Semi-open centripetal impeller structure and engine
By setting a fluid dissipation structure at the back notch of the semi-open centripetal impeller, the energy of the leakage flow is consumed by cavity, wall impact and vortex dissipation, which solves the energy dissipation problem caused by leakage vortex in the disc cavity and significantly improves the aerodynamic performance and efficiency of the impeller.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC HUNAN AVIATION POWERPLANT RES INST
- Filing Date
- 2026-03-06
- Publication Date
- 2026-05-12
AI Technical Summary
The leakage vortex formed at the notch on the back of the semi-open radial impeller causes energy dissipation, resulting in a decrease in impeller efficiency.
A fluid dissipation structure, including a honeycomb structure and a porous structure, is set at the wheel back gap between adjacent blades to dissipate the sealing leakage flow energy through cavity, wall impact and vortex dissipation.
It effectively suppresses leakage flow, reduces energy loss, and improves aerodynamic performance and impeller efficiency.
Smart Images
Figure CN122014356A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of power machinery technology, specifically to a semi-open radial impeller structure and engine. Background Technology
[0002] The impeller disk 13' of the semi-open radial impeller, serving as the mounting carrier for the impeller, is a key component for transmitting rotational power and bearing loads. The semi-enclosed cavity formed by the impeller back 11' and the impeller back partition is the impeller disk cavity. To prevent high-temperature gas leakage and ensure the impeller operates within a safe temperature range, a sealing cold gas stream needs to be introduced from the compressor outlet and injected into the low-pressure area at the center of the impeller. Under the action of the centrifugal force of the impeller rotation, it diffuses outwards to the outer periphery of the disk cavity, forming a gas barrier to prevent high-temperature gas leakage. The structure of the semi-open radial impeller is as follows: Figure 1 As shown.
[0003] As the impeller load increases, the circumferential lateral pressure difference of the impeller increases. Under the combined effect of the pressure difference and centrifugal force, the sealing cold air at the outermost periphery of the disk forms a sealing gas leakage suction surface branch G. 吸力 With sealing gas leakage pressure surface branch G 压力 Two airflows, see Figure 2 and Figure 3 The pressure side branch accounts for most of the sealing leakage flow. The sealing leakage flow mixes and interacts with other secondary flows in the channel, forming a large-span disc cavity leakage vortex at the impeller back notch 12', generating a large amount of energy dissipation, which leads to a sharp drop in the impeller efficiency of the centripetal impeller. Summary of the Invention
[0004] In view of this, the present invention provides a semi-open radial impeller structure and engine to solve the problem of leakage vortices in the disc cavity formed at the notch on the back of the semi-open radial impeller, which causes a large amount of energy dissipation.
[0005] In a first aspect, the present invention provides a semi-open radial impeller structure, comprising:
[0006] blade; The wheel has a wheel back and a wheel back notch, the wheel back notch being located between two adjacent blades; a fluid dissipation structure is provided at the wheel back notch, the fluid dissipation structure being able to dissipate the sealing leakage flow energy through at least one of cavity, wall impact and vortex dissipation.
[0007] Beneficial Effects: The semi-open radial impeller structure, by incorporating a fluid dissipation structure at the notch on the impeller back between adjacent blades, can dissipate energy from the sealing leakage flow using at least one of the following methods: cavity, wall impact, and vortex dissipation. This effectively suppresses the leakage from the pressure surface branch of the sealing gas in the impeller disk cavity, reducing energy loss caused by the leakage flow. After the leakage flow forms a vortex and dissipates kinetic energy within the fluid dissipation structure, it creates a stable airflow obstruction in the notch area on the impeller back, further hindering the flow of the pressure surface branch of the sealing gas and weakening the leakage flow intensity. This significantly improves the aerodynamic performance and impeller efficiency of the radial impeller.
[0008] In one alternative embodiment, the fluid dissipation structure includes: At least one of the following: honeycomb structure, porous structure, grid structure, groove array structure, raised array structure, labyrinth structure, vortex structure, damping cavity structure, and corrugated wall structure.
