CN112412885B - Adjustable self-circulation air injection stability expansion structure and centrifugal compressor with stability expansion structure - Google Patents
Adjustable self-circulation air injection stability expansion structure and centrifugal compressor with stability expansion structure Download PDFInfo
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- CN112412885B CN112412885B CN202011135772.8A CN202011135772A CN112412885B CN 112412885 B CN112412885 B CN 112412885B CN 202011135772 A CN202011135772 A CN 202011135772A CN 112412885 B CN112412885 B CN 112412885B
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- 238000002347 injection Methods 0.000 title claims abstract description 136
- 239000007924 injection Substances 0.000 title claims abstract description 136
- 230000000903 blocking effect Effects 0.000 claims abstract description 11
- 238000009826 distribution Methods 0.000 claims description 10
- 230000006641 stabilisation Effects 0.000 claims description 5
- 238000011105 stabilization Methods 0.000 claims description 5
- 230000003416 augmentation Effects 0.000 claims 1
- 238000000926 separation method Methods 0.000 abstract description 11
- 230000008859 change Effects 0.000 abstract description 2
- 230000000694 effects Effects 0.000 description 7
- 230000003068 static effect Effects 0.000 description 7
- 239000012530 fluid Substances 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 4
- 238000011160 research Methods 0.000 description 3
- 238000003754 machining Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000002706 hydrostatic effect Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000002401 inhibitory effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
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- 230000008569 process Effects 0.000 description 1
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
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Abstract
The invention discloses an adjustable self-circulation air injection stability expansion structure for a centrifugal compressor blade diffuser, which comprises a self-circulation cavity arranged at the outer side of the rim of the blade diffuser, wherein the self-circulation cavity is communicated with a blade diffuser flow passage through air injection holes H1, H2 and H3; an adjustable shielding component is arranged in the self-circulation cavity; under the blocking working condition, the shielding component is controlled to enable the air injection hole H1 and the air injection hole H2 to be opened and the air injection hole H3 to be blocked; during stall conditions, the modulating shroud is controlled so that the gas injection holes H1 and H3 are open and the gas injection holes H2 are blocked. The invention also provides the centrifugal compressor with the stability expanding structure. The invention can change the flow blockage and flow separation in the flow field of the blade diffuser, improve the flow condition in the diffuser, improve the stable working range of the centrifugal compressor and has simple structure.
Description
Technical Field
The invention relates to the technical field of centrifugal compressors, in particular to an adjustable self-circulation air injection stability expansion structure for a blade diffuser of a centrifugal compressor and the centrifugal compressor with the same.
Background
Diffusers applied to centrifugal compressors are mainly divided into vane diffusers and vaneless diffusers. Fig. 1 shows the internal structure of a centrifugal compressor with a vane diffuser. The centrifugal compressor comprises an impeller, a blade diffuser and a volute (not shown), wherein the outlet of the impeller is connected with the blade diffuser, and blades (the blades on the outer ring in figure 1) are arranged in the blade diffuser. The invention aims at the flow control and stability expansion design of the vane diffuser.
When the centrifugal compressor works, the impeller firstly applies work to the gas, so that the speed, the pressure and the like of the gas are increased; then in the blade diffuser, the gas speed is reduced, the static pressure is increased, and a part of kinetic energy of the gas is converted into pressure energy, so that the pressure is further increased after the gas flows out of the impeller, and the pressure ratio of the whole centrifugal compressor is improved. Generally, the operating flow is far smaller than the design flow, so that the phenomenon of rotating stall in a diffuser is caused, and fluid oscillation is caused; the operating flow is far larger than the design flow, so that the throat part of the diffuser blade is blocked, and the stable operating range of the centrifugal compressor is limited.
The jet application to the flow field is the most important stall active control method and is active control, aiming at changing the flow blockage in the flow field or inhibiting flow separation by the impact effect of the synthetic jet, thereby realizing the effect of delaying the occurrence of stall. However, the active control method requires an additional jet structure, and cannot simultaneously take into account both the directions of clogging and stall. The invention aims to design a self-circulation air injection stability-expanding structure which is simple in structure and can effectively give consideration to both the blocking direction and the stalling direction.
