CN115929694A - Centrifugal compressor diffuser and centrifugal compressor - Google Patents
Centrifugal compressor diffuser and centrifugal compressor Download PDFInfo
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Abstract
The invention provides a centrifugal compressor diffuser and a centrifugal compressor, wherein the centrifugal compressor diffuser comprises: the blade is arranged on the inner wall of the shell, a single blade is taken as a reference, the flowing direction of airflow in the shell is taken as an x axis, the front edge of the blade is taken as an O point, and the direction vertical to the x axis is taken as a y axis to establish an xy axis coordinate system; a blade mean camber line installation angle beta is clamped between a tangent line of each position on the mean camber line and the y axis, and the blade mean camber line installation angle follows a cubic function along a flow direction distribution rule: β = A 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 Less than or equal to 1. According to the invention, the air on the suction surface is not separated in the downstream flowing process, no low Mach number area is generated on the suction surface, and the suction surface of the diffuser is eliminatedAnd the backflow at the hub position reduces the air flow impact loss.
Description
Technical Field
The invention relates to the technical field of compressors, in particular to a centrifugal compressor diffuser and a centrifugal compressor.
Background
As a key part of the air cycle machine and an upstream component of a turbine part in the air cycle machine, the air compressor can decelerate and pressurize incoming low-pressure air and drive high-pressure air to further flow into the turbine to complete an expansion work-doing process. It can be seen that the boost capability of the compressor directly affects the work capacity of the turbine, which in turn affects the system performance of the air cycle machine. The compressor impeller directly acts on the total pressure rise of gas in the compressor, and the diffuser at the downstream of the impeller plays a role in speed reduction and pressure expansion, and the diffuser has to be well matched with the compressor impeller to enable the compressor to have higher efficiency and pressure ratio under the working condition of the whole stage redesign.
The invention researches and designs a diffuser of a centrifugal compressor and the centrifugal compressor, because the technical problems of backflow, large air flow impact loss, large entropy increase and the like exist at the hub position of the suction surface of the diffuser in the prior art.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect of backflow at the hub position of the suction surface of the diffuser in the prior art, so that the diffuser of the centrifugal compressor and the centrifugal compressor are provided.
In order to solve the above problems, the present invention provides a centrifugal compressor diffuser, comprising:
the blade is arranged on the inner wall of the shell, the single blade is used as a reference, the flowing direction of airflow in the shell is used as an x axis, the front edge of the blade is 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 also comprises a trailing edge, a pressure surface and a suction surface, a mean camber line of the blade is a camber line segment connecting the leading edge and the trailing edge of the blade, and the minimum distances from each point on the mean camber line to the pressure surface and the suction surface are equal;
and each position on the mean camber lineAn included angle is formed between the tangent and the y axis, namely the included angle is a mounting angle beta of the camber line of the blade, and the mounting angle of the camber line of the blade follows a cubic function along a 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 the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 Not more than 1, beta is the installation angle of the camber line 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 blade chord length is a straight line segment connecting the leading edge and the trailing edge of the blade, and is denoted by C, and the blade thickness h is the distance between the pressure surface and the suction surface along the perpendicular direction of the blade chord length at any position on the blade;
the distribution rule of the blade thickness 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 the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 The thickness of the blade corresponding to the position is less than or equal to 1,h.
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, and the throat area S is the throat distance multiplied by the vane height; and comprises the following components:
the distribution rule of the throat area S along the flow direction follows a quintic function: 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 Dividing the x value of any position on the mean camber line by the projection length of the total length of the mean camber line on the x axis, wherein x is more than or equal to 0 1 Less than or equal to 1,S is the area of the throat corresponding to the position.
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 direction is a pitch L, and the consistency of the blades δ = C/L.
In some embodiments, the number of the blades is 13, and the total pressure at the outlet/the total pressure at the inlet of the diffuser
＝0.985±0.02。
The invention also provides a centrifugal compressor which comprises the centrifugal compressor diffuser.
