CN118008888A - Vane diffuser, vane diffuser design method and centrifugal compressor - Google Patents
Vane diffuser, vane diffuser design method and centrifugal compressor Download PDFInfo
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- CN118008888A CN118008888A CN202410108068.5A CN202410108068A CN118008888A CN 118008888 A CN118008888 A CN 118008888A CN 202410108068 A CN202410108068 A CN 202410108068A CN 118008888 A CN118008888 A CN 118008888A
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- 238000000034 method Methods 0.000 title claims abstract description 12
- 238000013461 design Methods 0.000 title abstract description 8
- 230000004323 axial length Effects 0.000 claims abstract description 23
- 230000008859 change Effects 0.000 claims description 43
- 230000003247 decreasing effect Effects 0.000 claims description 15
- 238000013507 mapping Methods 0.000 claims description 3
- 238000000465 moulding Methods 0.000 claims 1
- 238000009792 diffusion process Methods 0.000 description 14
- 230000009467 reduction Effects 0.000 description 8
- 230000009286 beneficial effect Effects 0.000 description 6
- 238000012545 processing Methods 0.000 description 5
- 239000000306 component Substances 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000003801 milling Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
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Classifications
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- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/422—Discharge tongues
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- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4226—Fan casings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a vane diffuser, which comprises a diffuser hub, a diffuser wheel cover and a diffuser vane group, wherein the diffuser wheel cover surrounds the diffuser hub to form a meridian flow passage, the diffuser vane group is arranged in the meridian flow passage and comprises a first vane, a second vane and a third vane, the first vane, the second vane and the third vane are all provided with a plurality of first vanes, the second vane and the third vane which are alternately and uniformly distributed along the circumferential direction of an annular airflow passage, the axial length of the first vane is greater than that of the second vane, the axial length of the second vane is greater than that of the third vane, the first vane comprises a radial vane segment and an axial vane segment, the axial section edge line of the meridian flow passage, which is close to the diffuser wheel cover, is a curve, and the radial vane segment and the axial vane segment are integrally formed. The invention also discloses a design method of the vane type diffuser. The invention also discloses a centrifugal compressor.
Description
Technical Field
The invention relates to the technical field of centrifugal compressors, in particular to a vane diffuser. In addition, the invention also relates to a vane diffuser design method for designing the vane diffuser. In addition, the invention also relates to a centrifugal compressor comprising the vane diffuser.
Background
The diffuser is a core component of the centrifugal compressor and is arranged at a downstream position adjacent to the centrifugal impeller, and has decisive influence on the working efficiency, the blocking flow and other performances of the centrifugal compressor. The diffuser has the main effects of reducing and diffusing high-speed airflow at the outlet of the centrifugal impeller, converting kinetic energy into pressure energy to the greatest extent, providing high-pressure airflow meeting the flow field quality requirement for the rear combustion chamber and other components, generally requiring that the included angle between the airflow direction of the outlet of the diffuser and the meridian plane is not more than 15 degrees in the high-load centrifugal compressor, and the Mach number of the outlet airflow is not more than 0.25 so as to ensure that the high-pressure airflow after reducing and diffusing can meet the flow field quality requirement. The diffuser is mainly divided into a double-row vane diffuser (shown in figure 1) and a single-row vane diffuser (shown in figure 2), wherein radial vanes and axial vanes of the double-row vane diffuser are arranged separately to form a front row of vanes and a rear row of vanes, and the radial vanes and the axial vanes of the single-row vane diffuser are connected into a whole to form a row of vanes. The main components of the two are basically the same, and each component consists of a hub surface, blades and a cover plate.
At present, the high-pressure airflow after the speed reduction and diffusion of the double-row vane diffuser can meet the flow field quality requirement, but the ratio of the diameter of the outlet hub side of the diffuser to the diameter of the inlet of the diffuser is larger than 1.25, the radial size is overlarge, the assembly requirement of the diffuser in the high-load centrifugal compressor is not met, the ratio of the diameter of the outlet hub side of the diffuser and the diameter of the inlet of the diffuser after the single-row vane diffuser is reasonably designed can be not larger than 1.14, but the number of vanes of the single-row vane diffuser is relatively small, so that the requirement of flow field quality such as the airflow angle, mach number and the like of the outlet airflow of the diffuser in the high-load centrifugal compressor is difficult to ensure, and the diffuser can not be applied to the high-load centrifugal compressor.
