CN114321015A - Stability expansion blade for stability expansion of vane diffuser and vane diffuser - Google Patents
Stability expansion blade for stability expansion of vane diffuser and vane diffuser Download PDFInfo
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- CN114321015A CN114321015A CN202111663964.0A CN202111663964A CN114321015A CN 114321015 A CN114321015 A CN 114321015A CN 202111663964 A CN202111663964 A CN 202111663964A CN 114321015 A CN114321015 A CN 114321015A
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- 238000000926 separation method Methods 0.000 claims abstract description 18
- 230000000087 stabilizing effect Effects 0.000 claims description 10
- 230000003019 stabilising effect Effects 0.000 claims 3
- 239000012530 fluid Substances 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 230000036961 partial effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000002829 reductive effect Effects 0.000 description 1
- 230000003313 weakening effect Effects 0.000 description 1
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Abstract
The invention relates to a stability expansion blade for stability expansion of a blade diffuser and the blade diffuser. Compared with the prior art, the invention can stabilize the flow at the blade back of the compressor blade and inhibit or weaken the air flow separation at the blade back.
Description
Technical Field
The invention relates to the technical field of a bladed diffuser, in particular to a stability-expanding blade for expanding stability of the bladed diffuser and the bladed diffuser.
Background
For the centrifugal compressor, it is crucial to match a proper diffuser for the impeller, and the diffuser is used as an important component of the centrifugal compressor, and the stability of the flow field of the diffuser affects the overall operation range of the compressor. Currently, widely used diffusers mainly include vaneless diffusers and vaned diffusers. Compared with a vaned diffuser, the vaneless diffuser is simple in structure and wide in working range, but the change of the airflow angle in the vaneless diffuser is small, so that the diffuser is small in degree, large in windward area and long in flow, and large friction loss can be caused. Compare no leaf diffuser, the radial increase makes the air current speed reduction pressure boost on the one hand of having the leaf diffuser, also can change the air flow angle through the blade simultaneously, increases the through flow area, improves the diffusion degree to reduce the flow of air current, thereby reduce friction loss, raise the efficiency. Therefore, a vaned diffuser is commonly used in high performance centrifugal compressors, such as that disclosed in chinese utility model patent CN213331681U (entitled: a vaned diffuser suitable for passenger car turbochargers). The existing vaned diffuser mostly comprises an airfoil vaned diffuser, a wedge vaned diffuser, a double-arc vaned diffuser and the like. However, when the flow rate is reduced, the attack angle of the inlet of the vaned diffuser is increased, so that certain impact loss is caused, flow separation in a flow channel is easily caused, and a more serious instability phenomenon is caused.
Fig. 1 shows the state of the gas flow through the vaned diffuser. Fig. 1 shows that a sharp separation flow is generated at the blade back of the blade and a vortex is formed. The dark parts at the blade back in the figure represent the separation, where it can be seen that the separation of the gas flow is more severe. In conclusion, the air flow generates obvious flow separation at the blade back of the compressor blade, and the normal work of the compressor is influenced. For centrifugal compressors, there is typically significant separation vortex in this region under low flow conditions.
Disclosure of Invention
The present invention is directed to overcome the above-mentioned drawbacks of the prior art and to provide a stabilized vane and a vane diffuser for stabilizing the flow at the vane back of the compressor vane to suppress or reduce the flow separation at the vane back.
The purpose of the invention can be realized by the following technical scheme:
the invention provides a stability expansion blade for expanding stability of a bladed diffuser, wherein a plurality of stability expansion blades are uniformly distributed on the bladed diffuser along the circumference, and a saw-toothed groove structure used for reorganizing airflow to inhibit or weaken airflow separation is arranged on the blade back of each stability expansion blade.
Preferably, the distance d2 between the sawtooth-shaped groove structure and the airflow inflow end of the blade back is 3% -5% of the length of the blade back.
Preferably, the saw-toothed groove structure comprises a plurality of grooves arranged in sequence.
Preferably, each of the grooves includes a first slope and a second slope disposed at a set angle.
Preferably, the opening direction of the groove is perpendicular to the inflow direction of the airflow.
Preferably, an included angle α between the first inclined surface and the blade back is an obtuse angle.
Preferably, the included angle α between the first inclined surface and the blade back is 150 ° to 160 °.
Preferably, the first inclined surface of each groove is connected with the second inclined surface of the groove adjacent to one side.
Preferably, a plurality of the grooves are evenly distributed along the longitudinal direction of the blade back.
A vaned diffuser is provided with the stable expanding blades.
