Venturi micro-channel cooling structure compressor blade

Abstract

The application discloses a compressor blade with a Venturi micro-channel cooling structure, and the blade tip is provided with an arc-shaped small channel and micro-pores, and the adjacent channels are connected in series, so that the uniform distribution of cooling air is realized, a stable gas film cooling layer is formed on the surface of the blade, and the cooling and cooling effect are obviously improved. The inner wall of the channel adopts a shark skin micro-shield structure, so that the friction resistance is reduced and the turbulent flow characteristics of the airflow are enhanced, and the heat exchange performance is optimized. The grooves penetrating through the surface of the blade change the airflow flow path, destroy the formation of the liquid film cooling layer, thereby prolonging the service life of the blade, and through linkage with the small channel, the cooling effect and the contact of the airflow with the surface of the blade are enhanced, and the heat exchange performance is further improved. The micro-pores of the damping boss not only provide damping effect, but also effectively release cooling air, improve the combination of cooling and structural stability. The application optimizes the cooling effect, and obviously improves the working efficiency and service life of the blade.

Description

Technical Field

[0001] This invention belongs to the field of compressor blades, and more specifically, relates to a compressor blade with a venturi tube microchannel cooling structure. Background Technology

[0002] As a highly efficient and clean power generation device, gas turbines are seeing their share of electricity generation gradually increase in the context of the global pursuit of carbon peaking and carbon neutrality. The efficient operation of a gas turbine relies heavily on the stable functioning of its core component—the blades—which often need to operate continuously in high-temperature environments far exceeding the limits of their materials. Effective cooling measures are essential to ensure the blades can maintain normal operation under extreme conditions.

[0003] Although the operating environment of compressor blades is slightly lower in temperature than that of turbine blades, they still face harsh conditions of high temperature and high pressure. With the continuous increase in the inlet temperature of gas turbines, the cooling requirements of compressor blades also increase. Because compressor blades need to withstand significant thermal loads and aerodynamic forces during compression, especially in the trailing edge region, which has a complex structure and limited space, it is difficult to accommodate too many cooling structures. Commonly used cooling technologies include impingement cooling, finned turbulence, and column-finned turbulence. Among these, column-finned cooling channels are widely used in the trailing edge of compressor blades due to their compactness and high cooling efficiency, achieving structural support and effective cooling within a limited space.

[0004] However, with the continuous rise in inlet temperature of heavy-duty gas turbines, blade cooling faces unprecedented challenges. The traditional column-rib structure, with its enhanced heat transfer effect gradually weakens as the inlet Reynolds number increases, can no longer meet the ever-growing cooling demands.

[0005] In view of this, the present invention is proposed. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art and provide a compressor blade with a venturi tube microchannel cooling structure, thereby solving the problems mentioned in the background art.

[0007] To solve the above-mentioned technical problems, the basic concept of the technical solution adopted by the present invention is as follows:

[0008] A compressor blade with a Venturi tube microchannel cooling structure includes: a blade, the blade having a root and a tip, the tip having a plurality of parallel arc-shaped fine channels, the fine channels having micropores, the micropores being connected to adjacent fine channels, for guiding cooling air to the blade surface to form a stable air film cooling layer.

[0009] The tiny channels are arranged longitudinally and arcuately along the blade and are consistent with the blade surface structure. The surface of the blade is provided with several grooves that extend from the blade root to the blade tip. The blade is also provided with shock-absorbing bosses, and the inner wall of the tiny channels is provided with several linearly arranged vortex generators.

[0010] Optionally, there is a curved transition between the leaf base and the leaf tip, with the degree of curvature ranging from 15° to 45°.

[0011] Optionally, the groove shape conforms to the curve of the blade pressure surface, and the surface roughness of the groove is 20 to 50 micrometers.

[0012] Optionally, the damping boss has a transverse cooling channel inside, and the cooling channel and the micro channel are connected. The surface of the damping boss has several micropores, and the micropores are evenly distributed on the surface of the boss and connected to the inside of the cooling channel.

[0013] Optionally, the outlet of the micro-hole is tilted at 30° and faces the groove, wherein the groove gradually becomes shallower from the inlet to the outlet, so that the cooling air gradually diffuses as it is ejected with the change in the depth of the groove.

[0014] Optionally, the eddy current generator is a protrusion with a deflection angle.

