Backflow prevention vanes and rotors for axial flow compressors
By designing anti-backflow blades on the axial compressor to prevent backflow, the problem of efficiency reduction caused by gas backflow and underflow is solved, achieving higher boosting and pressurization capabilities and efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- CHENGDU CHENGFA SCI & TECH POWER ENG
- Filing Date
- 2025-08-21
- Publication Date
- 2026-06-26
AI Technical Summary
In existing axial compressors, gas backflow and leakage flow lead to a decrease in boosting and pressurization capacity, resulting in reduced efficiency.
Design an anti-backflow blade with an anti-backflow edge at the top of the blade basin. The anti-backflow edge extends away from the back of the blade at an angle of 80-120°, with a thickness of 0.5-2 times the thickness of the blade tip and a height of 0.03-0.1 times the height of the blade body. A rounded chamfer transition is provided between the anti-backflow edge and the blade body.
It effectively blocks backflow and underflow in radial motion, reduces flow loss, improves pressurization and pressure boosting capabilities, and enhances efficiency.
Smart Images
Figure CN224413956U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of axial flow compressor technology, and more specifically, to an anti-backflow vane and rotor for an axial flow compressor. Background Technology
[0002] An axial compressor is a type of bladed machine that uses the rotation of blades to perform work, greatly increasing the velocity of the gas and converting kinetic energy into pressure energy. To ensure safe operation during blade rotation, a suitable radial clearance is usually provided between the blades and the outer flow channel. This is especially true for industrial axial compressors, where larger and safer radial clearances are used to ensure long-term stable and safe operation. During unit operation, the pressurized airflow flows axially back through the radial clearance to the inlet side, and the high static pressure airflow at the blade head also flows submerged through the radial clearance to the blade back. Both backflow and submerged flow reduce the blade's pressurization and pressure-boosting capacity, leading to decreased efficiency. Utility Model Content
[0003] The purpose of this invention is to provide an anti-backflow vane and rotor for an axial compressor. It has a novel structure and can achieve less flow loss, higher boosting and pressurization capacity, and higher efficiency while ensuring safe radial clearance.
[0004] The embodiments of this utility model are implemented as follows:
[0005] An anti-backflow blade for an axial compressor includes a blade body with opposing blade basin and blade back sides. An anti-backflow edge is provided at the top of the blade basin side, and the anti-backflow edge extends away from the blade back side.
[0006] Furthermore, in other preferred embodiments of this utility model, the angle between the anti-backflow edge and the blade body is 80~120°.
[0007] Furthermore, in other preferred embodiments of this invention, the thickness of the leaf gradually decreases along the direction from the leaf base to the leaf tip.
[0008] Furthermore, in other preferred embodiments of this utility model, the thickness of the anti-backflow edge is 0.5 to 2 times the thickness of the blade tip.
[0009] Furthermore, in other preferred embodiments of this utility model, the height of the anti-backflow edge is 0.03 to 0.1 times the blade body.
[0010] Furthermore, in other preferred embodiments of this utility model, a rounded chamfer transition is provided between the anti-backflow edge and the blade body.
[0011] Furthermore, in other preferred embodiments of this utility model, the thickness of the anti-backflow edge is 1~5 mm, and the height is 0.5~2 mm; the radius of the rounded chamfer is 0.5~2 mm.
[0012] A rotor for an axial compressor includes a shaft and a plurality of the aforementioned anti-backflow vanes.
[0013] Furthermore, in other preferred embodiments of this utility model, the angle between the anti-backflow vane and the axis of rotation is 40~60°.
[0014] Furthermore, in other preferred embodiments of this utility model, the multiple anti-backflow blades are divided into multiple moving blade groups, and the multiple anti-backflow blades in each moving blade group are evenly distributed along the circumference of the rotating shaft, and the multiple moving blade groups are spaced apart along the axial direction of the rotating shaft.
[0015] The beneficial effects of this utility model embodiment are:
[0016] This invention provides an anti-backflow blade for an axial compressor, comprising a blade body with opposing blade facet and blade back sides. An anti-backflow edge is provided at the top of the blade facet side, extending away from the blade back side. This anti-backflow edge design effectively blocks radial backflow and subsurface flow, resulting in less flow loss, higher boosting and pressurizing capacity, and higher efficiency. Attached Figure Description
[0017] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.