[0009] Beneficial effects: Fluid dissipation structures can utilize at least one of the following: honeycomb structure, porous structure, grid structure, groove array structure, protrusion array structure, labyrinth structure, vortex structure, damping cavity structure, and corrugated wall structure. By employing cavity effect, wall impact, and vortex dissipation, they can dissipate energy from the sealed leakage flow, ensuring the suppression and energy dissipation of the leakage flow and improving the aerodynamic performance and working efficiency of the centripetal impeller.
[0010] In one optional embodiment, the fluid dissipation structure is a honeycomb structure; the honeycomb structure is a honeycomb strip composed of continuously and uniformly distributed hexagonal honeycomb truncated pyramids.
[0011] Beneficial effects: The use of a honeycomb structure as a fluid dissipation structure, with the honeycomb structure consisting of a honeycomb band composed of continuously and uniformly distributed hexagonal honeycomb truncated pyramids, can form a regular and stable cavity array at the wheel back notch. This allows the sealing leakage flow to fully impact the wall surface and form vortices after entering the honeycomb cavity, efficiently dissipating the leakage flow energy. It also forms a stable airflow wall at the wheel back notch, further suppressing the leakage of the sealing gas leakage pressure surface branch, reducing energy loss, and thus significantly improving the aerodynamic performance and working efficiency of the centripetal impeller. At the same time, the continuously and uniformly distributed structure is easy to process and form, has good structural stability, and reliable leakage suppression and energy dissipation effects.
[0012] In one alternative embodiment, the honeycomb strips are uniformly distributed along the circumference of the impeller at the notch on the back of the impeller.
[0013] Beneficial effects: The honeycomb belt is evenly distributed along the impeller circumference at the notch on the back of the impeller, which can dissipate the sealing leakage flow evenly and stably in the circumferential direction, ensuring that the leakage suppression effect between each blade channel is consistent, avoiding additional losses caused by excessive local leakage or uneven flow, and further improving the overall aerodynamic performance and operational stability of the centripetal impeller.
[0014] In one alternative embodiment, the wheel back notch has a U-shaped corner; The cellular strip extends from one side of the U-shaped corner along the other side of the U-shaped corner.
[0015] Beneficial effects: The wheel back notch is provided with a U-shaped corner, and the honeycomb strip extends from one side of the U-shaped corner to the other side, which enables the honeycomb structure to fully cover the key leakage area of the wheel back notch, especially the U-shaped corner, where leakage flow is prone to accumulate and form vortex dead angles, thus achieving comprehensive interception and energy dissipation of the sealing leakage flow.
[0016] In one alternative embodiment, the honeycomb strip covers the bottom of the entire impeller back notch along the circumferential span of the impeller.
[0017] Beneficial effects: The honeycomb belt covers the bottom of the entire impeller back notch along the circumferential span of the impeller, which can achieve full circumferential and dead-angle coverage of the leakage flow area within the impeller back notch. This ensures that the leakage flow cannot bypass the honeycomb belt from the bottom of the impeller back notch, further enhancing the interception and dissipation effect on the branch of the sealing gas leakage pressure surface, avoiding leakage escape due to local non-coverage, thereby forming a more stable airflow wall, effectively reducing leakage loss, and improving the aerodynamic performance and efficiency of the centripetal impeller.
[0018] In one alternative embodiment, the circumferential span of the honeycomb belt along the impeller does not exceed 1 / 2 of the height of the impeller back.
[0019] Beneficial effects: The span of the honeycomb belt along the impeller circumference does not exceed 1 / 2 of the impeller back height. Under the premise of ensuring effective dissipation and suppression of leakage flow, the honeycomb belt avoids occupying too much space, reduces interference with the overall structural strength and aerodynamic flow field of the impeller, ensures the impeller's operational stability and structural reliability, and at the same time takes into account the leakage suppression and energy dissipation effect and the impeller's own structural performance.