Disclosure of Invention
In view of the above, the invention provides an adjustable self-circulation air injection stability-expanding structure for a centrifugal compressor blade diffuser, which can change flow blockage and flow separation in a flow field of the blade diffuser, improve the flow condition in the diffuser, improve the stable working range of the centrifugal compressor, and has a simple structure.
In order to solve the technical problem, the invention is realized as follows:
an adjustable self-circulating jet stabilization structure for a centrifugal compressor blade diffuser, comprising: the self-circulation cavity is arranged on the outer side of the rim of the blade diffuser and communicated with the flow passage of the blade diffuser through the arranged gas injection holes; the three gas injection holes are in a group and named as H1, H2 and H3 from near to far according to the distance from the axis of the centrifugal compressor; each group of the gas injection holes corresponds to one diffuser blade, and the radial distribution area of the three gas injection holes H1, H2 and H3 in the group is positioned in the radial area occupied by the diffuser blade; the air injection holes H1 are located on the leading edge of the diffuser blade close to the suction surface side, the air injection holes H2 and H3 are located behind the throat position of the blade diffuser, the air injection holes H2 are close to the throat, and the air injection holes H3 are close to the trailing edge of the diffuser blade;
an adjustable shielding component is arranged in the self-circulation cavity; under the blocking working condition, the shielding component is controlled to enable the air injection hole H1 and the air injection hole H2 to be opened and the air injection hole H3 to be blocked; during stall conditions, the modulating shroud is controlled so that the gas injection holes H1 and H3 are open and the gas injection holes H2 are blocked.
Preferably, the radial positions of the gas injection holes H1, H2 and H3 are the same in different groups of gas injection holes.
Preferably, the radial positions of the gas injection holes H1, H2 and H3 are respectively located at 1.02R3、1.01Rt、0.9R4(ii) a Wherein R is3Is the vane diffuser inlet radius, RtIs the vane diffuser throat radius, R4Is the vane diffuser exit radius.
Preferably, the gas injection holes are arranged in the following way: a group of the gas injection holes H1, H2 and H3 are arranged along the same radial direction, or a group of the gas injection holes H1, H2 and H3 are arranged along the same blade flow direction of the blade diffuser.
Preferably, the number of groups of gas injection holes is the same as the number of diffuser blades.
Preferably, the gas injection holes H1 are arranged at an angle of 0-360 DEG/2 corresponding to the circumferential distance of the leading edge of the diffuser bladenIn the range of (a) to (b),nthe number of diffuser blades.
Preferably, the diameter of the gas injection hole ranges from 0.5mm to 1.5 mm; the flow of the gas injection holes is 4% -6% of the total flow of the blade diffuser under the blocking working condition, and is 2% -4% of the total flow of the blade diffuser under the stall working condition.
Preferably, the shielding component is a slidable shielding slider; when the shielding sliding block slides to the first position, the shielding sliding block shields the gas injection hole H3 but does not shield the gas injection holes H2 and H1; when the shielding slide block slides to the second position, the shielding slide block releases the air injection hole H3 to shield the air injection hole H2 but not shield the air injection hole H1.
Preferably, the self-circulation cavity (3) and the vane diffuser share the wall surface of the rim of the vane diffuser.
The invention also provides a centrifugal compressor with the stability expansion structure, and any one of the adjustable self-circulation air injection stability expansion structures is arranged in a blade diffuser of the centrifugal compressor.
Has the advantages that:
(1) the self-circulation cavity is arranged on the outer side of the rim of the blade diffuser, the air injection holes communicated with the self-circulation cavity and the flow channel of the blade diffuser are formed, and the three air injection holes form a group. Therefore, the method does not need an additional jet flow structure, and is simple in structure and easy to implement.
(2) The arrangement of the three air injection hole positions is matched with the shielding relation, so that the stall condition and the blockage condition can be met. Furthermore, a preferred embodiment of the present invention also provides that the radial positions of H1, H2, H3 are at 1.02R, respectively3、1.01Rt、0.9R4The reliability, universality and high efficiency of the stability expanding structure are considered.