Disclosure of Invention
The invention provides a vane type diffuser and a design method thereof, which are used for solving the technical problems that the existing diffuser is difficult to meet the assembly requirement of a high-load centrifugal compressor on the diffuser or meet the performance requirement of the high-load centrifugal compressor on the diffuser.
According to one aspect of the present invention, there is provided a vane diffuser comprising a diffuser hub, a diffuser shroud surrounding the diffuser hub to form a meridional flow passage, and a diffuser vane set disposed within the meridional flow passage to form a diffuser passage, the diffuser hub including a disk radial section and a disk axial section, the diffuser shroud including a shroud radial section disposed corresponding to the disk radial section and a shroud axial section disposed corresponding to the disk axial section, the diffuser vane set including first, second and third vanes, the first, second and third vanes each being provided in plurality, the plurality of first, second and third vanes being alternately and uniformly arranged in a circumferential direction of the annular flow passage, the axial length of the first vane being greater than the axial length of the second vane, the axial length of the second vane being greater than the axial length of the third vane, the first vane including a radial vane segment disposed between the disk radial section and the shroud radial section and an axial vane segment disposed between the axial sections of the shroud, the axial flow passage being integrally formed in a curved axial section and a meridional section of the diffuser hub.
As a further improvement of the above technical scheme:
Further, the inlet inflow angle of the tip part on the first blade is larger than the inlet inflow angle of the root part, the inlet inflow angle of the tip part on the second blade is larger than the inlet inflow angle of the root part, and the inlet inflow angle of the tip part on the third blade is smaller than the inlet inflow angle of the root part.
Further, when the incoming flow angle of the inlet of the upper tip part of the first blade is-76-70 degrees, the angle change rule of the blade profile of the upper tip part of the first blade is linearly increased to 0 degrees, and when the incoming flow angle of the inlet of the upper root part of the first blade is-73-67 degrees, the angle change rule of the blade profile of the upper root part of the first blade is slowly increased and then is rapidly increased to 0 degrees; and/or when the incoming flow angle of the inlet of the top part of the second blade is-66-60 degrees, the angle change rule of the blade profile of the top part of the second blade is linearly increased to 0 degrees, and when the incoming flow angle of the inlet of the root part of the second blade is-63-57 degrees, the angle change rule of the blade profile of the root part of the second blade is kept unchanged, and then the angle change rule of the blade profile of the root part of the second blade is rapidly increased to 0 degrees; and/or when the inlet incoming flow angle of the upper tip part of the third blade is-50-44 degrees, the angle change rule of the blade profile of the upper tip part of the third blade is linearly increased to 0 degrees, and when the inlet incoming flow angle of the upper root part of the third blade is-55-49 degrees, the angle change rule of the blade profile of the upper root part of the third blade is kept unchanged, and then the angle change rule of the blade profile of the upper root part of the third blade is rapidly increased to 0 degrees.
Further, the thickness change rule of the first blade is that the first blade is increased rapidly, then increased gradually, then decreased gradually and finally decreased rapidly; and/or the thickness change rule of the second blade is that the thickness of the second blade is firstly increased rapidly, then increased gradually, then decreased gradually and finally decreased rapidly; and/or the thickness change rule of the third blade is that the thickness change rule is firstly increased rapidly, then increased gradually, then decreased gradually and finally decreased rapidly.
Further, the first blade is a straight line blade; and/or the second blade is a straight blade; and/or the third blade is a straight blade.
Further, the radial distance between the leading edge line on the first plurality of blades and the axial centerline of the diffuser hub is the same; and/or the radial distance between the leading edge line on the second plurality of blades and the axial centerline of the diffuser hub is the same; and/or the radial distance between the leading edge line on the third plurality of blades and the axial centerline of the diffuser hub is the same.
Further, the axial position of the trailing edge line on the first blade, the axial position of the trailing edge line on the second blade, and the axial position of the trailing edge line on the third blade are the same.