[0020] In one alternative embodiment, the honeycomb strip is arranged at an angle θ to the impeller axis to form an airflow wall at the impeller back notch, thereby hindering the flow of the sealing gas leakage pressure surface branch.
[0021] Beneficial effects: The honeycomb belt is arranged at an angle θ with the impeller axis, which can be adaptively optimized according to the actual flow direction of the branch of the sealing gas leakage pressure surface. By adjusting the intensity and flow direction of the vortex in the honeycomb cavity through the angle θ, the energy dissipation effect on the leakage flow is enhanced, and a stable airflow wall is formed at the impeller back notch, thereby better hindering the flow of the branch of the sealing gas leakage pressure surface, improving the suppression effect on the leakage flow, reducing energy loss, and improving the aerodynamic performance and working efficiency of the centripetal impeller.
[0022] In one alternative embodiment, the cellular truncated pyramid includes: The upper cavity is a hexagonal prism structure; The lower cavity is a hexagonal pyramid structure.
[0023] Beneficial effects: The honeycomb truncated structure, which is composed of an upper cavity with a hexagonal prism structure and a lower cavity with a hexagonal pyramid structure, can form a stepped, variable cross-section cavity structure inside the honeycomb. This allows the leakage flow to generate vortices with higher intensity and more controllable direction when flowing through the upper and lower cavities, further enhancing the wall impact and energy dissipation of the sealing leakage flow.
[0024] Secondly, the present invention also provides an engine comprising the semi-open radial impeller structure described in any of the preceding claims.
[0025] Beneficial effects: Due to the adoption of the above-mentioned semi-open radial impeller structure, the engine can dissipate energy of the sealing leakage flow through the fluid dissipation structure at the impeller back notch by means of cavity, wall impact and vortex dissipation, effectively suppressing the leakage of the sealing gas leakage pressure surface branch of the radial impeller, reducing the energy loss caused by leakage flow, and ensuring the impeller efficiency of the radial impeller. Attached Figure Description
[0026] To more clearly illustrate the technical solutions in the specific embodiments or related technologies of the present invention, the drawings used in the description of the specific embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.
[0027] Figure 1 This is a schematic diagram of the structure of a semi-open radial impeller in related technologies; Figure 2 This is a schematic diagram illustrating the state of sealing gas leakage in a semi-open radial impeller in related technologies. Figure 3 A simulation diagram of the sealing gas leakage of a semi-open radial impeller in related technologies; Figure 4 This is a schematic diagram of the fluid dissipation structure at the notch on the back of a semi-open radial impeller according to an embodiment of the present invention. Figure 5 This is a schematic diagram showing the position of the U-shaped corner of the wheel back notch of a semi-open radial impeller according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the interception state of the airflow wall at the wheel back notch of this invention against the branch of the sealing gas leakage pressure surface; Figure 7 This is a schematic diagram of the honeycomb strip arrangement at the wheel back notch in an embodiment of the present invention; Figure 8 This is a three-dimensional structural diagram of a honeycomb truncated pyramid according to an embodiment of the present invention; Figure 9 This is a front view schematic diagram of a honeycomb truncated pyramid structure according to an embodiment of the present invention; Figure 10 The simulation diagram of Mach number for a semi-open radial impeller in related technologies; Figure 11 The simulation diagram of the Mach number of the semi-open radial impeller of the present invention; Figure 12 Simulation diagram of the mixing state of the disc cavity leakage vortex in a semi-open radial impeller in related technologies; Figure 13 This is a simulation diagram of the mixing state of the leakage vortex in the disk cavity of the semi-open radial impeller of the present invention.
[0028] Explanation of reference numerals in the attached figures: 11' Wheel arch; 12' Wheel arch notch; 13' Wheel disc; 10. Impeller; 11. Roulette; 112. Wheel arch notch; 1121. U-shaped corner; 20. Fluid dissipation structures; 21. Upper cavity; 22. Lower cavity; 30. Airflow wall. Detailed Implementation
[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.