(3) The invention provides two gas injection hole layouts, the mode of arranging all the gas injection hole groups along the same radial direction is easier to process, and the gas injection hole layout has universality for the blade diffuser centrifugal compressor with the same number of diffuser blades but different blade wrap angles.
(4) The gas injection holes H1, H2 and H3 in different gas injection hole groups are respectively arranged in the same radial direction to form three circular rings, so that the processing is convenient, the original circumferential distribution rule of a flow field is maintained, and the jet flow applying effect is uniformly controlled.
(5) In a preferred embodiment, the number of the groups of the gas injection holes is the same as that of the diffuser blades, so that the phenomenon of circumferential non-uniformity of the flow field distribution caused by the fact that the gas injection jet flow in the same radial direction acts on different circumferential positions of a flow passage of the blade diffuser is avoided, and circumferential balance of the flow field is damaged.
(6) In a preferred embodiment, the gas injection holes H1 are positioned at an angle of 0 to 360/2 relative to the circumferential distance from the leading edge of the bladenIn the range (2), the low energy region generated by flow separation on the suction surface side of the diffuser blade is effectively impacted, so that the flow separation is restrained and the diffuser is stabilized.
(7) In order to take two working conditions of blockage and stall into account, the diameter of an opening and the total flow of a blade diffuser under different working conditions are designed, so that high-speed jet flow is formed under the stall working condition, and effective flow division is formed under the blockage working condition.
Drawings
FIG. 1 is a schematic view of a centrifugal compressor vane diffuser;
FIG. 2 is a schematic view of a centrifugal compressor with an adjustable self-circulation air injection stability-expanding structure according to the present invention;
FIG. 3 is a schematic structural diagram of an adjustable self-circulation air-injection stability-expanding structure;
FIG. 4(a) is a schematic diagram of the operation of the adjustable self-circulation air injection stability-expanding structure under the condition of blockage according to the present invention;
FIG. 4(b) is a schematic diagram of the adjustable self-circulation jet stabilization structure of the present invention operating under stall condition;
FIG. 5(a) is a schematic view of the radial distribution of gas injection holes;
FIG. 5(b) is a schematic view of the gas injection hole flow direction distribution;
wherein, 1-impeller flow passage, 2-blade diffuser flow passage, 3-self-circulation cavity, 4-shielding part (shielding slide block), H1, H2, H3-gas orifice, R3-vane diffuser inlet radius, RtVane diffuser throat radius, R4-vane diffuser exit radius.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides an adjustable self-circulation air injection stability expansion structure for a blade diffuser of a centrifugal compressor. According to the scheme, a cavity is arranged on the outer side of the rim of the blade diffuser, the jet holes communicating the cavity with the flow channel of the blade diffuser are formed, the three jet holes form a group, local communication is achieved by opening the jet holes at different positions under different working conditions, the flow of the blade diffuser in the flow channel flows into the cavity through one jet hole and then flows back to the blade diffuser through the other jet hole, and therefore the effect of applying jet flow to the flow field is achieved. The self-circulation cavity can realize the self-circulation flow of the air flow, so the self-circulation cavity is called as the self-circulation cavity in the invention. Therefore, the method does not need an additional jet structure, is simple in structure and easy to realize, and can simultaneously consider different working conditions through different shielding relations, and the following detailed analysis is carried out.
Referring to fig. 2, the outlet of the impeller flow passage 1 is connected with the vane diffuser flow passage 2. And a self-circulation cavity 3 is arranged on the outer side of the rim of the blade diffuser flow passage 2, and the self-circulation cavity 3 is communicated with the blade diffuser flow passage through an opened gas orifice. The jet holes are grouped into three groups and are named as H1, H2 and H3 from near to far according to the distance from the axis of the centrifugal compressor. Each group of gas injection holes corresponds to one blade, and the radial distribution area of the three gas injection holes H1, H2 and H3 in one group is positioned in the radial range occupied by the blade. Preferably, the number of the groups of the gas injection holes is the same as that of the diffuser blades, so that the phenomenon of circumferentially uneven distribution of a flow field caused by the fact that the gas injection jet flow in the same radial direction acts on different circumferential positions of a flow passage of the blade diffuser is avoided, circumferential balance of the flow field is damaged, and the highest-capacity applied jet flow meeting the circumferential balance condition is realized. In practice, if the circumferential non-uniformity of the flow field is to be controlled, part of the diffuser blades can be provided with the air injection hole groups.
