CN114321015B - Stabilized vane for stabilizing a vaned diffuser and vaned diffuser - Google Patents
Stabilized vane for stabilizing a vaned diffuser and vaned diffuser Download PDFInfo
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- CN114321015B CN114321015B CN202111663964.0A CN202111663964A CN114321015B CN 114321015 B CN114321015 B CN 114321015B CN 202111663964 A CN202111663964 A CN 202111663964A CN 114321015 B CN114321015 B CN 114321015B
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- vaned diffuser
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- 230000000087 stabilizing effect Effects 0.000 title claims description 10
- 238000000926 separation method Methods 0.000 claims abstract description 19
- 238000009792 diffusion process Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000002474 experimental method Methods 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
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Abstract
The utility model relates to a stable expansion blade for a vaned diffuser and the vaned diffuser, wherein a plurality of stable expansion blades are uniformly distributed on the vaned diffuser along the circumference, and the vane back of each stable expansion blade is provided with a serrated groove structure for reorganizing airflow to inhibit or weaken airflow separation. Compared with the prior art, the utility model 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 utility model relates to the technical field of vaned diffusers, in particular to a stable expansion blade for stable expansion of a vaned diffuser and the vaned diffuser.
Background
For centrifugal compressors, it is important to match the impeller with a suitable diffuser, which is 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, the most widely used diffusers mainly include vaneless diffusers and vaned diffusers. Compared with a vaneless diffuser, the vaneless diffuser has simple structure and wider working range, but has smaller diffusion degree and larger windward area due to smaller change of the airflow angle in the vaneless diffuser, and has longer flow path, thereby causing larger friction loss. Compared with a vaneless diffuser, the vaneless diffuser has the advantages that on one hand, airflow is decelerated and pressurized through the increase of the radius, meanwhile, the airflow angle can be changed through the blades, the flow area is increased, the diffusion degree is improved, the flow path of the airflow is reduced, and therefore friction loss is reduced, and efficiency is improved. Therefore, a vaned diffuser is often used in high performance centrifugal compressors, such as that disclosed in chinese patent application CN213331681U (titled: a vaned diffuser suitable for use in passenger car turbochargers). The existing vaned diffusers mainly comprise airfoil-shaped vaned diffusers, wedge-shaped vaned diffusers, double-arc vaned diffusers and the like. However, when the flow rate is reduced, the attack angle of the inlet of the vaned diffuser is increased, so that a certain impact loss is caused, and the flow separation in the flow passage is easily caused, so that a more serious instability phenomenon is caused.
FIG. 1 illustrates the flow of air through a vaned diffuser. Figure 1 shows that significant separation flow occurs at the blade back and vortices are formed. The dark portions at the blade backs in the figures represent the separation situation, and it can be seen that the airflow separation is more severe at the blade backs. In conclusion, the airflow generates obvious flow separation at the blade back of the compressor blade, and the normal operation of the compressor is affected. For centrifugal compressors, there is typically a significant separation vortex in this region during low flow conditions.
Disclosure of Invention
The utility model aims to overcome the defects of the prior art and provide a stable expansion blade for expanding and stabilizing a vaned diffuser and the vaned diffuser so as to stabilize the flow at the vane back of a compressor vane and inhibit or weaken the separation of air flow at the vane back.
The aim of the utility model can be achieved by the following technical scheme:
the utility model provides a stability expansion blade for a vaned diffuser, wherein a plurality of stability expansion blades are uniformly distributed on the vaned diffuser along the circumference, and the vane back of each stability expansion blade is provided with a serrated groove structure for reorganizing airflow to inhibit or weaken airflow separation.
Preferably, the distance d2 between the serrated groove structure and the airflow inflow end of the blade back is 3% -5% of the length of the blade back.
Preferably, the serrated 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 air flow.
Preferably, the included angle α between the first inclined plane and the blade back is an obtuse angle.
Preferably, the included angle alpha between the first inclined plane and the blade back is 150-160 degrees.
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 said grooves are uniformly distributed along the longitudinal direction of said blade back.
A vaned diffuser is provided with the stabilizing vane.
Compared with the prior art, the utility model has the following advantages:
(1) According to the utility model, the zigzag groove structure is arranged at the blade back of the blade, so that the flow of the boundary layer area on the surface of the blade back is reorganized, and the large-scale separation area in the area is changed into a series of fine separation areas, so that the flow in the whole flow field is more uniform, and the occurrence of air flow separation is inhibited or weakened.
(2) According to the utility model, the opening direction of the grooves is perpendicular to the inflow direction of the air flow, so that the disturbance on the fluid is maximum, and the fluid can be reorganized to the greatest extent.
(3) The utility model enables the large-scale separation area to be better disassembled by arranging the first inclined surface of each groove to be connected with the second inclined surface of the groove adjacent to one side.