[0015] Optionally, the inner walls of the narrow channels and cooling channels are provided with shield scales to form a sharkskin-inspired biomimetic structure.

[0016] Optionally, the micropores consist of two expanding segments and one contracting segment, with the contracting segment located between the two expanding segments.

[0017] The blade structure of this invention adopts a streamlined design, aiming to optimize the gas compression process through the synergistic effect of the moving and stationary blades, significantly improving the compressor's pressure ratio and flow characteristics. The blade consists of a root and a tip, with multiple parallel, arc-shaped fine channels designed in the tip region. These arc-shaped channels are distributed along the streamline direction of the blade surface, reducing airflow separation and turbulence, thereby reducing flow losses in the high-pressure region, making the airflow smoother, and improving the gas's pressure and kinetic energy. The blade in this application exhibits a smooth arc-shaped profile, a structure that conforms to the core characteristics of streamlined design, namely, reducing airflow resistance and separation.

[0018] Furthermore, the multiple parallel, arc-shaped microchannels on the blade surface conform to the streamlined design principle. These channels follow the natural curvature of the blade and are arranged along the streamline direction. These arc-shaped channels not only guide the smooth flow of cooling air but also reduce airflow interference on the surface, allowing the cooling air to adhere to the blade surface and form a stable film cooling layer.

[0019] Finally, the grooves run from the blade root to the blade tip across the entire blade surface, exhibiting a smooth S-shaped curve. This S-shaped curve design guides the cooling airflow along the blade surface, avoiding direct jet impact and helping to maintain a streamlined distribution of the cooling airflow.

[0020] By employing the blades described in this application, the compressor's pressure ratio can be improved. This improvement is attributed to the optimized streamlined design, which reduces the total pressure loss within the axial diffuser and maintains a more uniform pressure distribution within the compressor. The reduced circumferential pressure distortion at the compressor outlet due to the streamlined design results in more stable airflow characteristics in all regions, lowers the excessive angle of attack at the diffuser blade leading edge, and avoids the problem of increased adverse pressure gradient, thereby improving the overall compression ratio.

[0021] Furthermore, the design of the fine channels helps to ensure a uniform distribution of cooling gas on the blade surface, ensuring that the airflow adheres closely to the blade surface and reducing flow separation. In the high-pressure region, through the rational design of the streamlined blade surface structure, the airflow can adhere more tightly to the blade, reducing flow losses and improving flow efficiency. In the low-pressure region, the airflow is more stable, further reducing flow losses. This structural improvement optimizes the flow characteristics of the airflow within the compressor, thereby improving the overall efficiency and kinetic energy conversion efficiency of the blades.

[0022] By adopting the above technical solution, the present invention has the following beneficial effects compared with the prior art. Of course, any product implementing the present invention does not necessarily need to achieve all of the following advantages at the same time:

[0023] This invention significantly improves cooling efficiency by incorporating arc-shaped microchannels and micropores at the blade tip, combined with a series design of adjacent channels. This ensures uniform distribution of cooling air and the formation of a stable film cooling layer on the blade surface. Simultaneously, grooves penetrating the blade surface optimize the airflow path, enhancing local heat exchange. Vibration-damping bosses provide vibration reduction while releasing cooling air through micropores, integrating cooling and structural stability. Furthermore, vortex generators within the channels generate turbulence, further enhancing heat transfer performance. The overall design effectively reduces the blade's thermal load and vibration fatigue, improving its operating efficiency and service life under high-temperature and high-pressure environments.

[0024] The specific embodiments of the present invention will now be described in further detail with reference to the accompanying drawings. Attached Figure Description

[0025] The accompanying drawings described below are merely some embodiments. Those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0026] In the picture:

[0027] Figure 1 This is a schematic diagram of the three-dimensional structure of the blade;

[0028] Figure 2 This is a schematic diagram of the three-dimensional structure of the blade;

[0029] Figure 3 This is a schematic diagram of the blade cross-section;

[0030] Figure 4 This is a cross-sectional view of the micro-cooling channels;

[0031] Figure 5 This is a diagram of the surface structure of a compressor blade;

[0032] Figure 6 This is one of the simulation comparison images of the micropores of the present invention and existing technologies;

[0033] Figure 7 This is the second simulation comparison image of the micropores of the present invention and existing technologies;

[0034] Figure 8 This is the third simulation comparison diagram of the micropores of the present invention and existing technologies;

[0035] Figure 9 This is a contour plot of the flow velocity of the blades during operation.