[0030] In the description of the invention, it should be noted that, unless otherwise stated, "a plurality of" means two or more; the terms "upper," "lower," "left," "right," "inner," "outer," "front end," "rear end," "head," "tail," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element 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 the invention. Furthermore, the terms "first," "second," "third," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance.
[0031] In the description of this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0032] In compact power systems such as micro gas turbines and aerospace auxiliary power units, centripetal impellers have become key components for energy conversion due to their core advantages of compact structure, strong adaptability to varying operating conditions, and low manufacturing and maintenance costs. With the development of aerospace technology, the equivalent power and performance requirements of impellers are constantly increasing. Centripetal impellers are gradually developing towards a high expansion ratio. The requirements of a high expansion ratio and compact structure necessitate high-load designs for centripetal impellers. To achieve high power density and high energy conversion efficiency, the blade tip speed of centripetal impellers is relatively high, resulting in significant centrifugal stress at the blade root and impeller disk. Furthermore, as the impeller inlet temperature increases, the strength issue of centripetal impellers becomes particularly prominent. To comprehensively consider impeller strength and performance, semi-open centripetal impellers have been developed. Based on conventional centripetal impellers, the rotor disk at the inlet section is removed, significantly reducing rotor weight and centrifugal stress on the impeller disk. For the structure of semi-open centripetal impellers in related technologies, please refer to [link to related technologies]. Figure 1 .
[0033] The impeller disk of a semi-open radial impeller, serving as the mounting carrier for the impeller, is a key component for transmitting rotational power and bearing loads. The semi-enclosed cavity formed by the impeller back and the impeller back partition is the impeller disk cavity. To prevent high-temperature gas leakage and ensure the impeller operates within a safe temperature range, a sealing cold gas stream needs to be introduced from the compressor outlet and injected into the low-pressure zone at the center of the impeller. Under the action of the centrifugal force of the impeller rotation, it diffuses outwards from the disk cavity, forming a gas barrier to prevent high-temperature gas leakage. As the impeller load increases, the circumferential lateral pressure difference of the impeller increases. Under the combined action of the pressure difference and centrifugal force, the sealing cold gas at the outermost periphery of the disk cavity forms two airflows: a sealing gas leakage suction side branch and a sealing gas leakage pressure side branch. The pressure side branch accounts for the majority of the sealing leakage flow. like Figure 2 and Figure 3 As shown, the sealing leakage flow mixes and interacts with other secondary flows in the channel, forming a large-span disc cavity leakage vortex at the impeller back notch, generating a large amount of energy dissipation. This leads to a sharp decrease in the impeller efficiency of the centripetal impeller, creating an inherent contradiction between protection and efficiency. Therefore, there is an urgent need for a semi-open centripetal impeller structure that can suppress the branching of the pressure surface of the disc cavity sealing gas leakage.
[0034] The following is combined with Figures 4 to 13 Embodiments of the present invention are described.
[0035] According to embodiments of the present invention, in one aspect, such as Figure 4 and Figure 7 As shown, a semi-open radial impeller structure is provided, comprising: blade; The wheel 11 has a wheel back and a wheel back notch 112, the wheel back notch 112 is located between two adjacent blades; a fluid dissipation structure 20 is provided at the wheel back notch 112, the fluid dissipation structure 20 can dissipate the sealing leakage flow energy through at least one of cavity, wall impact and vortex dissipation.
[0036] The semi-open radial impeller structure, by setting a fluid dissipation structure 20 at the impeller back notch 112 between adjacent blades, can dissipate energy of the sealing leakage flow through at least one of the following methods: cavity, wall impact, and vortex dissipation. This effectively suppresses the leakage of the sealing gas leakage pressure surface branch in the impeller disk cavity and reduces the energy loss caused by the leakage flow. After the leakage flow forms a vortex and dissipates kinetic energy within the fluid dissipation structure 20, it can form a stable airflow obstruction in the region of the impeller back notch 112, further hindering the flow of the sealing gas leakage pressure surface branch and weakening the leakage flow intensity, thereby significantly improving the aerodynamic performance and impeller efficiency of the radial impeller.
