the flow direction distribution law: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 The method comprises the steps of carrying out a first treatment on the surface of the The coefficient values are shown in Table 1 (x) 1 For the relative position 0.ltoreq.x along the flow direction 1 And (1), wherein beta is a blade mounting angle corresponding to the relative position of the flow direction, so that the blade mounting angle distribution along the flow direction can be determined.
TABLE 1 diffuser blade camber line mounting angle distribution function coefficient values along flow direction
| Coefficients of | Value of |
| A 1 | 76.288±0.006 |
| B 1 | -59.586±0.058 |
| C 1 | 113.578±0.137 |
| D 1 | -65.873±0.091 |
In some embodiments, the chord length of the blade is a straight line segment connecting the leading edge 21 and the trailing edge 22 of the blade 2, denoted by C (i.e., the chord length of the blade is C), and the thickness h of the blade is a distance between the pressure surface 23 and the suction surface 24 along a perpendicular line direction of the chord length of the blade at any position on the blade;
the distribution law of the thickness of the blade follows a cubic function: h=a 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And h is less than or equal to 1 and is the thickness of the blade corresponding to the position.
The utility model follows the distribution rule of the thickness of the blade to a cubic function:
h＝A 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 in particular A 2 ＝0.389±0.004，B 2 ＝8.688±0.003，C 2 ＝1.743±0.007，D 2 = -10.298 ±0.004, the throat area S follows a five-order function along the flow direction distribution law: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 In particular A 3 ＝37.426±0.377，B 3 ＝-301.008±4.455，C 3 ＝1154.700±20.081，D 3 ＝-2052.157±43.322，E 3 ＝1679.370±44.920，F 3 The internal entropy value of the optimized diffuser flow channel is obviously lower than that of the original design scheme, a high entropy area does not exist in the flow channel, and a relatively high entropy value is only generated on the surface of the blade and in the wake area; the diffuser is therefore capable of ensuring that incoming air enters the flow passage against the vane surface and does not flow downstreamThe suction surface separation is generated, unnecessary loss in the flow channel is restrained, the entropy increase is controlled in the boundary layer of the blade surface, and no obvious loss exists in the flow channel.
In some embodiments, a 2 ＝0.389±0.004，B 2 ＝8.688±0.003，C 2 ＝1.743±0.007，D 2 ＝-10.298±0.004。
The variation of blade thickness in the flow direction is given by fig. 5. The thickness distribution rule thereof follows a cubic function: h=a 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 The method comprises the steps of carrying out a first treatment on the surface of the The coefficient values are shown in Table 2 (x) 1 For the relative position 0.ltoreq.x along the flow direction 1 And h is less than or equal to 1 and corresponds to the thickness of the blade at the opposite position of the flow direction). And the blades are symmetrically distributed on two sides of the mean camber line by taking the mean camber line as a reference. Thereby, the blade thickness is determined.
TABLE 2 coefficient values of blade thickness distribution function along flow direction
| Coefficients of | Value of |
| A 2 | 0.389±0.004 |
| B 2 | 8.688±0.003 |
| C 2 | 1.743±0.007 |
| D 2 | -10.298±0.004 |
In some embodiments, the minimum distance between two adjacent blades at any one location is the throat 3, which is the throat distance at that location, the throat area S being the throat distance multiplied by the blade height (the blade is a stretched body, the blade height is the length in its stretched direction, i.e. the blade length in the direction perpendicular to the paper surface is the blade height as shown in fig. 3); and has the following components:
the throat area S follows a five-order function along the flow direction distribution rule: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And S is equal to or less than 1, and the throat area corresponding to the position is S.
In some embodiments, a 3 ＝37.426±0.377，B 3 ＝-301.008±4.455，C 3 ＝1154.700±20.081，D 3 ＝-2052.157±43.322，E 3 ＝1679.370±44.920，F 3 ＝-478.755±17.983。
In summary, it can be further determined that the throat area of the device follows the five-order function along the flow direction distribution rule: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 The method comprises the steps of carrying out a first treatment on the surface of the The coefficient values are shown in Table 3 (x) 1 For the relative position x in the flow direction of 0.2 ∈x 1 Less than or equal to 0.8, S is diffuser throat flow area corresponding to the relative position of the flow direction).
TABLE 3 throat area distribution function coefficient values along flow direction
| Coefficients of | Value of |
| A 3 | 37.426±0.377 |
| B 3 | -301.008±4.455 |
| C 3 | 1154.700±20.081 |
| D 3 | -2052.157±43.322 |
| E 3 | 1679.370±44.920 |
| F 3 | -478.755±17.983 |
In some embodiments, the spacing between the trailing edges of two adjacent blades 2 along the y-axis is the pitch L, the consistency of the blades δ=c/L.
FIG. 7 shows Mach number distribution in a centrifugal compressor diffuser flow path under design conditions of the present utility model, where the inlets of the initial design and the optimal design maintain good flow conditions, and where the suction side air is not separated during downstream flow in the optimized diffuser flow path, and where the suction side is not created in a low Mach number region.