Drawings
FIG. 1 is a schematic view of a prior art blade surface flow provided by the present utility model;
FIG. 2 is a schematic view of a stable expansion blade for a vaned diffuser in accordance with the present embodiment;
FIG. 3 is a schematic view of a circumferentially distributed stabilizing vane of a vaned diffuser;
FIG. 4 is a first partial enlarged schematic view of a stabilized vane for use in a vaned diffuser stabilized in accordance with the present embodiment;
FIG. 5 is a second partial enlarged schematic view of a stabilized vane for use in a vaned diffuser stabilized in accordance with the present embodiment;
reference numerals illustrate: 1. the blade stabilizing device comprises a stabilizing blade 11, a blade back 2, grooves 21, a first inclined plane 22, a second inclined plane 3 and a blade diffuser.
Detailed Description
The utility model will now be described in detail with reference to the drawings and specific examples. The present embodiment is implemented on the premise of the technical scheme of the present utility model, and a detailed implementation manner and a specific operation process are given, but the protection scope of the present utility model is not limited to the following examples.
Referring to fig. 2 to 5, the present embodiment provides a stable expansion blade for a vaned diffuser, in which a plurality of stable expansion blades 1 are uniformly distributed on the vaned diffuser along the circumference, and the vane back 11 of each stable expansion blade 1 is provided with a serrated groove structure.
From the theory of shear flow instability, it is known that a necessary condition for flow instability is the presence of inflection points in the velocity gradient profile. The zigzag groove structure provided in this 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 area becomes a series of fine separation areas, and 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 machine is improved. The scheme of the utility model is suitable for subsonic occasions with the inlet Mach number Ma of the vaned diffuser less than or equal to 0.9.
The distance d2 between the serrated groove structure and the airflow inflow end of the blade back 11 is 3% -5% of the length of the blade back 11, so that the front edge of the blade is prevented from being thinned, and the strength of the blade is reduced. Each zigzag groove structure comprises a plurality of grooves 2 which are sequentially arranged, 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 the groove 2 is perpendicular to the inflow direction of the air flow, the disturbance caused by the air flow is maximum, and the air flow can be reorganized to the greatest extent. The angle α between the first inclined surface 21 and the blade back 11 is an obtuse angle. The first inclined surface 21 of each groove 2 is connected to the second inclined surface 22 of an adjacent groove 2 on one side for better breaking up the large-scale separation zone. The groove depths of all the grooves 2 are equal.
As an alternative embodiment, the angle α between the first inclined surface 21 and the blade back 11 is 150 ° to 160 °, so as to generate a local three-dimensional turbulence near the groove 2, improve the flow performance and reduce the flow resistance.
Example 2
The present embodiment provides a vaned diffuser comprising a vane 1, the back of the vane 1 being provided with a saw tooth groove structure for a vaned diffuser as in any of the embodiments 1.
The foregoing describes in detail preferred embodiments of the present utility model. It should be understood that numerous modifications and variations can be made in accordance with the concepts of the utility model by one of ordinary skill in the art without undue burden. Therefore, all technical solutions which can be obtained by logic analysis, reasoning or limited experiments based on the prior art by the person skilled in the art according to the inventive concept shall be within the scope of protection defined by the claims.
Claims (4)
1. The stable expansion blade for the stable expansion of the vaned diffuser is characterized in that a plurality of stable expansion blades (1) are uniformly distributed on the vaned diffuser (3) along the circumference, and a sawtooth-shaped groove structure for reorganizing airflow to inhibit or weaken airflow separation is arranged on a blade back (11) of each stable expansion blade (1);
the distance d2 between the serrated groove structure and the airflow inflow end of the blade back (11) is 3% -5% of the length of the blade back (11);
the serrated groove structure comprises a plurality of grooves (2) which are sequentially arranged;
the first inclined surface (21) of each groove (2) is connected with the second inclined surface (22) of the groove (2) adjacent to one side;
the opening direction of the groove (2) is perpendicular to the inflow direction of the air flow;
each groove (2) comprises a first inclined surface (21) and a second inclined surface (22) which are arranged at a set angle;
the included angle alpha between the first inclined plane (21) and the blade back (11) is an obtuse angle.
2. A stabilizing vane for a vaned diffuser according to claim 1, characterized in that the angle α between the first bevel (21) and the vane back (11) is of the order of 150 ° to 160 °.
3. A stabilizing vane for a vaned diffuser according to claim 1, characterized in that the groove depth of all grooves (2) is equal.
4. A vaned diffuser, characterized in that the vaned diffuser (3) is provided with a stabilizing vane (1) according to any one of claims 1-3.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114321015A CN114321015A (en) | 2022-04-12 |
| CN114321015B true CN114321015B (en) | 2024-03-19 |
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| CN202111663964.0A Active CN114321015B (en) | 2021-12-31 | 2021-12-31 | Stabilized vane for stabilizing a vaned diffuser and vaned diffuser |
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| 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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| Publication number | Publication date |
|---|---|
| CN114321015A (en) | 2022-04-12 |
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