Compared with the prior art, the invention has the following advantages:
(1) the invention enables the flow in the boundary layer area of the surface of the blade back to be reorganized by arranging the zigzag groove structure at the blade back of the blade, so that the large-scale separation area in the boundary layer area is changed into a series of fine separation areas, thereby enabling the flow in the whole flow field to be more uniform and inhibiting or weakening the occurrence of airflow separation.
(2) According to the invention, the opening direction of the groove is perpendicular to the inflow direction of the airflow, so that the disturbance on the fluid is maximum, and the fluid can be reorganized to the maximum extent.
(3) According to the invention, the first inclined plane of each groove is connected with the second inclined plane of the adjacent groove on one side, so that the large-scale separation area can be better disassembled.
Drawings
FIG. 1 is a schematic representation of a prior art blade surface flow provided by the present invention;
FIG. 2 is a schematic structural diagram of a stabilized blade for stabilizing a diffuser with blades according to the present embodiment;
FIG. 3 is a schematic view of circumferentially distributed stabilizing blades of a vaned diffuser;
FIG. 4 is a first enlarged partial schematic view of a stabilizing blade for a vaned diffuser in accordance with an exemplary embodiment;
FIG. 5 is a second enlarged partial schematic view of a stabilizing blade for a vaned diffuser of the present embodiment;
description of reference numerals: 1. the blade comprises a stabilizing blade 11, a blade back 2, a groove 21, a first inclined surface 22, a second inclined surface 3 and a blade diffuser.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments. The present embodiment is implemented on the premise of the technical solution of the present invention, and a detailed implementation manner and a specific operation process are given, but the scope of the present invention is not limited to the following embodiments.
Referring to fig. 2 to 5, in the embodiment, a plurality of stability expansion blades 1 are uniformly distributed on the bladed diffuser along the circumference, and a blade back 11 of each stability expansion blade 1 is provided with a saw-toothed groove structure.
According to the shear flow unsteady flow theory, the essential condition for flow instability is the presence of an inflection point in the velocity gradient profile. The serrated groove structure arranged in the embodiment can reorganize the flow in the boundary layer area on the surface of the blade back 1, so that the large-scale separation area in the boundary layer area is changed into a series of fine separation areas, the flow in the whole flow field is more uniform, and the occurrence of airflow separation is inhibited or weakened. The stable working margin of the compressor is increased, and the working performance of the vaned diffuser and even the whole compressor is improved. The scheme of the invention is suitable for subsonic occasions with the inlet Mach number Ma of the vane diffuser being less than or equal to 0.9.
The distance d2 between the sawtooth-shaped groove structure and the airflow inflow end of the blade back 11 is 3% -5% of the length of the blade back 11, so as to prevent the leading edge of the blade from thinning and reduce the strength of the blade. Each sawtooth-shaped groove structure comprises a plurality of grooves 2 which are arranged in sequence, each groove 2 comprises a first inclined surface 21 and a second inclined surface 22 which are arranged according to a set angle, the opening direction of each groove 2 is perpendicular to the inflow direction of airflow, the disturbance on the fluid is the largest, and the flow can be reorganized to the largest extent. The angle α between the first inclined surface 21 and the blade back 11 is obtuse. The first inclined surface 21 of each groove 2 is connected to the second inclined surface 22 of the groove 2 adjacent to one side for better unraveling of the large-scale separation zone. The groove depths of all the grooves 2 are equal.
As an alternative embodiment, the included angle α between the first inclined surface 21 and the blade back 11 is 150 ° to 160 ° to generate local three-dimensional turbulence near the groove 2, so as to improve the flow performance and reduce the flow resistance.
Example 2
The embodiment provides a vaned diffuser, which comprises a vane 1, wherein the back of the vane 1 is provided with a sawtooth-shaped groove structure for the vaned diffuser as in any one of embodiments 1.
The foregoing detailed description of the preferred embodiments of the invention has been presented. It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (10)
1. The stability expansion blade for the stability expansion of the blade diffuser is characterized in that a plurality of stability expansion blades (1) are uniformly distributed on the blade diffuser (3) along the circumference, and a saw-toothed groove structure used for reorganizing airflow to inhibit or weaken airflow separation is arranged on a blade back (11) of each stability expansion blade (1).
2. The stabilizing blade for a bladed diffuser according to claim 1, characterized in that the distance d2 between said serrated groove structure and the air flow inlet end of the blade back (11) is between 3% and 5% of the length of the blade back (11).
3. The stabilizing blade for a vaned diffuser according to claim 2, wherein the serrated groove structure comprises a plurality of grooves (2) arranged in series.
