CN117345692A - Porous laryngeal diffuser structure of centrifugal compressor - Google Patents
Porous laryngeal diffuser structure of centrifugal compressor Download PDFInfo
- Publication number
- CN117345692A CN117345692A CN202311500076.6A CN202311500076A CN117345692A CN 117345692 A CN117345692 A CN 117345692A CN 202311500076 A CN202311500076 A CN 202311500076A CN 117345692 A CN117345692 A CN 117345692A
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- Prior art keywords
- diffuser
- compressor
- blades
- porous
- channel
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- Pending
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- 238000000926 separation method Methods 0.000 claims abstract description 19
- 239000000306 component Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a porous throat diffuser structure of a centrifugal compressor, which can ensure the performance of the compressor, effectively inhibit flow separation and asymmetry in a channel, improve the stall margin of the compressor and widen the stable operation range of the compressor. The utility model provides a centrifugal compressor porous throat diffuser structure, includes the diffuser, the runner side of diffuser is equipped with a plurality of blades, forms the passageway that supplies the air current to pass through between the adjacent blade, the back side of diffuser is equipped with annular back through groove, and each passageway of diffuser is equipped with the fluting respectively, the fluting makes each passageway all communicate with back through groove; when the compressor operates, pressure difference exists in the pressure in each passage of the diffuser, air flows from a high-pressure position to a low-pressure position through the back through groove, flow separation in the low-pressure passage is improved, and then the air flows into the volute through the passage.
Description
Technical Field
The invention relates to the technical field of turbochargers, in particular to a porous throat diffuser structure of a centrifugal compressor.
Background
The main function of the air compressor in the turbocharger is to compress air, and the air enters the cylinder through the air inlet pipe of the engine to participate in combustion after reaching a certain density so as to increase the power density of the engine. Centrifugal compressors are widely used in turbochargers with the advantages of high performance, wide flow range, compact structure, and the like. In order to meet the requirements of diesel engines, the pressure ratio of a centrifugal compressor is higher and higher, the flow complexity in the high-pressure ratio compressor is increased along with the increase of the pressure ratio, and a diffuser is used as a core component of the high-pressure ratio compressor to directly influence the overall performance of the compressor, and particularly, when the centrifugal compressor is operated to a medium-high rotating speed, a component limiting the stability of the centrifugal compressor is a diffuser component.
The flow separation near the suction surface angle area of the diffuser blades affects the stable operation of the compressor and has potential connection with the rotating stall of the compressor. The tip-type early-stage stall mode can be detected before the surge of the centrifugal compressor, and is mainly caused by throat blockage caused by forward extension of large-scale angle vortex of the suction surface under the working condition of small flow, so that the separation of the blade tip at the front edge of the blade is induced. While the separation zone may cause greater viscosity losses and blending losses. Meanwhile, the asymmetry of the volute of the centrifugal compressor can cause unstable flow in the air compressing impeller and the diffuser, so that the stable operation range of the compressor is narrowed. In order to effectively inhibit flow separation in a diffuser channel and flow loss caused by asymmetry of a volute, and improve stall margin and stable working range of a centrifugal compressor, the invention designs a porous throat diffuser structure for the centrifugal compressor with high pressure ratio.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a porous laryngeal diffuser structure of a centrifugal compressor, which can ensure the performance of the compressor, improve the stall margin of the compressor and widen the stable operation range of the compressor.
The purpose of the invention is realized in the following way:
the utility model provides a centrifugal compressor porous throat diffuser structure, includes the diffuser, the runner side of diffuser is equipped with a plurality of blades, forms the passageway that supplies the air current to pass through between the adjacent blade, the back side of diffuser is equipped with annular back through groove, and each passageway of diffuser is equipped with the fluting respectively, the fluting makes each passageway all communicate with back through groove;
when the compressor operates, pressure difference exists in the pressure in each passage of the diffuser, air flows from a high-pressure position to a low-pressure position through the back through groove, flow separation in the low-pressure passage is improved, and then the air flows into the volute through the passage.