The air injection holes H1 are located on the leading edge of the diffuser blade close to the suction side, the air injection holes H2 and H3 are located behind the throat position of the blade diffuser, the air injection holes H2 are close to the throat, and the air injection holes H3 are close to the trailing edge of the diffuser blade. In general, for convenience of machining and uniform control of the jet application effect, the positions of all the groups of the gas injection holes are designed to be the same, that is, the radial positions of the gas injection holes H1, H2 and H3 are the same in all the groups of the gas injection holes, and the gas injection holes form three circular rings.
Throat (R) in the vane diffuser flow passagetPosition), when the flow rate of the centrifugal compressor is far more than the designed flow rate, the blockage phenomenon at the throat position can be caused. At this time, the static pressure distribution in the passage of the vane diffuser is reduced and then increased along the flow direction, and a local low static pressure occurs at the throat position. To effectively relieve flow blockage and to act as a flow divider, the gas injection holes H1 at the leading edge of the diffuser vane and the gas injection holes H2 beyond the throat position are operated so that a part of the fluid flowing into the vane diffuser flows out of H1, passes through the self-circulation cavity and then flows into the diffuser from H2. Therefore, the flow pressure of the excessive flow to the throat part can be effectively relieved, the flow splitting work is realized, and the stable working range of the gas compressor under the large-flow working condition is expanded. Under the working condition, the gas injection holes near the trailing edge of the diffuser blade are blocked to prevent the high-pressure fluid at the outlet of the diffuser from flowing back, and the working schematic diagram is shown in fig. 4 (a).
The radial position of the gas injection holes H2 is determined based on the static pressure distribution in the vane diffuser passage. First, to effectively split, H2 must be located after the throat position. Preferably, to prevent the static pressure at the backflow H2 from being less than the static pressure at H1, since the static pressure in the vane diffuser passage increases gradually from the throat. According to research, the hydrostatic pressure is rapidly increased after the throat, so in order to ensure the effectiveness of the flow division, the radial position of the gas injection holes H2 is as close to the throat as possible, and R is recommendedH2=1.01Rt。RtIs the vane diffuser throat radius.
When the flow of the compressor is far smaller than the designed flow, the meridional velocity of the fluid flowing out of the impeller is reduced, the tangential component of the absolute velocity is increased, the attack angle is increased when the fluid flows into the blade diffuser, flow separation is generated, and the diffuser stall is induced. At this time, the air injection holes H1 and H3 located near the leading edge and the trailing edge of the diffuser blade start to work, high-speed fluid in the blade diffuser flows out of H3 and flows in from H1 through the self-circulation cavity, and the formed high-pressure jet flow generates an impact effect on the separation area of the leading edge of the diffuser blade to inhibit flow separation, so that stall is delayed, and the stable working range of small flow of the compressor is expanded, wherein the working schematic diagram is shown in fig. 4 (b). Under the working condition, the larger the pressure difference between the two air injection holes is, the better the pressure difference is, so that the air injection hole H2 is blocked, and the H1 and H3 air injection holes with the larger pressure difference are selected to generate high-speed jet flow, so that the stability expansion effect is achieved.
The radial position of the gas injection hole H3 is selected within a range Rt<RH3<R4Preferably near the trailing edge of the diffuser vanes. Considering the geometry of the vane diffuser and the volute following it and the self-circulating cavity machining problems, it is recommended to choose RH3=0.9R4。R4Is the vane diffuser exit radius.
The radial position of the gas injection holes H1 is selected based on the extent of the flow separation region on the suction side of the diffuser blade leading edge to optimize the impingement flow separation center location. According to the research data R3<RH1<RtSelecting RH1=1.02R3Preferably, it is used.