4. The diffuser vane as claimed in claim 3, wherein the recess (2) is open in a direction perpendicular to the inflow direction of the air flow.
5. The stabilizing blade for a vaned diffuser according to claim 4, wherein each of the grooves (2) comprises a first inclined surface (21) and a second inclined surface (22) arranged at a predetermined angle.
6. The stabilizing blade for a bladed diffuser according to claim 5, characterized in that the angle α between said first inclined surface (21) and said blade back (11) is obtuse.
7. The diffuser vane as claimed in claim 6, wherein the angle α between the first inclined surface (21) and the vane back (11) is 150 ° to 160 °.
8. A stabilising blade for a vaned diffuser according to claim 3, wherein the first ramp (21) of each groove (2) is connected to the second ramp (22) of the groove (2) adjacent to one side.
9. A stabilising blade for a vaned diffuser according to claim 3, wherein all of the grooves (2) have equal groove depth.
10. A vaned diffuser, characterized in that the vaned diffuser (1) is provided with stabilising vanes (1) according to any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111663964.0A CN114321015B (en) | 2021-12-31 | 2021-12-31 | Stabilized vane for stabilizing a vaned diffuser and vaned diffuser |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111663964.0A CN114321015B (en) | 2021-12-31 | 2021-12-31 | Stabilized vane for stabilizing a vaned diffuser and vaned diffuser |
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| Publication Number | Publication Date |
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| CN114321015A true CN114321015A (en) | 2022-04-12 |
| CN114321015B CN114321015B (en) | 2024-03-19 |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736474A (en) * | 2016-03-31 | 2016-07-06 | 广东美的制冷设备有限公司 | Static blade of axial flow cabinet machine, guide component and axial flow cabinet machine |
| CN106089807A (en) * | 2016-06-28 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of diffuser based on fractal blade |
| KR20180019416A (en) * | 2016-08-16 | 2018-02-26 | 한화파워시스템 주식회사 | Centrifugal compressor |
| CN108730230A (en) * | 2018-04-04 | 2018-11-02 | 大连依勒斯涡轮增压技术有限公司 | A kind of turbocharger and its centrifugal compressor |
| CN108869400A (en) * | 2018-08-24 | 2018-11-23 | 浙江南元泵业有限公司 | Centrifugal pump guide vane |
| CN209444615U (en) * | 2018-12-29 | 2019-09-27 | 捷和电机制品(深圳)有限公司 | A kind of diffuser, blower and dust catcher |
| CN110439865A (en) * | 2019-08-14 | 2019-11-12 | 溧阳市盛杰机械有限公司 | A kind of compressor for cooling cycle system |
| CN211901078U (en) * | 2019-12-03 | 2020-11-10 | 珠海格力电器股份有限公司 | Axial flow guide diffuser and high-speed motor with same |
| CN112814946A (en) * | 2019-11-18 | 2021-05-18 | 珠海格力电器股份有限公司 | Diffuser and motor |
-
2021
- 2021-12-31 CN CN202111663964.0A patent/CN114321015B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105736474A (en) * | 2016-03-31 | 2016-07-06 | 广东美的制冷设备有限公司 | Static blade of axial flow cabinet machine, guide component and axial flow cabinet machine |
| CN106089807A (en) * | 2016-06-28 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of diffuser based on fractal blade |
| KR20180019416A (en) * | 2016-08-16 | 2018-02-26 | 한화파워시스템 주식회사 | Centrifugal compressor |
| CN108730230A (en) * | 2018-04-04 | 2018-11-02 | 大连依勒斯涡轮增压技术有限公司 | A kind of turbocharger and its centrifugal compressor |
| CN108869400A (en) * | 2018-08-24 | 2018-11-23 | 浙江南元泵业有限公司 | Centrifugal pump guide vane |
| CN209444615U (en) * | 2018-12-29 | 2019-09-27 | 捷和电机制品(深圳)有限公司 | A kind of diffuser, blower and dust catcher |
| CN110439865A (en) * | 2019-08-14 | 2019-11-12 | 溧阳市盛杰机械有限公司 | A kind of compressor for cooling cycle system |
| CN112814946A (en) * | 2019-11-18 | 2021-05-18 | 珠海格力电器股份有限公司 | Diffuser and motor |
| CN211901078U (en) * | 2019-12-03 | 2020-11-10 | 珠海格力电器股份有限公司 | Axial flow guide diffuser and high-speed motor with same |
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| CN114321015B (en) | 2024-03-19 |
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