According to another aspect of the present invention, there is also provided a method for designing a vaned diffuser, the method comprising the steps of: firstly, a meridian flow passage in a wheel cover and a wheel hub of the diffuser is given, the meridian flow passage is determined to be a continuous curved surface, then a virtual modeling plane is obtained according to the meridian flow passage, a plane coordinate system is established, blade shapes of blades in a blade group of the diffuser are generated on the modeling plane according to a given angle change rule and a thickness change rule to obtain blade shape data under the plane coordinate system, then the blade shapes on the modeling plane are converted to a three-dimensional rotation surface formed by the meridian flow passage according to a conformal mapping relation between the modeling plane and the rotation surface, column coordinates are established to obtain blade shape data under the column coordinates, finally the blade shape data under the column coordinates are converted to blade shape data under a Cartesian coordinate system, and a first blade, a second blade and a third blade in the blade group of the diffuser are generated in the meridian flow passage based on the blade shape data under the Cartesian coordinate system, so that the blade diffuser is obtained.
As a further improvement of the above technical scheme:
further, the step of generating the vane profile of the vane in the diffuser vane set on the modeling plane according to the given angle change rule and thickness change rule further comprises the steps of: at the same time, the circumferential stacking angles of the root tip profiles of the first blade, the second blade and the third blade are respectively given to control the radial positions of the leading edge lines and the axial positions of the trailing edge lines of the first blade, the second blade and the third blade.
According to another aspect of the present invention, there is also provided a centrifugal compressor including the vane diffuser described above.
The invention has the following beneficial effects:
the vane diffuser of the invention forms a meridian flow passage through the surrounding of the diffuser wheel cover and the diffuser wheel hub so as to facilitate the airflow passage, and then arranges a diffuser vane group in the meridian flow passage so as to form the diffuser passage, thereby realizing the speed reduction diffusion of airflow, particularly, a plurality of first vanes, second vanes and third vanes are alternately and uniformly arranged along the circumferential direction of the annular airflow passage, the axial length of the first vanes is larger than that of the second vanes, the axial length of the second vanes is larger than that of the third vanes, the increase of the number of vanes is realized under the limited space, the control of multiple dimensions of airflow is realized, the edge line of the axial section of the meridian flow passage, which is close to the diffuser wheel hub, is a curve, the curvature of the meridian flow passage is continuous, the flow direction control of airflow in the diffuser passage at the corner is facilitated, the method reduces the flow separation of the air flow, so that the high-pressure air flow after the speed reduction and the diffusion of the diffuser meets the requirement of the high-load centrifugal compressor on the quality of an outlet flow field of the diffuser, namely, the included angle between the direction of the outlet air flow and a meridian plane is not more than 15 degrees, the Mach number of the outlet air flow is not more than 0.25, and as the first blade with the longest axial length consists of a radial blade segment and an axial blade segment, the first blade, the second blade and the third blade are arranged in the same row in the circumferential direction, so as to ensure that the ratio of the diameter of the outlet hub side of the diffuser to the diameter of the inlet of the diffuser is not more than 1.14, thereby meeting the assembly requirement of the high-load centrifugal compressor on the diffuser, and compared with the prior art, the vane-type diffuser of the scheme can meet the assembly requirement of the high-load centrifugal compressor and the performance requirement of the high-load centrifugal compressor, the air flow speed reduction diffusion under the condition of limited radial assembly space is realized, the application range is wide, the practicability is strong, and the air flow speed reduction diffusion device is suitable for wide popularization and application.
In addition to the objects, features and advantages described above, the present invention has other objects, features and advantages. The present invention will be described in further detail with reference to the drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the application. In the drawings:
FIG. 1 is a schematic view of a portion of a prior art double row vaned diffuser;
FIG. 2 is a schematic view of a portion of a prior art single row vane diffuser;
FIG. 3 is a schematic view of a vane diffuser according to a preferred embodiment of the present invention;
Fig. 4 is a graph showing angular variation patterns of the first, second and third blades in the vane diffuser according to the preferred embodiment of the present invention.