The diffuser of the centrifugal compressor and the centrifugal compressor provided by the invention have the following beneficial effects:
the invention sets the camber line installation angle of the blade to follow a cubic function along the distribution rule of the flow direction: β = 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 flow velocity of air at the inlet of the optimized diffuser enters the flow channel by attaching the blades to the flow channel, the air at the suction surface is not separated in the downstream flowing process, and no low Mach number region is generated on the suction surface, so that the backflow at the hub position of the original suction surface of the diffuser is effectively eliminated, and the impact loss of the air flow is reduced; in addition, the distribution rule 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 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, and the distribution law of the throat area S in the flow direction follows a quintic function: 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 = 478.755 ± 17.983, so that the entropy value in the optimized diffuser flow passage is obviously lower than that in the initial design scheme, no high-entropy area exists in the flow passage, and relatively high entropy values are generated only on the surface of the blade and in the wake area; therefore, the diffuser can ensure that the incoming flow air is attached to the surface of the blade and enters the flow channel, and no suction surface separation is generated in the downstream flow process, meanwhile, unnecessary loss in the flow channel is restrained, entropy increase is controlled in the boundary layer of the blade surface, and no obvious loss exists in the flow channel.
Drawings
FIG. 1 is a block diagram of a centrifugal compressor diffuser of the present invention;
FIG. 2 is a view of the assembled structure of the centrifugal compressor diffuser and volute of the present invention;
FIG. 3 is a schematic view of the vane structure of the centrifugal compressor diffuser of the present invention;
FIG. 4 is a graph of the distribution of blade stagger angles in the flow direction of the present invention;
FIG. 5 is a graph of the distribution of blade thickness in the flow direction of the present invention;
FIG. 6 is a graph of the distribution of the throat area of a diffuser of the present invention in the flow direction;
FIG. 7 is a graph of Mach number distribution in the flow path of an optimized diffuser according to the present invention (in comparison to prior art solutions);
FIG. 8 is a graph of the entropy distribution within the flow path of an optimized diffuser of the present invention (in comparison to prior art solutions).
The reference numerals are represented 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. a volute.
Detailed Description
As shown in fig. 1-8, the present invention 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, a single blade 2 is taken as a reference, the flow direction of airflow in the shell 1 is taken as an x axis, the front edges 21 of the blades 2 are O points, and the direction perpendicular to the x axis is taken 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, a mean camber line 25 of the blade is an arc line segment connecting the leading edge 21 and the trailing edge 22 of the blade 2, and the minimum distance between each point on the mean camber line 25 and the pressure surface 23 and the suction surface 24 is equal;
an included angle is formed between a tangent line of each position on the camber line 25 and the y axis, namely the mounting angle beta of the camber line of the blade, and the mounting angle of the camber line of the blade follows a cubic function along a flow direction distribution rule: β = A 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 X is the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 Not more than 1, beta is the installation angle of the camber line of the blade corresponding to the position.
The invention sets the camber line installation angle of the blade to follow a cubic function along the distribution rule of the flow direction: β = 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 flow velocity of the air flow at the inlet of the diffuser enters the flow channel after optimization, the air at the suction surface is not separated in the downstream flowing process, no low Mach number region is generated on the suction surface, and the backflow at the hub position of the original suction surface of the diffuser is effectively eliminated, so that the flow velocity of the air flow at the inlet of the diffuser is reduced to 65.873 +/-0.091Small air flow shock losses.
The invention solves the following technical problems:
1. the invention eliminates the backflow of the original diffuser suction surface hub position (because the air of the suction surface is not separated in the downstream flowing process, the suction surface has no low Mach number area);
2. the air flow at the inlet of the diffuser is attached to the blade and enters the flow channel, so that the impact loss of the air flow is reduced;
3. the invention controls entropy increase in the boundary layer of the leaf surface, and has no obvious loss in a 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 view of some of the geometric design parameters of the diffuser blades, including the stagger angle and pitch, arc length, and flow direction of the diffuser, which can be determined by the design method described below.
Diffuser inlet design:
1. determining total parameters of the state of gas at the inlet of the diffuser, such as total temperature, total pressure and the like;
2. giving the radius of the diffuser inlet, and calculating by utilizing the angular momentum conservation theorem to obtain the tangential velocity of the diffuser inlet;
3. calculating to obtain an airflow angle of the inlet of the diffuser by utilizing a flow function, so that the mounting angle beta of the inlet of the blade can be determined;
4. after the calculation is completed, the flow direction velocity component of the diffuser inlet can be determined, and then the static parameters of the gas state at the inlet and the outlet can be obtained.