Preferably, the blades of the diffuser are distributed asymmetrically, and the boundary line of the asymmetrical distribution passes through the center of the diffuser and the volute tongue position;
when the compressor operates in a low-flow working condition, flow separation exists in a diffuser channel adjacent to the volute tongue, so that the operation stability of the compressor is affected, the compressor is stalled, at the moment, the flow separation in the channel can be improved by each slotting structure, the flow in the diffuser channel is more uniform, a low-speed flow mass disappears, and the surge margin is increased while the performance of the compressor is improved.
Preferably, the diffuser has 17 diffuser blades, the 17 diffuser blades are divided into two groups along the boundary line of asymmetric distribution, one group of the diffuser blades is 8, the other group of the diffuser blades is 9, the angle difference between adjacent blades in the range of 180 degrees is 22.5 degrees, and the angle difference between adjacent blades in the range of 180 degrees is 20 degrees in the group of the diffuser blades of 9 pieces.
Preferably, the slot is in the shape of a bar, the slot of the bar being perpendicular to the channel.
Preferably, the length of the slot is 60% -90% of the width of the channel, and the width of the slot is 2% -8% of the width of the channel.
Preferably, both ends of the slot are semicircular.
Preferably, when the compressor operates in a low-flow condition, flow separation exists in a diffuser channel adjacent to the volute tongue, so that the operation stability of the compressor is affected, and the compressor stalls, and at the moment, the flow separation in the channel can be improved by each slotting structure, so that the flow in the diffuser channel is more uniform, a low-speed flow mass disappears, the performance of the compressor is improved, and the surge margin is increased.
By adopting the technical scheme, the invention can ensure the performance of the air compressor, effectively inhibit flow separation and asymmetry in the channel, improve the stall margin of the air compressor and widen the stable operation range of the air compressor.
Drawings
FIG. 1 is a top view of a diffuser flow path side. In the figure, 1 is a diffuser center line, 2 and 3 are diffuser blades, and 4 is a porous throat slot;
fig. 2 is a top view of the back side of the diffuser. In the figure, 4 is a multi-hole throat slot, and 5 is a diffuser back through slot;
FIG. 3 is a schematic cross-sectional view of a diffuser;
FIG. 4 is a porous throat diffuser flow mechanism with the inside arrows indicating the flow of air in the diffuser back through slot and the outside arrows indicating the flow of air in the volute;
FIG. 5 is a graph of the effect of a porous throat diffuser to improve flow fields;
fig. 6 is a diffuser and volute assembly position diagram.
Detailed Description
The multi-hole throat diffuser structure widens the stable operation range of the compressor and mainly depends on the pressure difference between different throats to flow in a back side channel of the diffuser so as to reduce the flow separation in other channels.
The diffuser blades are distributed asymmetrically, and are divided into 8 and 9 groups of diffuser blades, wherein a center line 1 of the figure is taken as a dividing line, 8 blades on the left side are uniformly distributed within a 180-degree range, the angle difference between the two blades is 22.5 degrees, 9 blades on the right side are uniformly distributed within the 180-degree range, and the angle difference between the two blades is 20 degrees. The asymmetric position is positioned at the position of the volute tongue, which is shown by an arrow in fig. 6, so that the stall margin of the compressor and the whole-stage efficiency of the compressor can be improved.
The grooving position of the porous throat is positioned at the throat between two blades of the diffuser and is used for communicating the back side through groove of the diffuser. The parameters of the porous throat are two semicircles, the middle rectangular structure, the width of the diffuser throat (channel) is D, the semicircular diameters of the two ends are 0.05D, the length of the middle rectangle is 0.7D, the slotting width is 0.1D, and the asymmetric two sides are perforated according to the parameters.
The depth of the through groove on the back side of the diffuser needs to ensure that the volume of the diffuser is larger than that of the grooves of the porous throat, so that air flow can smoothly flow in the through groove. When the compressor is operated, the pressure in each passage of the diffuser is different, and the air flow can flow from the position with high pressure to the position with low pressure, as shown by the inner arrow in fig. 4, the flow separation in the low pressure passage is improved, and then the air flow enters the volute and flows in the volute along with the main flow.
