CN116696842A - Compressor blade and impeller - Google Patents
Compressor blade and impeller Download PDFInfo
- Publication number
- CN116696842A CN116696842A CN202310843389.5A CN202310843389A CN116696842A CN 116696842 A CN116696842 A CN 116696842A CN 202310843389 A CN202310843389 A CN 202310843389A CN 116696842 A CN116696842 A CN 116696842A
- Authority
- CN
- China
- Prior art keywords
- blade
- compressor
- blade surface
- bottom end
- hub
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000009792 diffusion process Methods 0.000 abstract description 6
- 238000013461 design Methods 0.000 description 8
- 238000000034 method Methods 0.000 description 8
- 230000000694 effects Effects 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000011162 downstream development Methods 0.000 description 2
- 238000010408 sweeping Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/388—Blades characterised by construction
Abstract
The application relates to the technical field of compressors, in particular to a compressor blade and an impeller, which comprise: the blade comprises a first blade surface and a second blade surface which are integrally formed, wherein the first blade surface is arranged along the vertical direction, the bottom end of the first blade surface is connected with the top end of the second blade surface, and a preset included angle is formed between the second blade surface and the first blade surface, so that the second blade surface is bent towards the suction side of the blade; the leading edge of the second leaf surface is swept forward in the flow direction. According to the application, leakage vortex at the gap between the blade and the hub can be weakened, the blockage is reduced, and the diffusion capability of the blade is improved.
Description
Technical Field
The application relates to the technical field of compressors, in particular to a compressor blade and an impeller.
Background
In some gas turbines, a gap is provided between the blade root of the compressor and the hub, and a high static pressure gradient across the blade near the gap induces strong leakage flow in the rotor gap region. The strong leakage flow interferes with the suction surface boundary layer of the blade and shears with the main flow, a large low-speed area is induced at the root of the blade of the air compressor, and a large low-speed fluid mass is induced along with the strong leakage vortex, so that not only is the large aerodynamic loss caused, but also the airflow channel is seriously blocked and the occurrence of rotating stall of the air compressor is aggravated, and the working stability of the air compressor is seriously affected.
Therefore, there is a need for a compressor blade and impeller that solves the above problems.
Disclosure of Invention
The embodiment of the application provides a compressor blade and an impeller, which can weaken leakage vortex at a gap between the blade and a hub, reduce blockage and improve the diffusion capability of the blade.
In a first aspect, an embodiment of the present application provides a compressor blade, including: the blade comprises a first blade surface and a second blade surface which are integrally formed, wherein the first blade surface is arranged along the vertical direction, the bottom end of the first blade surface is connected with the top end of the second blade surface, and a preset included angle is formed between the second blade surface and the first blade surface so that the second blade surface is bent towards the suction side of the blade;
the leading edge of the second leaf surface is swept forward in the flow direction.
In one possible design, the vertical distance d1 from the intersection point of the middle section axis of the first blade surface and the middle section axis of the second blade surface to the bottom end of the second blade surface is in the range of:
5g＜d1＜0.2h；
wherein g is the gap height between the bottom end of the second blade surface and the hub of the compressor; h is the distance between the top end of the first leaf surface to the bottom end of the second leaf surface.
In one possible design, the preset angle is an angle between a middle section axis of the first leaf surface and a middle section axis of the second leaf surface.
In one possible design, the preset included angle has a value ranging from 0 ° to 45 °.
In one possible design, the forward swept portion of the second leaf surface has a triangular shape with a leading edge that is swept forward in the flow direction.
In one possible design, a perpendicular distance from an intersection point of an extension line of a hypotenuse of the triangle to a trailing edge direction of the second blade surface and an extension line of an edge of the leading edge to a hub direction to a bottom end of the second blade surface is equal to a perpendicular distance from an intersection point of a middle section axis of the first blade surface and a middle section axis of the second blade surface to the bottom end of the second blade surface.
In one possible design, the angle between the hypotenuse of the triangle and the bottom end of the second leaf surface is in the range of 0-45 °.
In one possible design, the cross-sectional shapes of the first and second lobes are both: the direction from the leading edge to the trailing edge becomes larger and then smaller.
In a second aspect, an embodiment of the present application provides a compressor wheel comprising: a hub and a plurality of blades of any of the designs described above;
the plurality of blades are uniformly arranged along the circumferential direction of the hub.