FIG. 8 shows the entropy distribution in the diffuser flow path of the centrifugal compressor under the design condition of the present utility model, the internal entropy value of the diffuser flow path after optimization is obviously lower than that of the original design scheme, and the optimization scheme only generates higher entropy value on the surface of the blade and the wake area, and the partial loss is unavoidable; and a high entropy area does not exist in the flow channel of the optimization scheme. Therefore, the diffuser can ensure that the incoming air enters the flow passage by being attached to the surface of the blade, and no suction surface separation is generated in the downstream flow process, and meanwhile, unnecessary loss in the flow passage is restrained.
In some embodiments, the number of vanes 2 is 13, and the total diffuser outlet pressure/inlet pressure=0.985±0.02. As shown in table 4 below:
TABLE 4 initial, optimization scheme comparison
Table 4 shows that the number of blades of the optimized solution is greatly reduced and the loss of air flowing in the diffuser is significantly reduced, compared with the original solution before the optimized solution.
The utility model also provides a centrifugal compressor, which comprises the centrifugal compressor diffuser.
The utility model provides a centrifugal compressor diffuser and a design thought of a low-consistency diffuser suitable for low-pressure ratio centrifugal compressors, which can determine the low-consistency diffuser type suitable for most low-pressure compressors, and can inhibit the generation of separation vortex on the suction surface of the diffuser by utilizing the design thought, eliminate the loss caused by the separation vortex and improve the pneumatic performance of the diffuser; the centrifugal compressor diffuser provided in combination with the method has the following advantages: the inlet incoming flow of the rotor can be completely matched with the geometry of the blade, and impact loss caused by attack angle can be effectively restrained. Under the condition of meeting the performance requirement, the diffuser quality can be reduced and the machining difficulty can be reduced by reducing the number of blades.
The foregoing description of the preferred embodiments of the utility model is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the utility model. The foregoing is merely a preferred embodiment of the present utility model, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present utility model, and these modifications and variations should also be regarded as the scope of the utility model.
Claims (9)
1. A centrifugal compressor diffuser, characterized by: comprising the following steps:
the device comprises a shell (1) and blades (2), wherein the blades (2) are arranged on the inner wall of the shell (1), the flow direction of air flow in the shell (1) is taken as an x-axis based on the single blades (2), the front edge (21) of each blade (2) is taken as an O point, and an xy-axis coordinate system is established by taking the direction perpendicular to the x-axis as a y-axis;
the blade (2) further comprises a trailing edge (22), a pressure surface (23) and a suction surface (24), wherein a camber line (25) of the blade is a camber line connecting a front edge (21) and the trailing edge (22) of the blade (2), and the minimum distance between each point on the camber line (25) and the pressure surface (23) and the suction surface (24) is equal;
and an included angle is formed between a tangent line of each position on the camber line (25) and the y axis, namely a blade camber line installation angle beta, and the blade camber line installation angle follows a cubic function along the flow direction distribution rule: beta=a 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And the angle is less than or equal to 1, and beta is the camber line installation angle of the blade corresponding to the position.
2. The centrifugal compressor diffuser of claim 1, wherein:
A 1 ＝76.288±0.006，B 1 ＝-59.586±0.058，C 1 ＝113.578±0.137，D 1 ＝-65.873±0.091。
3. the centrifugal compressor diffuser of claim 1, wherein:
the chord length of the blade is a straight line segment connecting the front edge (21) and the tail edge (22) of the blade (2), the straight line segment is denoted by C, the thickness h of the blade is the distance between the pressure surface (23) and the suction surface (24) along the vertical line direction of the chord length of the blade at any position on the blade;
the distribution law of the thickness of the blade follows a cubic function: h=a 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And h is less than or equal to 1 and is the thickness of the blade corresponding to the position.
4. A centrifugal compressor diffuser according to claim 3, wherein:
A 2 ＝0.389±0.004，B 2 ＝8.688±0.003，C 2 ＝1.743±0.007，D 2 ＝-10.298±0.004。
5. the centrifugal compressor diffuser of claim 1, wherein:
the minimum distance between two adjacent blades at any position is the throat (3), the distance is the throat distance at the position, and the throat area S is the throat distance multiplied by the blade height; and has the following components:
the throat area S follows a five-order function along the flow direction distribution rule: s=a 3 +B 3 x 1 +C 3 x 1 2 +D 3 x 1 3 +E 3 x 1 4 +F 3 x 1 5 Wherein x is 1 X is equal to or less than 0 and is equal to or less than the projection length of the total length of the mean camber line on the x axis, and the x value of any position on the mean camber line is divided by the projection length of the total length of the mean camber line on the x axis 1 And S is equal to or less than 1, and the throat area corresponding to the position is S.
6. The centrifugal compressor diffuser of claim 1, wherein:
A 3 ＝37.426±0.377，B 3 ＝-301.008±4.455，C 3 ＝1154.700±20.081，
D 3 ＝-2052.157±43.322，E 3 ＝1679.370±44.920，F 3 ＝-478.755±17.983。
7. a centrifugal compressor diffuser according to claim 3, wherein:
the pitch between the trailing edges of two adjacent blades (2) in the y-axis direction is the pitch L, the consistency of the blades delta = C/L.
8. A centrifugal compressor diffuser according to claim 3, wherein:
the number of the blades (2) is 13, and the total pressure of the diffuser outlet/the total pressure of the inlet=0.985+/-0.02.
9. A centrifugal compressor, characterized by: comprising a centrifugal compressor diffuser according to any one of claims 1-8.
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