Legend description:
100. a diffuser hub; 200. diffuser wheel cover; 300. a diffuser vane set; 310. a first blade; 320. a second blade; 330. and a third blade.
Detailed Description
Embodiments of the invention are described in detail below with reference to the attached drawing figures, but the invention can be practiced in a number of different ways, as defined and covered below.
FIG. 1 is a schematic view of a portion of a prior art double row vaned diffuser; FIG. 2 is a schematic view of a portion of a prior art single row vane diffuser; FIG. 3 is a schematic view of a vane diffuser according to a preferred embodiment of the present invention; fig. 4 is a graph showing angular variation patterns of the first, second and third blades in the vane diffuser according to the preferred embodiment of the present invention.
As shown in fig. 1 and 2, the vane diffuser of this embodiment includes a diffuser hub 100, a diffuser shroud 200 surrounding the diffuser hub 100 to form a meridional flow channel, and a diffuser vane set 300 disposed in the meridional flow channel to form a diffusion channel, wherein the diffuser hub 100 includes a disk radial section and a disk axial section, the diffuser shroud 200 includes a shroud radial section disposed corresponding to the disk radial section and a shroud axial section disposed corresponding to the disk axial section, the diffuser vane set 300 includes a first vane 310, a second vane 320, and a third vane 330, the first vane 310, the second vane 320, and the third vane 330 are all provided in plurality, the plurality of first vane 310, the second vane 320, and the third vane 330 are alternately and uniformly arranged along a circumferential direction of the meridional flow channel, an axial length of the first vane 310 is greater than an axial length of the second vane 320, an axial length of the second vane 320 is greater than an axial length of the third vane 330, the first vane 310 includes a radial vane segment disposed between the disk radial section and the shroud radial section, and a radial vane segment disposed between the shroud axial section and the shroud axial section, and the axial vane shroud axial section is disposed near a curved axial section of the hub 100, and the axial vane section is a curved axial section is formed near the axial section of the diffuser and the axial section. Specifically, the vane diffuser of the present invention forms a meridional flow path by enclosing the diffuser wheel cover 200 and the diffuser wheel hub 100, so as to facilitate the airflow passage, and then arranges the diffuser vane group 300 in the meridional flow path to form a diffusion passage, so as to realize the deceleration diffusion of the airflow, specifically, the plural first vanes 310, second vanes 320 and third vanes 330 are alternately and uniformly arranged along the circumferential direction of the annular airflow passage, the axial length of the first vanes 310 is greater than the axial length of the second vanes 320, the axial length of the second vanes 320 is greater than the axial length of the third vanes 330, so as to realize the increase of the number of vanes in a limited space, and realize the control of multiple dimensions of the airflow, and the meridional flow path is curved near the axial section edge line of the diffuser wheel hub 100, the meridional flow path is curved near the axial section edge line of the diffuser wheel cover 200, and the curvature of the meridional flow path is continuous, the flow direction control of the airflow in the diffuser passage at the corner is facilitated, so that the flow separation of the airflow is reduced, the high-pressure airflow after the speed reduction and diffusion of the diffuser meets the requirement of the high-load centrifugal compressor on the quality of an outlet flow field of the diffuser, namely, the included angle between the direction of the outlet airflow and a meridian plane is not more than 15 degrees, the Mach number of the outlet airflow is not more than 0.25, and the first blade 310 with the longest axial length consists of a radial blade segment and an axial blade segment and is an integrated blade with the radial direction and the axial direction, the first blade 310, the second blade 320 and the third blade 330 are distributed in the same row in the circumferential direction, so that the ratio of the diameter of the outlet hub side of the diffuser to the diameter of the inlet of the diffuser is not more than 1.14, the assembly requirement of the high-load centrifugal compressor on the diffuser is met, and compared with the prior art, the blade diffuser of the scheme can meet the assembly requirement of the high-load centrifugal compressor, and the performance requirement of the high-load centrifugal compressor can be met, the air flow speed reduction and diffusion under the condition of limited radial assembly space are realized, the application range is wide, the practicability is strong, and the device is suitable for wide popularization and application. Optionally, the first blade 310 is a large blade, the second blade 320 is a middle blade, the third blade 330 is a small blade, the large, medium and small blades are alternately and uniformly arranged along the circumferential direction of the meridian flow passage, the large blade is a radial-axial integrated blade, the middle blade is a radial-axial integrated blade or an axial blade, and the small blade is a radial-axial integrated blade or an axial blade.