The circumferential positions of each group of the gas injection holes (H1, H2 and H3) are selected in two ways, as shown in FIGS. 5(a) and 5(b), three gas injection holes in the same group are arranged along the same radial direction, as shown in FIG. 5(a), connecting lines of the three gas injection holes are crossed with the blade, and H1 is positioned at the leading edge of the diffuser blade close to the suction surface side; two are arranged in the same group of three gas injection holes along the flow direction, and referring to fig. 5(b), the connecting line of the three gas injection holes is not crossed with the blade and is basically consistent with the flow direction of the blade. According to the analysis of the technical principle, only the gas injection holes H1 have the requirement of circumferential position, namely must be positioned in the flow separation area and are optimized in the center position of flow separation.
According to research data, the gas injection holes H1 need to be arranged on the suction surface side of the diffuser blade, and the angle corresponding to the circumferential distance from the leading edge of the diffuser blade is 0-360 degrees/2nIn the range of (a) to (b),nfor diffuser vane count, the angle is 1/3 (360/2)n) Most preferred. Taking the number of 16 diffuser blades as an example, the circumferential positions of the gas injection holes H1 are: is located on the suction surface side of the diffuser blade within the range of 0-11 degrees from the leading edge of the blade by 3 degrees.Most preferably 5 deg.. The gas injection holes H2 and H3 should avoid interference with the diffuser vanes and, in addition, have no requirement for circumferential location. In view of ease of manufacture and general applicability to vaned diffusers having different diffuser vane wrap angles but equal vane numbers, the first arrangement is preferred, i.e., three gas injection holes arranged in the same radial direction.
The opening size of the air injection hole is designed according to two working conditions of blocking and stalling. Under the blocking working condition, in order to effectively shunt, the opening is required to be large; whereas in stall conditions, a smaller orifice is required in order to form a high velocity jet. Considering both, the diameter of the opening is selected from 0.5mm-1.5mm, preferably 1 mm.
According to the size of the opening, the air injection flow of the adjustable self-circulation air injection stability expansion structure is 4% -6% of the total flow of the blade diffuser under the blocking working condition, and is 2% -4% of the total flow of the blade diffuser under the stall working condition.
To achieve selection of the gas injection holes. An adjustable shielding component 4 is arranged in the self-circulation cavity 3; under the blocking working condition, the shielding component is controlled to enable the air injection holes H1 and H2 to work and the air injection holes H3 to be blocked; during stall conditions, the modulating shroud is controlled such that the gas injection holes H1 and H3 operate and the gas injection holes H2 are blocked.
The shielding member 4 may have any structure as long as the above-described function is realized. Figure 3 shows a compact preferred structure. The shutter member 4 is a slidable shutter slider, and the length of the shutter slider is specially designed so that the shutter slider is located between H2 and H3 and the length is slightly greater than the interval between H2 and H3. When the shielding sliding block slides to the first position under the blocking working condition, the shielding sliding block blocks the gas orifice H3 and does not shield the gas orifice H2 and H1; when in a stall condition, the shielding sliding block slides to the second position, releases the gas orifice H3, and blocks the gas orifice H2 but does not block the gas orifice H1.
The self-circulation cavity 3 is independently designed for each group of gas injection holes, and the annular cavities above different gas injection hole groups are not communicated with each other. Preferably, each group shares a vane diffuser rim wall surface with the vane diffuser.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (8)
1. An adjustable self-circulation jet-stabilizing structure for a centrifugal compressor blade diffuser is characterized by comprising: the self-circulation cavity (3) is arranged on the outer side of the rim of the blade diffuser, and the self-circulation cavity (3) is communicated with the flow channel (2) of the blade diffuser through an air injection hole; the three gas injection holes are in a group and named as H1, H2 and H3 from near to far according to the distance from the axis of the centrifugal compressor; each group of the gas injection holes corresponds to one diffuser blade, and the radial distribution area of the three gas injection holes H1, H2 and H3 in the group is positioned in the radial area occupied by the diffuser blade; the air injection holes H1 are located on the leading edge of the diffuser blade close to the suction surface side, the air injection holes H2 and H3 are located behind the throat position of the blade diffuser, the air injection holes H2 are close to the throat, and the air injection holes H3 are close to the trailing edge of the diffuser blade; in the same air injection hole group, the air injection holes H1, H2 and H3 are arranged along the same radial direction, or the air injection holes H1, H2 and H3 are arranged along the flow direction of the same blade of the blade diffuser; in different air injection hole groups, the radial positions of the air injection holes H1 are the same, the radial positions of the air injection holes H2 are the same, and the radial positions of the air injection holes H3 are the same;
an adjustable shielding component (4) is arranged in the self-circulation cavity (3); under the blocking working condition, the shielding component is controlled to enable the air injection hole H1 and the air injection hole H2 to be opened and the air injection hole H3 to be blocked; during a stall condition, the shutter member is controlled so that the gas injection holes H1 and H3 are open and the gas injection holes H2 are blocked.