In the embodiment of the application, the load distribution of the root of the blade can be changed by bending the second blade surface towards the suction side of the blade and forward sweeping the front edge of the second blade surface towards the flow direction, so that the maximum load is reduced and forward moved, the load of the front edge is increased, and the load of the middle part is reduced. On the one hand, the maximum load is advanced, and the leading edge load is increased, so that the starting point of the leakage vortex entering the flow field is advanced. On the other hand, the maximum load is reduced, so that the vortex core strength of the leakage vortex is reduced, the leakage vortex is influenced by the middle load in the downstream development process, and therefore the load in the middle of the blade is reduced, and the leakage flow is weakened. Therefore, the compressor blade provided by the application can weaken leakage vortex at the gap between the blade and the hub, reduce blockage and improve the diffusion capacity of the blade, thereby improving the pressure ratio and efficiency of the compressor.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a prior art blade according to an embodiment of the present application;
FIG. 2 is an axial view of a compressor blade at an angle according to an embodiment of the present application;
FIG. 3 is an axial view of a compressor blade at another angle in accordance with an embodiment of the present application;
FIG. 4 is a side view of a compressor blade provided in accordance with an embodiment of the present application;
FIG. 5 is a front view of a compressor blade provided in accordance with an embodiment of the present application;
FIG. 6 is a schematic illustration of leakage vortex created by a prior art blade;
fig. 7 is a schematic view of leakage vortex generated by the vane provided by the application.
Reference numerals:
1-leaf blade;
11-a first leaf surface; 12-a second leaf surface;
2-wheel hubs.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments, and all other embodiments obtained by those skilled in the art without making any inventive effort based on the embodiments of the present application are within the scope of protection of the present application.
As shown in fig. 1, a schematic structural diagram of a compressor blade provided in the prior art is shown. As can be seen from the figure, the blades are arranged perpendicularly to the radial direction, the cross-sectional area remaining unchanged. The vane can generate strong leakage vortex near the clearance between the vane top and the hub, so that not only is the aerodynamic loss reduced, but also the airflow channel is seriously blocked, and the phenomena of rotating stall of the compressor and the like are aggravated.
For the above reasons, the inventors have improved the vane profile of the compressor.
As shown in fig. 2 to 5, in a first aspect, an embodiment of the present application provides a compressor blade, including: the first blade surface 11 and the second blade surface 12 are integrally formed, the first blade surface 11 is arranged along the vertical direction, the bottom end of the first blade surface 11 is connected with the top end of the second blade surface 12, and a preset included angle is formed between the second blade surface 12 and the first blade surface 11, so that the second blade surface 12 is bent towards the suction side of the blade 1;
the leading edge of the second blade face 12 is swept forward in the direction of flow.
In this embodiment, by bending the second blade face 12 toward the suction side of the blade 1 and sweeping the leading edge of the second blade face 12 forward in the flow direction, the load distribution at the root of the blade 1 can be changed, the maximum load can be reduced and shifted forward, the leading edge load can be increased, and the center load can be reduced. On the one hand, the maximum load is advanced, and the leading edge load is increased, so that the starting point of the leakage vortex entering the flow field is advanced. On the other hand, the maximum load is reduced, so that the vortex core strength of the leakage vortex is reduced, the leakage vortex is influenced by the middle load in the downstream development process, and therefore the load in the middle of the blade 1 is reduced, and the leakage flow is weakened. It can be seen that the compressor blade provided by this embodiment can weaken the leakage vortex at the gap between the blade 1 and the hub 2, reduce the blockage and improve the diffusion capability of the blade 1, thereby improving the pressure ratio and efficiency of the compressor.
As shown in fig. 4, in some embodiments, the vertical distance d1 from the intersection point of the middle section axis of the first blade surface 11 and the middle section axis of the second blade surface 12 to the bottom end of the second blade surface 12 is in the range of:
5g＜d1＜0.2h；
wherein g is the height of the gap between the bottom end of the second blade surface 12 and the hub 2 of the compressor; h is the distance from the top end of the first leaf surface 11 to the bottom end of the second leaf surface 12.
In addition, the preset included angle is an included angle between the middle section axis of the first blade surface 11 and the middle section axis of the second blade surface 12. The preset included angle alpha has a value ranging from 0 to 45 deg., preferably from 20 to 30 deg..
In some embodiments, as shown in fig. 5, the forward-swept portion of the leading edge of the second leaf surface 12 is triangular in shape.
In some embodiments, the perpendicular distance from the intersection point of the extension line of the hypotenuse of the triangle to the direction of the trailing edge of the second blade surface 12 and the extension line of the edge of the leading edge to the direction of the hub 2 to the bottom end of the second blade surface 12 is equal to the perpendicular distance from the intersection point of the middle section axis of the first blade surface 11 and the middle section axis of the second blade surface 12 to the bottom end of the second blade surface 12.
Further, the angle β between the hypotenuse of the triangle and the base end of the second leaf surface 12 has a value ranging from 0 to 45 °, preferably from 20 to 30 °.