In this embodiment, the inlet inflow angle of the tip portion on the first blade 310 is larger than the inlet inflow angle of the root portion, the inlet inflow angle of the tip portion on the second blade 320 is larger than the inlet inflow angle of the root portion, and the inlet inflow angle of the tip portion on the third blade 330 is smaller than the inlet inflow angle of the root portion. Specifically, through the inlet incoming flow angles of the first blade 310 root tip, the second blade 320 root tip and the third blade 330 root tip respectively controlled, so as to adapt to the direction of the incoming flow of the air flow, reduce the flow damage of the air flow, be favorable to improving the performance of the diffuser, and further improve the vibration-inducing margin of the centrifugal compressor after being assembled in the centrifugal compressor.
In this embodiment, when the incoming flow angle of the tip portion on the first blade 310 is-76 to-70 °, the angle change rule of the tip portion blade profile on the first blade 310 is linearly increased to 0 °, and when the incoming flow angle of the root portion on the first blade 310 is-73 to-67 °, the angle change rule of the root portion blade profile on the first blade 310 is slowly increased first and then rapidly increased to 0 °, so that after the incoming flow angle of the root portion on the first blade 310 is determined, the expansion degree of the airflow is controlled by controlling the angle change rule of the root portion blade profile on the first blade 310, and further, the flow field of the turning section from radial direction to axial direction in the diffusion channel is improved, thereby improving the performance of the diffuser. As shown in fig. 4, preferably, the inlet inflow angle of the tip on the first blade 310 is-73 °, the angle change rule of the tip profile on the first blade 310 is linearly increased to 0 °, the inlet inflow angle of the root on the first blade 310 is-70 °, and the angle change rule of the root profile on the first blade 310 is slowly increased and then rapidly increased to 0 °.
In this embodiment, when the incoming flow angle of the tip portion on the second blade 320 is-66 to-60 °, the angle change rule of the tip portion blade profile on the second blade 320 is linearly increased to 0 °, and when the incoming flow angle of the root portion on the second blade 320 is-63 to-57 °, the angle change rule of the root portion blade profile on the second blade 320 is maintained unchanged, and then is rapidly increased to 0 °, so that after the incoming flow angle of the root portion of the second blade 320 is determined, the expansion degree of the airflow is controlled by controlling the angle change rule of the root portion blade profile on the second blade 320, and further, the flow field of the turning section from radial direction to axial direction in the diffusion passage is improved, thereby improving the performance of the diffuser. As shown in fig. 4, preferably, when the incoming flow angle of the tip portion on the second blade 320 is-63 °, the angle change rule of the tip profile on the second blade 320 is linearly increased to 0 °, the incoming flow angle of the root portion on the second blade 320 is-60 °, and the angle change rule of the root profile on the second blade 320 is first maintained unchanged and then rapidly increased to 0 °.
In this embodiment, when the incoming flow angle of the tip portion of the third blade 330 is-50 to-44 °, the angle change rule of the tip portion blade profile of the third blade 330 is linearly increased to 0 °, and when the incoming flow angle of the root portion of the third blade 330 is-55 to-49 °, the angle change rule of the root portion blade profile of the third blade 330 is maintained unchanged, and then is rapidly increased to 0 °, so that after the incoming flow angle of the root portion of the third blade 330 is determined, the expansion degree of the airflow is controlled by controlling the angle change rule of the root portion blade profile of the third blade 330, and further, the flow field of the turning section from radial direction to axial direction in the diffusion passage is improved, thereby improving the performance of the diffuser. As shown in fig. 4, preferably, when the incoming flow angle of the tip portion on the third blade 330 is-47 °, the angle change rule of the tip profile on the third blade 330 is linearly increased to 0 °, the incoming flow angle of the root portion on the third blade 330 is-52 °, and the angle change rule of the root profile on the third blade 330 is first maintained unchanged and then rapidly increased to 0 °.