[0037] In some embodiments, the fluid dissipation structure 20 includes: At least one of the following: honeycomb structure, porous structure, grid structure, groove array structure, raised array structure, labyrinth structure, vortex structure, damping cavity structure, and corrugated wall structure.
[0038] The fluid dissipation structure 20 can utilize at least one of the following structures: honeycomb structure, porous structure, grid structure, groove array structure, raised array structure, labyrinth structure, vortex structure, damping cavity structure, and corrugated wall structure. It employs various methods such as cavity effect, wall impact, and vortex dissipation to dissipate energy from the sealed leakage flow, ensuring effective leakage suppression and energy dissipation, and improving the aerodynamic performance and working efficiency of the centripetal impeller. In practical applications, any one or any combination of these methods can be flexibly selected according to the actual working conditions, resulting in diverse structural forms and strong applicability.
[0039] In the following embodiments, the fluid dissipation structure 20 is a honeycomb structure as an example for illustration.
[0040] In some embodiments, such as Figure 4 , Figure 5 and Figure 7 As shown, the fluid dissipation structure 20 is a honeycomb structure; the honeycomb structure is a honeycomb strip composed of continuously and uniformly distributed hexagonal honeycomb truncated pyramids.
[0041] The honeycomb structure is used as the fluid dissipation structure 20. The honeycomb structure is composed of a honeycomb band of continuously and uniformly distributed hexagonal honeycomb truncated pyramids. It can form a regular and stable cavity array at the wheel back notch 112. After the sealing leakage flow enters the honeycomb cavity, it fully impacts the wall and forms a vortex, which efficiently dissipates the leakage flow energy. A stable airflow wall 30 is formed at the wheel back notch 112, which further suppresses the leakage of the sealing gas leakage pressure surface branch and reduces energy loss, thereby significantly improving the aerodynamic performance and working efficiency of the centripetal impeller. At the same time, the continuously and uniformly distributed structure is easy to process and form, has good structural stability, and reliable leakage suppression and energy dissipation effect.
[0042] Specifically, this embodiment uses a regular hexagonal honeycomb truncated pyramid, which results in more uniform dissipation and better consistency in the suppression of leakage.
[0043] In some embodiments, such as Figure 7 As shown, the honeycomb strip is evenly distributed along the circumference of the impeller 10 at the notch 112 on the back of the impeller.
[0044] The honeycomb strip is evenly distributed along the impeller 10 circumferential direction at the impeller back notch 112, which can make the sealing leakage flow uniformly and stably dissipated in the circumferential direction, ensuring that the leakage suppression effect between each blade channel is consistent, avoiding additional losses caused by excessive local leakage or uneven flow, and further improving the overall aerodynamic performance and operational stability of the centripetal impeller.
[0045] In some embodiments, such as Figure 4 and Figure 5 As shown ( Figure 5 The black shaded area in the middle shows the location of the U-shaped corner 1121; the wheel arch notch 112 has the U-shaped corner 1121; The honeycomb strip extends from one side of the U-shaped corner 1121 along the other side of the U-shaped corner 1121.
[0046] The wheel back notch 112 is provided with a U-shaped bend 1121, and the honeycomb strip extends from one side of the U-shaped bend 1121 to the other side, which enables the honeycomb structure to fully cover the key leakage area of the wheel back notch 112, especially the U-shaped bend 1121, where leakage flow is prone to accumulate and form vortex dead angles, thus achieving comprehensive interception and energy dissipation of the sealing leakage flow.
[0047] In some embodiments, the honeycomb strip covers the bottom of the entire impeller back notch 112 along the circumferential span of the impeller 10.
[0048] The honeycomb belt covers the bottom of the entire impeller back notch 112 along the circumferential span of the impeller 10, which can achieve full circumferential and dead-angle coverage of the leakage flow area within the impeller back notch 112. This ensures that the leakage flow cannot bypass the honeycomb belt from the bottom of the impeller back notch 112, further enhancing the interception and dissipation effect on the branch of the sealing gas leakage pressure surface, avoiding leakage escape due to local non-coverage, thereby forming a more stable airflow wall 30, effectively reducing leakage loss, and improving the aerodynamic performance and efficiency of the centripetal impeller.