2. The adjustable self-circulation air injection stabilization structure of claim 1, wherein the radial positions of the air injection holes H1, H2 and H3 are respectively located at 1.02R3、1.01Rt、0.9R4(ii) a Wherein R is3Is the vane diffuser inlet radius, RtIs the vane diffuser throat radius, R4Is the vane diffuser exit radius.
3. The adjustable self-circulating gas injection stability enhancement structure of claim 1, wherein the number of gas injection hole groups is the same as the number of diffuser blades.
4. The adjustable self-circulating jet stabilization structure of claim 3, wherein the angle corresponding to the circumferential distance between the jet holes H1 and the leading edge of the diffuser blade is 0-360 °/2nIn the range of (a) to (b),nthe number of diffuser blades.
5. The adjustable self-circulating gas injection stability augmentation structure of claim 1, wherein the gas injection holes have a diameter in the range of 0.5mm to 1.5 mm; the flow of the gas injection holes is 4% -6% of the total flow of the blade diffuser under the blocking working condition, and is 2% -4% of the total flow of the blade diffuser under the stall working condition.
6. The adjustable self-circulating gas injection stabilization structure according to claim 1, wherein the shielding component (4) is a slidable shielding slider; when the shielding sliding block slides to the first position, the shielding sliding block shields the gas injection hole H3 but does not shield the gas injection holes H2 and H1; when the shielding slide block slides to the second position, the shielding slide block releases the air injection hole H3 to shield the air injection hole H2 but not shield the air injection hole H1.
7. The adjustable self-circulation air injection stability-expanding structure as claimed in claim 1, wherein the self-circulation cavity (3) and the vane diffuser share a wall surface of a rim of the vane diffuser.
8. A centrifugal compressor with a stability expansion structure, wherein the adjustable self-circulation jet stability expansion structure as claimed in any one of claims 1-7 is arranged in a blade diffuser of the centrifugal compressor.
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| CN114321014A (en) * | 2021-12-24 | 2022-04-12 | 中国科学院工程热物理研究所 | Local self-circulation flow control structure of radial diffuser of centrifugal compressor |
| CN115247657B (en) * | 2021-12-27 | 2023-05-09 | 兰州理工大学 | Self-circulation jet anti-cavitation structure and centrifugal pump with same |
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| JP2010151033A (en) * | 2008-12-25 | 2010-07-08 | Ihi Corp | Centrifugal compressor |
| JP2010151032A (en) * | 2008-12-25 | 2010-07-08 | Ihi Corp | Centrifugal compressor |
| CN103967843A (en) * | 2013-02-04 | 2014-08-06 | 中国科学院工程热物理研究所 | Air compressor peripheral groove self-circulating and jetting combined stability extension device and method |
| CN106968724A (en) * | 2015-12-08 | 2017-07-21 | 通用电气公司 | The processing of venturi-effect end wall |
| CN205823738U (en) * | 2016-06-16 | 2016-12-21 | 上海和兰动力科技有限公司 | Vane diffuser for centrifugal compressor |
| CN107228095A (en) * | 2017-07-24 | 2017-10-03 | 北京航空航天大学 | It is a kind of to improve the adaptive compressor of rotator tip and stator corner region flow |
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