In this embodiment, the thickness variation rule of the first blade 310 is that the thickness variation rule is first increased rapidly, then increased gradually, then decreased gradually, and finally decreased rapidly, so as to ensure that the aerodynamic performance and the processing difficulty of the first blade 310 are correct through the appropriate thickness variation rule.
In this embodiment, the thickness variation rule of the second blade 320 is that the thickness variation rule is first increased rapidly, then increased gradually, then decreased gradually, and finally decreased rapidly, so as to ensure that the aerodynamic performance and the processing difficulty of the second blade 320 are correct through the appropriate thickness variation rule.
In this embodiment, the thickness variation rule of the third blade 330 is that the thickness of the third blade 330 is increased rapidly, then increased gradually, then decreased gradually, and finally decreased rapidly, so as to ensure that the aerodynamic performance and the processing difficulty of the third blade 330 are proper through the proper thickness variation rule.
In this embodiment, the first blade 310 is a straight blade. In particular, when the first blade 310 is a straight blade, the first blade 310 may be subjected to side milling, which is beneficial to reducing the processing cost. Alternatively, the first blade 310 is formed using a root tip having two overlapping cross-sectional areas.
In this embodiment, the second blade 320 is a straight blade. Specifically, when the second blade 320 is a straight blade, the second blade 320 may be machined by side milling, which is beneficial to reducing machining cost. Alternatively, the second blade 320 is formed by overlapping two cross-sectional areas of the root tip.
In this embodiment, the third blade 330 is a straight blade. In particular, when the third blade 330 is a straight blade, the third blade 330 may be subjected to side milling, which is beneficial to reducing the processing cost. Optionally, the third blade 330 is formed by overlapping two cross-sectional areas of the root tip.
In this embodiment, the radial distance between the leading edge line of the first blades 310 and the axial center line of the diffuser hub 100 is the same, so as to ensure that the distance between the inlet of the first blades 310 and the outlet of the upstream free center blade are equal, which is beneficial for the air flow entering the diffuser passage.
In this embodiment, the radial distance between the leading edge line of the plurality of second blades 320 and the axial center line of the diffuser hub 100 is the same, so as to ensure that the distances between the inlets of the plurality of second blades 320 and the outlets of the upstream free center blades are equal, which is beneficial for the airflow entering the diffuser passage.
In this embodiment, the radial distance between the leading edge line on the third blades 330 and the axial centerline of the diffuser hub 100 is the same to ensure that the inlet on the second blades 320 and the outlet on the upstream free center blade are equidistant to facilitate the flow of air into the diffuser passage.
In this embodiment, the axial position of the trailing edge line on the first blade 310, the axial position of the trailing edge line on the second blade 320, and the axial position of the trailing edge line on the third blade 330 are the same, so as to ensure that the outlet airflow of the diffuser is more uniform, and further improve the performance of the diffuser.
The vane diffuser design method of the embodiment designs the vane diffuser, and specifically includes the following steps: the method comprises the steps of firstly giving a meridian flow channel in a diffuser wheel cover 200 and a diffuser hub 100, determining that the meridian flow channel is a continuous curved surface so as to be freely adjustable in aerodynamic design, facilitating control of airflow, obtaining a virtual modeling plane according to the meridian flow channel, establishing a plane coordinate system, generating blade profiles of blades in a diffuser blade set 300 on the modeling plane according to a given angle change rule and a thickness change rule so as to obtain blade profile data under the plane coordinate system, converting the blade profiles on the modeling plane onto a three-dimensional rotating surface formed by the meridian flow channel according to a conformal mapping relation between the modeling plane and the rotating surface, establishing cylindrical coordinates so as to obtain blade profile data under the cylindrical coordinates, and finally converting the blade profile data under the cylindrical coordinates into blade profile data under a Cartesian coordinate system so as to generate a first blade 310, a second blade 320 and a third blade 330 in the diffuser blade set 300 in the meridian flow channel based on the blade profile data under the Cartesian coordinate system, so as to obtain the diffuser.