[0049] In some embodiments, the circumferential span of the honeycomb belt along the impeller 10 does not exceed 1 / 2 of the height of the impeller back.
[0050] The honeycomb belt spans no more than 1 / 2 of the impeller back height along the circumference of the impeller 10. While ensuring effective dissipation and suppression of leakage flow, the honeycomb belt avoids occupying too much space, reduces interference with the overall structural strength and aerodynamic flow field of the impeller 10, ensures the operational stability and structural reliability of the impeller 10, and takes into account both leakage suppression and energy dissipation effects and the structural performance of the impeller 10 itself.
[0051] In some embodiments, such as Figure 7 As shown (x direction in the figure is the axial direction of impeller 10), the honeycomb belt is arranged at an angle θ with the axial direction of impeller 10 to form an airflow wall 30 at the impeller back notch 112, which hinders the flow of the sealing gas leakage pressure surface branch. Figure 6 A schematic diagram showing the state of the airflow wall 30 obstructing the sealing leakage pressure surface branch is shown.
[0052] The honeycomb strip is arranged at an angle θ with the impeller 10 axis. This angle can be adaptively optimized according to the actual flow direction of the branch of the sealing gas leakage pressure surface. By adjusting the angle θ, the intensity and flow direction of the vortex in the honeycomb cavity are enhanced, thereby increasing the energy dissipation effect on the leakage flow. A stable airflow wall 30 is formed at the impeller back notch 112, which better hinders the flow of the branch of the sealing gas leakage pressure surface, improves the suppression effect on the leakage flow, reduces energy loss, and improves the aerodynamic performance and working efficiency of the centripetal impeller.
[0053] In some embodiments, such as Figure 8 As shown, the cellular truncated pyramid includes: Upper cavity 21, upper cavity 21 is a hexagonal prism structure; Lower cavity 22 is a hexagonal pyramid structure.
[0054] The honeycomb truncated structure, which is composed of an upper cavity 21 with a hexagonal prism structure and a lower cavity 22 with a hexagonal pyramid structure, can form a stepped, variable cross-section cavity structure inside the honeycomb. This allows the leakage flow to generate vortices with higher intensity and more controllable direction when flowing through the upper cavity 21 and the lower cavity 22, further enhancing the wall impact and energy dissipation of the sealing leakage flow.
[0055] like Figure 9As shown, the regular hexagonal honeycomb truncated cone can optimize the depth h1 of the upper cavity 21, the depth h2 of the lower cavity 22, and the width d1 of the upper cavity 21 and the width d2 of the lower cavity 22, so that the leaking fluid forms a stable, efficient, and complete energy dissipation vortex flow field in the concave cavity of the honeycomb structure, thereby achieving the purpose of better suppressing the leakage flow.
[0056] In one embodiment, h1 is 0.4 mm, h2 is 0.2 mm, d1 is 1.5 mm, and d2 is 0.5 mm, which can increase the impeller efficiency by 0.1 percentage points.
[0057] Furthermore, in conjunction with the U-shaped bend 1121 at the wheel back notch and the full-coverage honeycomb belt arrangement, it can achieve all-round, no-dead-angle energy dissipation and leakage suppression in areas where leakage flow is prone to accumulate and vortex dead angles are easily formed. It can more efficiently hinder the flow of the branch of the sealing gas leakage pressure surface, significantly reduce leakage loss, and improve the aerodynamic performance and working efficiency of the centripetal impeller.
[0058] Figure 10 and Figure 11 The figures shown are simulation diagrams of the Mach number of the semi-open radial impeller of the related technology and the present invention, respectively. The circled portions in both figures are visible. Figure 11 As shown in the figure, the area of the high Mach number region within the circled region of the present invention is significantly reduced, and this region corresponds to the branch of the sealing leakage pressure surface.