Designing the outlet of the diffuser:
5. setting the outlet installation angle of the diffuser blade;
6. giving the radius ratio of the diffuser outlet to the diffuser inlet;
7. calculating the arc length, the equivalent expansion angle, the consistency and the like of the diffuser blade, determining whether the equivalent expansion angle and the consistency are in a reasonable range interval, if the equivalent expansion angle and the consistency meet the requirements, deducing a design flow, and if the equivalent expansion angle and the consistency do not meet the requirements, returning to the step 5 for a new round of iterative design.
After the geometric parameters are determined, the three-dimensional modeling design of the blade can be expanded, namely the installation angle and the thickness distribution of the blade in the flow direction are determined. As shown in fig. 4, the camber line setting angle of the diffuser blade follows a cubic function in the flow direction distribution law: beta = A 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 (ii) a The coefficient values are shown in Table 1 (x) 1 X is more than or equal to 0 at the relative position along the flow direction 1 Is less than or equal to 1, and beta is the blade mounting angle corresponding to the relative position of the flow direction), thereby the blade mounting angle can be determined along the flow direction distribution.
TABLE 1 diffuser vane mean camber line installation angle along flow distribution function coefficient values
| Coefficient of performance | 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 blade chord length is a straight line segment connecting the leading edge 21 and the trailing edge 22 of the blade 2, and is denoted by C (i.e. the blade chord length is C), and the blade thickness h is the distance between the pressure surface 23 and the suction surface 24 at any position on the blade along the perpendicular direction of the blade chord length;
the distribution rule of the blade thickness 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 the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 The thickness of the blade corresponding to the position is less than or equal to 1,h.
The invention makes the distribution rule of the blade thickness follow 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, and the distribution rule of the throat area S in the flow direction follows a quintic function: 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 = -478.755 +/-17.983, so that the internal entropy of the optimized diffuser flow passage is obviously lower than that of the initial design scheme, a high entropy area does not exist in the flow passage, and a relatively high entropy value is generated only on the surface of the blade and a wake area; therefore, the diffuser can ensure that the incoming air is attached to the surface of the blade and enters the flow channel, no suction surface separation is generated in the downstream flowing process, unnecessary loss in the flow channel is restrained, 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 the blade thickness in the flow direction is given by fig. 5. It is provided withThe thickness distribution law follows a cubic function: h = A 2 +B 2 x 1 +C 2 x 1 2 +D 2 x 1 3 (ii) a The coefficient values are shown in Table 2 (x) 1 X is more than or equal to 0 in the relative position of the flow direction 1 Less than or equal to 1,h is the thickness of the blade corresponding to the opposite position of the flow direction). And the thickness of the blade is 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 values of distribution function coefficients of blade thickness along flow direction
| Coefficient of performance | 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 lobes at any one location is the throat 3, which is the throat distance at that location, and the throat area S is the throat distance multiplied by the lobe height (a lobe is a stretched body and the lobe height is the length in its stretch direction, i.e. the length of the lobe in the direction perpendicular to the plane of the paper as shown in fig. 3 is the lobe height); and comprises the following components:
the distribution rule of the throat area S along the flow direction follows a quintic function: 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 Dividing the x value of any position on the mean camber line by the projection length of the total length of the mean camber line on the x axis, wherein x is more than or equal to 0 1 Less than or equal to 1,S is the area of the throat corresponding to the position.
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 conclusion, it can be further determined that the distribution law of the throat area along the flow direction follows a quintic function: 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 (ii) a The coefficient values are shown in Table 3 (x) 1 X is more than or equal to 0.2 in the relative position of the flow direction 1 Less than or equal to 0.8, S is the flow area of the throat of the diffuser corresponding to the opposite position of the flow direction).
TABLE 3 throat area distribution function coefficient values along flow direction
| Coefficient of performance | 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 distance between the trailing edges of two adjacent blades 2 along the y-axis direction is a pitch L, and the consistency of the blades δ = C/L.
FIG. 7 shows Mach number distribution in the diffuser flow channel of the centrifugal compressor under the design condition of the present invention, the inlets of the initial design scheme and the optimized design scheme maintain good flow state, and in the optimized diffuser flow channel, the air on the suction surface is not separated in the downstream flow process, and no low Mach number region is generated on the suction surface.
FIG. 8 shows the entropy distribution in the diffuser flow channel of the centrifugal compressor under the design condition of the present invention, the entropy value in the optimized diffuser flow channel is significantly lower than that in the initial design scheme, and the optimization scheme only generates a relatively high entropy value on the blade surface and the wake region, and this part of the loss is unavoidable; and no high-entropy area exists in the flow channel of the optimization scheme. Therefore, the diffuser can ensure that the incoming air is attached to the surface of the blade and enters the flow channel, and the suction surface separation is not generated in the downstream flow process, and meanwhile, unnecessary loss in the flow channel is restrained.