In some embodiments, the cross-sectional shape of the first leaf surface 11 and the second leaf surface 12 are both: the direction from the leading edge to the trailing edge becomes larger and then smaller.
Through the arrangement, the load distribution of the root of the blade 1 can be effectively improved, the vortex core strength of leakage vortex is reduced, the blocking is reduced, the diffusion capacity of the blade is improved, and the pressure ratio and the efficiency of the compressor are further improved.
In order to demonstrate the effect of the inventive vane in reducing leakage vortex, the inventors conducted simulation tests on the prior art vane and the inventive vane, and the test results are shown in fig. 6 and 7. Wherein, FIG. 6 is a leakage vortex generated by using a prior art blade, and FIG. 7 is a leakage vortex generated by using a blade of the present application. As can be seen from the graph, the vortex core strength of the leakage vortex in fig. 7 is significantly smaller than that in fig. 6. Therefore, the compressor blade provided by the application can effectively improve the load distribution of the blade root, reduce the vortex core strength of leakage vortex, reduce blockage and improve the diffusion capacity of the blade, thereby improving the pressure ratio and efficiency of the compressor.
In a second aspect, an embodiment of the present application further provides a compressor wheel, including a hub 2 and a plurality of blades 1 provided in any of the above embodiments;
the plurality of blades 1 are uniformly arranged along the circumferential direction of the hub 2.
It should be noted that, the compressor impeller provided in this embodiment and the compressor blade provided in the previous embodiment have the same technical effects, and the technical effects of each implementation in this embodiment are not described herein.
It is noted that relational terms such as first and second, and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one …" does not exclude the presence of additional identical elements in a process, method, article or apparatus that comprises the element.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and are not limiting; although the application has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present application.
Claims (9)
1. A compressor blade, comprising: the blade comprises a first blade surface (11) and a second blade surface (12) which are integrally formed, wherein the first blade surface (11) is arranged in the vertical direction, the bottom end of the first blade surface (11) is connected with the top end of the second blade surface (12), and a preset included angle is formed between the second blade surface (12) and the first blade surface (11), so that the second blade surface (12) is bent towards the suction side of the blade (1);
the leading edge of the second leaf surface (12) is swept forward in the direction of flow.
2. The compressor blade according to claim 1, characterized in that the perpendicular distance d1 from the intersection point of the mid-section axis of the first blade face (11) and the mid-section axis of the second blade face (12) to the bottom end of the second blade face (12) is in the range of:
5g＜d1＜0.2h；
wherein g is the height of a gap between the bottom end of the second blade surface (12) and the hub (2) of the compressor; h is the distance between the top end of the first leaf surface (11) and the bottom end of the second leaf surface (12).
3. The compressor blade according to claim 2, wherein the preset angle is the angle of the mid-section axis of the first blade face (11) to the mid-section axis of the second blade face (12).
4. A compressor blade according to claim 3, wherein the predetermined included angle has a value in the range of 0 to 45 °.
5. The compressor blade according to claim 2, wherein the forward edge of the second blade face (12) is triangular in shape to the forward swept portion of the flow direction.
6. The compressor blade according to claim 5, wherein a perpendicular distance from an intersection point of an extension line of a hypotenuse of the triangle to a trailing edge direction of the second blade surface (12) and an extension line of an edge of the leading edge to a hub (2) direction to a bottom end of the second blade surface (12) is equal to a perpendicular distance from an intersection point of a middle section axis of the first blade surface (11) and a middle section axis of the second blade surface (12) to the bottom end of the second blade surface (12).
7. The compressor blade according to claim 6, characterized in that the angle between the hypotenuse of the triangle and the bottom end of the second blade face (12) is in the range of 0-45 °.
8. The compressor blade according to any one of claims 1 to 7, wherein the first and second blade faces (11, 12) each have a cross-sectional shape of: the direction from the leading edge to the trailing edge becomes larger and then smaller.
9. An impeller of a compressor, characterized by comprising a hub (2) and a plurality of blades (1) according to any one of claims 1-8;
a plurality of the blades (1) are uniformly arranged along the circumferential direction of the hub (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310843389.5A CN116696842A (en) | 2023-07-10 | 2023-07-10 | Compressor blade and impeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310843389.5A CN116696842A (en) | 2023-07-10 | 2023-07-10 | Compressor blade and impeller |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116696842A true CN116696842A (en) | 2023-09-05 |
Family
ID=87835855
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310843389.5A Pending CN116696842A (en) | 2023-07-10 | 2023-07-10 | Compressor blade and impeller |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116696842A (en) |
-
2023
- 2023-07-10 CN CN202310843389.5A patent/CN116696842A/en active Pending
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