[0018] Figure 1 This is a schematic diagram of the moving blade in the prior art and its cross-sectional view on plane AA;
[0019] Figure 2 A schematic diagram and a cross-sectional view of the anti-backflow vane for an axial compressor provided for an embodiment of the present invention;
[0020] Figure 3 This is a schematic diagram of a rotor for an axial compressor provided in an embodiment of the present invention.
[0021] Icons: 100-moving blade; 110-blade body; 111-blade basin side; 112-blade back side; 200-anti-backflow blade; 210-blade body; 211-blade basin side; 212-blade back side; 220-anti-backflow side; 300-outer flow channel; 20-rotor; 21-shaft; 22-moving blade assembly. Detailed Implementation
[0022] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this utility model, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model. Therefore, the following detailed description of the embodiments of this utility model provided in the accompanying drawings is not intended to limit the scope of the claimed utility model, but merely represents selected embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the scope of protection of this utility model.
[0023] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.
[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this utility model, "a plurality of" means two or more, unless otherwise explicitly specified.
[0025] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. For those skilled in the art, the specific meaning of the above terms in this utility model can be understood according to the specific circumstances.
[0026] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature. Example
[0027] like Figure 1 As shown, in the prior art, the moving blade 100 is a blade mounted on the rotor of an axial compressor. It is typically arc-shaped, with the blade body 110 including an inwardly concave blade basin side 111 and an outwardly convex blade back side 112. The blade basin side 111 faces away from the air intake direction of the axial compressor, while the blade back side 112 faces the air intake direction. To ensure the safety of the rotor during rotation, a suitable radial clearance is usually provided between the moving blade 100 and the outer flow channel 300. During the operation of the axial compressor, since the blade basin side 111 is located on the side of the high-pressure gas, the gas will travel radially across the top of the moving blade 100 and through the radial clearance to reach the blade back side 112, which is gas backflow. Furthermore, the high static pressure airflow from the blade basin side 111 will also flow through the radial clearance to the blade back side 112, which is gas underflow. Both backflow and underflow will cause a decrease in the pressurization and boosting capacity and efficiency of the moving blade 100.
[0028] This embodiment provides an anti-backflow vane 200 for an axial flow compressor, such as... Figure 2As shown, it includes a blade body 210, which includes opposing blade basin side 211 and blade back side 212. An anti-backflow edge 220 is provided at the top of the blade basin side 211, extending away from the blade back side 212. By providing the anti-backflow edge 220 at the top of the blade basin side 211, backflow and undercurrent can be effectively intercepted. The anti-backflow edge 220 extends from the leading edge to the trailing edge along the chord direction of the blade basin side 211, thereby achieving less flow loss, higher pressurization and boosting capacity, and higher efficiency.
[0029] Furthermore, the angle between the anti-backflow edge 220 and the blade 210 is 80~120°. Preferably, it is set to 90°, as this angle range achieves better interception efficiency. Increasing the angle further increases the chance of backflow and undercurrent overflow, reducing interception efficiency. Conversely, decreasing the angle hinders gas movement, easily leading to turbulent resonance and reducing the service life of the anti-backflow blade 200.
[0030] Optionally, the thickness of the blade body 210 gradually decreases from the blade base to the blade tip. The thickness of the anti-backflow edge 220 is 0.5 to 2 times the thickness of the blade tip. The height of the anti-backflow edge 220 is 0.03 to 0.1 times the thickness of the blade body. If the thickness or height of the anti-backflow edge 220 is too large, it will cause the center of gravity of the blade body to be too high. The torque generated by the high center of gravity under the action of airflow can easily damage the blade body 210. Within the size range of this embodiment, the anti-backflow edge 220 can not only achieve better interception efficiency, but also has little impact on the center of gravity distribution of the anti-backflow blade 200, and will not disrupt the balance of the rotor during rotation. It should be noted that the thickness of the blade body 210 refers to the distance from the blade back side 212 to the blade base side 211, while the thickness of the anti-backflow edge 220 refers to the dimension in the same direction as the thickness of the blade body 210. The height of the blade body 210 refers to the distance from the blade base to the blade tip, while the height of the anti-backflow edge 220 refers to the dimension in the same direction as the height of the blade body 210.