In some embodiments, the number of the blades 2 is 13, and the diffuser outlet total pressure/inlet total pressure =0.985 ± 0.02. As shown in table 4 below:
TABLE 4 initial, optimized protocol comparison
Table 4 shows the comparison of the optimized version of the present invention with the original version before optimization, the optimized version having a greatly reduced number of blades and significantly reduced losses due to the air flow in the diffuser.
The invention also provides a centrifugal compressor which comprises the centrifugal compressor diffuser.
The invention provides a centrifugal compressor diffuser and a low-consistency diffuser design idea suitable for a low-pressure-ratio centrifugal compressor, which can determine the type of the low-consistency diffuser suitable for most of the low-pressure compressors, and can inhibit the generation of separation vortex on the suction surface of the diffuser, eliminate the loss generated by the separation vortex, and improve the pneumatic performance of the diffuser; the centrifugal compressor diffuser provided by combining the method has the following advantages: the inlet incoming flow of the rotor can be completely matched with the geometry of the blade, and the impact loss generated by an attack angle can be effectively inhibited. Under the condition of meeting the performance requirement, the quality of the diffuser can be reduced by reducing the number of the blades, and the machining difficulty is reduced.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents and improvements made within the spirit and principle of the present invention are intended to be included within the scope of the present invention. The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (9)
1. A centrifugal compressor diffuser characterized by: the method comprises 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), a single blade (2) is used as a reference, the flow direction of airflow in the shell (1) is used as an x axis, the front edge (21) of each blade (2) is an O point, and a 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), a mean camber line (25) of the blade is a camber line segment connecting the leading edge (21) and the trailing edge (22) of the blade (2), and the minimum distances from each point on the mean camber line (25) to the pressure surface (23) and the suction surface (24) are equal;
an included angle is formed between a tangent line of each position on the mean camber line (25) and the y axis, namely the mounting angle beta of the mean camber line of the blade, and the mounting angle of the mean camber line of the blade follows a cubic function along a flow direction distribution rule: β = A 1 +B 1 x 1 +C 1 x 1 2 +D 1 x 1 3 Wherein x is 1 Dividing the x value of any position on the mean camber line by the projection length of the total length of the mean camber line on the x axis, wherein x is more than or equal to 0 1 Not more than 1, beta is the installation angle of the camber line 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 blade chord length is a straight line segment connecting a front edge (21) and a tail edge (22) of the blade (2), and is represented by C, the blade thickness h is the distance between the pressure surface (23) and the suction surface (24) at any position on the blade along the perpendicular direction of the blade chord length;
the distribution rule of the blade thickness 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 the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 Less than or equal to 1,hThe position corresponds to the blade thickness.
4. The centrifugal compressor diffuser of 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 any of claims 1 to 4, wherein:
the throat (3) is arranged at the position of the minimum distance between two adjacent blades at any position, 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 distribution rule of the throat area S along the flow direction follows a quintic function: 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 the projection length of the x axis of the total length of the mean camber line divided by the value of x at any position on the mean camber line, and x is more than or equal to 0 1 The throat area corresponding to the position is less than or equal to 1,S.
6. The centrifugal compressor diffuser of any one of claims 1 to 5, 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. the centrifugal compressor diffuser of claim 3, wherein:
the distance between the tail edges of two adjacent blades (2) along the y-axis direction is a pitch L, and the consistency delta = C/L of the blades.
8. The centrifugal compressor diffuser of claim 3, wherein:
the number of the blades (2) is 13, and the total pressure of the outlet/total pressure of the inlet of the diffuser is =0.985 +/-0.02.
9. A centrifugal compressor, characterized by: comprising a centrifugal compressor diffuser according to any one of claims 1 to 8.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116241508A (en) * | 2023-05-12 | 2023-06-09 | 潍柴动力股份有限公司 | Air outlet pipe of air compressor, air compressor and engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116241508A (en) * | 2023-05-12 | 2023-06-09 | 潍柴动力股份有限公司 | Air outlet pipe of air compressor, air compressor and engine |
| CN116241508B (en) * | 2023-05-12 | 2023-09-15 | 潍柴动力股份有限公司 | Air outlet pipe of air compressor, air compressor and engine |
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