In this embodiment, the step of generating the vane profile of the vane in the diffuser vane set 300 on the modeling plane according to the given angle change rule and thickness change rule further includes the steps of: meanwhile, the circumferential stacking angles of the tip blade profiles of the first blade 310, the second blade 320 and the third blade 330 are respectively set so as to control the radial positions of the leading edge lines and the axial positions of the trailing edge lines of the first blade 310, the second blade 320 and the third blade 330, further ensure that the distances between the inlets of the first blades 310 and the centrifugal impeller outlet are equal, the distances between the inlets of the second blades 320 and the centrifugal impeller outlet are equal, and the distances between the inlets of the third blades 330 and the centrifugal impeller outlet are equal, and simultaneously ensure that the axial positions of the trailing edge lines on the first blades 310, the axial positions of the trailing edge lines on the second blades 320 and the axial positions of the trailing edge lines on the third blades 330 are the same.
In this embodiment, the front ends of the second blades 320 are disposed downstream of the throat line between two adjacent first blades 310. It should be appreciated that the placement and length of the second vane 320 is associated with the first vane 310, the throat being the location where the expanded gas flow capacity is minimal, the second vane 320 increases the control restriction of the diffuser to the gas flow while not affecting the flow capacity of the diffuser, and reduces the flow separation of the gas flow in the diffuser at high loads and large diffusers.
In this embodiment, the front end of the third blade 330 is disposed at the starting point of the axial segment of the radial flow channel that is located at the rear of the radial rotation axis. It should be appreciated that the location and length of the third vane 330 are easily separated from the flow from the starting point of the axial segment due to the radial axis of the airflow in the meridian passage being directed rearward by centrifugal force, the flow therein is improved by the third vane 330, and the addition of the third vane 330 also increases the actual angle of the airflow, which is advantageous for the outlet airflow angle to be satisfactory.
The centrifugal compressor of the embodiment comprises the vane diffuser. Specifically, the vane type diffuser is adopted in the centrifugal compressor, so that the speed reduction diffusion of high-speed airflow can be realized under the condition of limited radial assembly space, the requirement of the centrifugal compressor on the quality of the diffuser outlet flow field can be met, and the vane type diffuser has strong practicability and is suitable for wide popularization and application.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A vane diffuser comprising a diffuser hub (100), a diffuser shroud (200) surrounding the diffuser hub (100) to form a meridional flow path, and a diffuser vane set (300) disposed in the meridional flow path for forming a diffuser passage, the diffuser hub (100) comprising a disk radial section and a disk axial section, the diffuser shroud (200) comprising a shroud radial section disposed corresponding to the disk radial section and a shroud axial section disposed corresponding to the disk axial section, characterized in that the diffuser vane set (300) comprises a first vane (310), a second vane (320) and a third vane (330), the first vane (310), the second vane (320) and the third vane (330) are all provided in plurality, the plurality of first vane (310), the second vane (320) and the third vane (330) are alternately and uniformly arranged along the circumferential direction of the annular flow path, the axial length of the first vane (310) is greater than the axial length of the second vane (320), the axial length of the second vane (320) is greater than the axial length of the third vane (330), the axial length of the axial section of the third vane (330) disposed corresponding to the disk axial section, the axial section is disposed between the radial sections of the diffuser shroud axial section and the radial section of the diffuser hub (100 and the axial section, the radial section is disposed near the axial section of the diffuser shroud axial section and the axial section of the axial section, the radial blade section and the axial blade section are integrally formed.
2. The vaned diffuser of claim 1, wherein an inlet angle of incidence of a tip on the first vane (310) is greater than an inlet angle of incidence of a root, an inlet angle of incidence of a tip on the second vane (320) is greater than an inlet angle of incidence of a root, and an inlet angle of incidence of a tip on the third vane (330) is less than an inlet angle of incidence of a root.