[0031] In addition, a rounded chamfer transition is provided between the anti-backflow edge 220 and the blade 210. The rounded chamfer transition makes the airflow movement smoother and further reduces flow loss.
[0032] Optionally, the thickness of the anti-backflow edge 220 is 1~5 mm, and the height is 0.5~2 mm; the radius of the rounded chamfer is 0.5~2 mm. Correspondingly, the radial clearance is 1~2 mm. Under these dimensions, the overall strength of the blade 210 and the anti-backflow edge 220 can be guaranteed, and higher aerodynamic efficiency can be obtained.
[0033] In addition, the height of the anti-backflow edge 220 can be set to be gradual. As it moves away from the blade back side 212, the height of the anti-backflow edge 220 gradually decreases, thereby forming an inclined surface (not shown) at the top of the anti-backflow edge 220. The strength of the anti-backflow edge 220 is enhanced by utilizing the triangular support principle.
[0034] This embodiment also provides a rotor 20 for an axial flow compressor, such as... Figure 3 As shown, it includes a rotating shaft 21 and multiple anti-backflow blades 200 as described above.
[0035] Furthermore, the anti-backflow vane 200 and the axis of the rotating shaft 21 form an angle of 40° to 60°. This maintains a relatively good pressurization efficiency for the gas.
[0036] Multiple anti-backflow blades 200 are divided into multiple moving blade groups 22. The multiple anti-backflow blades 200 in each moving blade group 22 are evenly distributed along the circumference of the rotating shaft 21, and the multiple moving blade groups 22 are spaced apart along the axial direction of the rotating shaft 21. This achieves the effect of continuous pressurization in stages.
[0037] In summary, this utility model embodiment provides an anti-backflow vane 200 for an axial flow compressor, which includes a vane body 210. The vane body 210 includes opposing vane basin side 211 and vane back side 212. An anti-backflow edge 220 is provided at the top of the vane basin side 211, and the anti-backflow edge 220 extends away from the vane back side 212. The design of the anti-backflow edge 220 can effectively block radial backflow and undercurrent, thereby achieving less flow loss, higher pressurization and boosting capacity, and higher efficiency.
[0038] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.
Claims
1. An anti-backflow vane for an axial compressor, characterized in that, The leaf includes a leaf body, which includes a leaf base side and a leaf back side, and the top of the leaf base side is provided with an anti-backflow edge, which extends away from the leaf back side.
2. The anti-backflow blade according to claim 1, characterized in that, The angle between the anti-backflow edge and the blade body is 80~120°.
3. The anti-backflow blade according to claim 2, characterized in that, The thickness of the leaf gradually decreases from the leaf base to the leaf tip.
4. The anti-backflow blade according to claim 3, characterized in that, The thickness of the anti-backflow edge is 0.5 to 2 times the thickness of the blade tip.
5. The anti-backflow blade according to claim 4, characterized in that, The height of the anti-backflow edge is 0.03 to 0.1 times the blade body.
6. The anti-backflow blade according to claim 5, characterized in that, A rounded chamfer transition is provided between the anti-backflow edge and the blade body.
7. The anti-backflow blade according to claim 6, characterized in that, The thickness of the anti-backflow edge is 1~5 mm, and the height is 0.5~2 mm; the radius of the rounded chamfer is 0.5~2 mm.
8. A rotor for an axial compressor, characterized in that, It includes a rotating shaft and a plurality of anti-backflow blades as described in any one of claims 1 to 7.
9. The rotor according to claim 8, characterized in that, The anti-backflow vane forms an angle of 40° to 60° with the axis of the rotating shaft.
10. The rotor according to claim 9, characterized in that, The multiple anti-backflow blades are divided into multiple moving blade groups. The multiple anti-backflow blades in each moving blade group are evenly distributed along the circumference of the rotating shaft, and the multiple moving blade groups are spaced apart along the axial direction of the rotating shaft.