When the compressor operates in a low-flow working condition, obvious flow separation exists in a diffuser channel close to the volute tongue, so that the operation stability of the compressor is affected, and the compressor stalls. At this time, the porous throat structure of the diffuser can obviously improve the flow separation in the channel, especially the flow instability at the volute tongue position, as shown in fig. 5, the flow in the diffuser channel with the porous throat structure at the volute tongue position is more uniform, the low-speed flow mass disappears, and the surge margin is increased while the performance of the compressor is improved.
Finally, it is noted that the above-mentioned preferred embodiments are only intended to illustrate rather than limit the invention, and that, although the invention has been described in detail by means of the above-mentioned preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the scope of the invention as defined by the appended claims.
Claims (6)
1. The utility model provides a porous laryngeal diffuser structure of centrifugal compressor, includes the diffuser, the runner side of diffuser is equipped with a plurality of blades, forms the passageway that supplies the air current to pass through between the adjacent blade, its characterized in that: the back side of the diffuser is provided with an annular back through groove, each channel of the diffuser is respectively provided with a slot, and each channel is communicated with the back through groove through the slots;
when the compressor operates, pressure difference exists in the pressure in each passage of the diffuser, air flows from a high-pressure position to a low-pressure position through the back through groove, flow separation in the low-pressure passage is improved, and then the air flows into the volute through the passage.
2. The centrifugal compressor porous throat diffuser structure according to claim 1, wherein: the blades of the diffuser are distributed asymmetrically, and the boundary line of the asymmetrical distribution passes through the center of the diffuser and the volute tongue position;
when the compressor operates in a low-flow working condition, flow separation exists in a diffuser channel adjacent to the volute tongue, so that the operation stability of the compressor is affected, the compressor is stalled, at the moment, the flow separation in the channel can be improved by each slotting structure, the flow in the diffuser channel is more uniform, a low-speed flow mass disappears, and the surge margin is increased while the performance of the compressor is improved.
3. The centrifugal compressor porous throat diffuser structure according to claim 1, wherein: the diffuser has 17 diffuser blades, the 17 diffuser blades are divided into two groups along the asymmetric distribution boundary line, one group of diffuser blades is 8, the other group of diffuser blades is 9, the angle difference between adjacent blades in the range of 180 degrees is 22.5 degrees, and the angle difference between adjacent blades in the range of 180 degrees is 20 degrees in the group of 9 diffuser blades.
4. The centrifugal compressor porous throat diffuser structure according to claim 1, wherein: the slot is strip-shaped, and the strip-shaped slot is perpendicular to the channel.
5. The centrifugal compressor porous throat diffuser structure according to claim 4, wherein: the length of the slot is 60% -90% of the width of the channel, and the width of the slot is 2% -8% of the width of the channel.
6. The centrifugal compressor porous throat diffuser structure according to claim 4, wherein: the two ends of the slot are semicircular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311500076.6A CN117345692A (en) | 2023-11-13 | 2023-11-13 | Porous laryngeal diffuser structure of centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311500076.6A CN117345692A (en) | 2023-11-13 | 2023-11-13 | Porous laryngeal diffuser structure of centrifugal compressor |
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| Publication Number | Publication Date |
|---|---|
| CN117345692A true CN117345692A (en) | 2024-01-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311500076.6A Pending CN117345692A (en) | 2023-11-13 | 2023-11-13 | Porous laryngeal diffuser structure of centrifugal compressor |
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|---|---|
| CN (1) | CN117345692A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117725704A (en) * | 2024-02-07 | 2024-03-19 | 浙江飞旋科技有限公司 | Design method of vaned diffuser and vaned diffuser |
-
2023
- 2023-11-13 CN CN202311500076.6A patent/CN117345692A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117725704A (en) * | 2024-02-07 | 2024-03-19 | 浙江飞旋科技有限公司 | Design method of vaned diffuser and vaned diffuser |
| CN117725704B (en) * | 2024-02-07 | 2024-05-14 | 浙江飞旋科技有限公司 | Design method of vaned diffuser and vaned diffuser |
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