[0059] Figure 12 and Figure 13 The images show simulation diagrams of the mixing state of leakage vortices in the disk cavity of a semi-open radial impeller, representing both related technologies and the present invention. The circled areas in both images are visible. Figure 13 As shown in the diagram, the mixing of leakage vortices in the disc cavity within the circled area of the present invention is significantly reduced.
[0060] In summary, after the semi-open radial impeller of the present invention is provided with a honeycomb band composed of regular hexagonal honeycomb truncated pyramids at the impeller back notch 112, the leakage of the sealing gas leakage pressure surface branch is significantly reduced, effectively reducing energy loss and ensuring the impeller efficiency of the semi-open radial impeller.
[0061] According to an embodiment of the present invention, another aspect provides an engine including a semi-open radial impeller structure.
[0062] Because the engine adopts a semi-open radial impeller structure, it can dissipate energy of the sealing leakage flow through the fluid dissipation structure 20 at the impeller back notch 112 by means of cavity, wall impact and vortex dissipation. This effectively suppresses the leakage of the sealing gas leakage pressure surface branch of the radial impeller, reduces the energy loss caused by leakage flow, and ensures the impeller efficiency of the radial impeller.
[0063] Furthermore, the U-shaped corner 1121 and the honeycomb strip extending along the corner can fully cover the critical leakage area of the wheel back notch 112, achieving comprehensive interception and energy dissipation at the parts where leakage flow is prone to accumulate and form vortex dead zones. It forms a stable airflow blocking effect in the wheel back notch 112 area, further hindering the flow of the sealing gas leakage pressure surface branch and weakening the leakage flow intensity, thereby significantly improving the aerodynamic performance and working efficiency of the engine.
[0064] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by this application.
Claims
1. A semi-open radial impeller structure, characterized in that, include: blade; The wheel (11) is provided with a wheel back and a wheel back notch (112), the wheel back notch (112) being located between two adjacent blades; a fluid dissipation structure (20) is provided at the wheel back notch (112), the fluid dissipation structure (20) being able to dissipate the sealing leakage flow energy through at least one of cavity, wall impact and vortex dissipation.
2. The semi-open radial impeller structure according to claim 1, characterized in that, The fluid dissipation structure (20) includes: At least one of the following: honeycomb structure, porous structure, grid structure, groove array structure, raised array structure, labyrinth structure, vortex structure, damping cavity structure, and corrugated wall structure.
3. The semi-open radial impeller structure according to claim 2, characterized in that, The fluid dissipation structure (20) is a honeycomb structure; the honeycomb structure is a honeycomb strip composed of continuously and uniformly distributed hexagonal honeycomb truncated pyramids.
4. The semi-open radial impeller structure according to claim 3, characterized in that, The honeycomb strip is evenly distributed along the circumference of the impeller (10) at the notch on the back of the impeller (112).
5. The semi-open radial impeller structure according to claim 4, characterized in that, The wheel back notch (112) has a U-shaped corner (1121); The cellular strip extends from one side of the U-shaped corner (1121) along the other side of the U-shaped corner (1121).
6. The semi-open radial impeller structure according to claim 4, characterized in that, The honeycomb strip covers the bottom of the entire wheel back notch (112) along the circumferential span of the impeller (10).
7. The semi-open radial impeller structure according to claim 3, characterized in that, The circumferential span of the honeycomb belt along the impeller (10) does not exceed 1 / 2 of the height of the impeller back.
8. The semi-open radial impeller structure according to claim 3, characterized in that, The honeycomb strip is arranged at an angle θ with the impeller (10) axis to form an airflow wall (30) at the impeller back notch (112) to obstruct the flow of the sealing gas leakage pressure surface branch.
9. The semi-open radial impeller structure according to any one of claims 3 to 8, characterized in that, The honeycomb truncated pyramid includes: Upper cavity (21), wherein the upper cavity (21) is a hexagonal prism structure; The lower cavity (22) is a hexagonal pyramid structure.
10. An engine, characterized in that, The semi-open radial impeller structure includes any one of claims 1 to 9.