3. The vaned diffuser of claim 2, wherein when the incoming flow angle of the tip of the first vane (310) is-76-70 °, the angular variation of the tip profile of the first vane (310) increases linearly to 0 °, and when the incoming flow angle of the root of the first vane (310) is-73-67 °, the angular variation of the root profile of the first vane (310) increases slowly and then increases rapidly to 0 °; and/or
When the incoming flow angle of the inlet of the upper tip part of the second blade (320) is-66-60 degrees, the angle change rule of the blade profile of the upper tip part of the second blade (320) is linearly increased to 0 degrees, and when the incoming flow angle of the inlet of the root part of the second blade (320) is-63-57 degrees, the angle change rule of the blade profile of the root part of the second blade (320) is kept unchanged, and then is rapidly increased to 0 degrees; and/or
When the inlet inflow angle of the upper tip part of the third blade (330) is-50-44 degrees, the angle change rule of the upper tip part blade profile of the third blade (330) is linearly increased to 0 degrees, and when the inlet inflow angle of the root part of the third blade (330) is-55-49 degrees, the angle change rule of the root part blade profile of the third blade (330) is kept unchanged, and then is rapidly increased to 0 degrees.
4. A vaned diffuser according to any one of claims 1-3, wherein the first vane (310) has a thickness that varies with a rapid increase, a gradual decrease, and a rapid decrease; and/or
The thickness change rule of the second blade (320) is that the thickness change rule is firstly increased rapidly, then increased gradually, then decreased gradually and finally decreased rapidly; and/or
The thickness variation law of the third blade (330) is that the thickness is firstly increased rapidly, then gradually increased, then gradually decreased, and finally reduced rapidly.
5. The vaned diffuser of any one of claims 1-3, wherein the first vane (310) is a straight vane; and/or
The second blade (320) is a straight blade; and/or
The third blade (330) is a straight blade.
6. The vaned diffuser of any one of claims 1-3, wherein a radial distance between a leading edge line on the first plurality of vanes (310) and an axial centerline of the diffuser hub (100) is the same; and/or
The radial distance between the leading edge line on the plurality of second blades (320) and the axial centerline of the diffuser hub (100) is the same; and/or
The radial distance between the leading edge line on the plurality of third blades (330) and the axial centerline of the diffuser hub (100) is the same.
7. The vaned diffuser of any one of claims 1-3, wherein an axial position of a trailing edge line on the first vane (310), an axial position of a trailing edge line on the second vane (320), and an axial position of a trailing edge line on the third vane (330) are the same.
8. A method of designing a vaned diffuser, comprising the steps of:
firstly, a meridian runner in a diffuser wheel cover (200) and a diffuser wheel hub (100) is given, the meridian runner is determined to be a continuous curved surface, then a virtual modeling plane is obtained according to the meridian runner, a plane coordinate system is established, the blade shapes of blades in a diffuser blade group (300) are generated on the modeling plane according to a given angle change rule and a thickness change rule so as to obtain blade shape data under the plane coordinate system, then the blade shapes on the modeling plane are converted to a three-dimensional rotating surface formed by the meridian runner according to a conformal mapping relation between the modeling plane and the rotating surface, column coordinate is established so as to obtain blade shape data under the column coordinate system, finally the blade shape data under the column coordinate system is converted to blade shape data under a Cartesian coordinate system so as to generate a first blade (310), a second blade (320) and a third blade (330) in the diffuser blade group (300) in the meridian runner based on the blade shape data under the Cartesian coordinate system, and thus the blade diffuser is obtained.
9. The method of designing a vaned diffuser according to claim 8, wherein the step of generating a profile of a vane in the diffuser vane pack (300) on the molding plane according to a given angular variation law and thickness variation law further comprises the steps of:
At the same time, the circumferential stacking angles of the root tip blade profiles of the first blade (310), the second blade (320) and the third blade (330) are respectively given to control the radial positions of the leading edge lines and the axial positions of the trailing edge lines of the first blade (310), the second blade (320) and the third blade (330).
10. A centrifugal compressor comprising a vaned diffuser according to any one of claims 1-7.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN119203427A (en) * | 2024-11-22 | 2024-12-27 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | A design method for integrated meridian flow passage of axial exhaust oblique flow compressor |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN119203427A (en) * | 2024-11-22 | 2024-12-27 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | A design method for integrated meridian flow passage of axial exhaust oblique flow compressor |
| CN119203427B (en) * | 2024-11-22 | 2025-01-24 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Design method of axial exhaust inclined flow compressor integrated meridian flow passage |
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