[0036] Figure 10 This is a pressure contour diagram of the blade during operation.

[0037] The attached diagram lists the components represented by each number as follows:

[0038] 1. Leaf blade; 2. Leaf root; 3. Leaf tip; 4. Fine channel; 5. Micropore; 6. Groove; 7. Shock-absorbing boss; 8. Vortex generator; 9. Cooling channel; 10. Micropore; 11. Tapering section; 12. Expanding section; 13. Shield scale.

[0039] It should be noted that these accompanying drawings and textual descriptions are not intended to limit the scope of the invention in any way, but rather to illustrate the concept of the invention to those skilled in the art by referring to specific embodiments. Detailed Implementation

[0040] The invention will now be described in further detail with reference to the accompanying drawings.

[0041] Please see Figure 1-10As shown, this embodiment provides a compressor blade with a Venturi tube microchannel cooling structure, including a blade 1. The blade 1 has two parts: a blade root 2 and a blade tip 3. The blade tip 3 is provided with several parallel-arranged arc-shaped fine channels 4. The fine channels 4 are provided with micropores 5, which are connected to adjacent fine channels 4 to guide cooling air to the surface of the blade 1 to form a stable film cooling layer. The combination of arc-shaped fine channels 4 and micropores 5 provides a highly efficient and uniform cooling solution for the blade 1. The arc-shaped arrangement of the fine channels 4 perfectly matches the shape of the blade 1, which not only optimizes the flow path of the cooling air but also enhances the stability of the airflow. The micropores 5 further precisely guide the cooling air to the surface of the blade 1, forming a continuous and stable film cooling layer under high-temperature conditions, effectively isolating the high-temperature airflow and significantly reducing the thermal load of the blade 1. This design not only improves the heat resistance of the blade 1 but also reduces material damage caused by thermal stress, thereby extending the service life of the blade 1 and ensuring the efficient and stable operation of the gas turbine under extreme conditions.

[0042] The fine channels 4 are arranged longitudinally and arcuately along the blade 1 and conform to the surface structure of the blade 1. The surface of the blade 1 has several grooves 6 extending from the blade root 2 to the blade tip 3. The blade 1 also has damping bosses 7, and the inner wall of the fine channels 4 is equipped with several linearly arranged vortex generators 8. Through the longitudinal and arcuate arrangement of the fine channels 4, the cooling structure perfectly matches the external aerodynamic shape of the blade 1, ensuring uniform distribution of cooling air across the entire blade 1 surface, thereby optimizing the overall heat dissipation effect. The grooves 6 extending from the blade root 2 to the blade tip 3 further guide the flow of cooling air, improving heat exchange efficiency. The damping bosses 7 not only enhance the structural stability of the blade 1 but also provide additional cooling capacity through the internal cooling channels 9, significantly reducing fatigue damage caused by vibration during high-speed operation of the blade 1. Furthermore, the linear vortex generators 8 arranged on the inner wall of the channels generate turbulent airflow, enhancing heat exchange between the cooling air and the inner wall of the channels, effectively improving the cooling performance of the blade 1.

[0043] In this embodiment, the blade root 2 and blade tip 3 form a curved transition, with a curvature ranging from 15° to 45°, preferably 30°. This 30° curvature achieves an optimal balance between mechanical and aerodynamic performance. The 30° curvature is sufficient to effectively disperse the stress borne by the blade 1 during operation, reducing localized stress concentration and improving the fatigue resistance of the blade 1. Simultaneously, the curvature angle allows airflow to flow more smoothly along the blade surface. This curvature angle effectively prevents airflow separation. Airflow separation typically leads to irregular airflow, forming vortices, which increases friction and resistance, resulting in energy waste. The curvature angle keeps the airflow in contact with the blade surface, reducing this separation.

[0044] Furthermore, optimizing the bending angle can reduce aerodynamic losses. Aerodynamic losses refer to the energy loss caused by friction and uneven flow when airflow passes over the blade surface. Through bending design, airflow can flow more smoothly, reducing unnecessary drag and allowing the airflow to more efficiently complete the compression and acceleration process of the gas.

[0045] Ultimately, this design not only improves airflow stability and efficiency but also enhances the overall efficiency of the gas turbine. Smoother airflow and reduced energy loss lead to improved system efficiency. This is analogous to optimizing the path of water flow, allowing it to move faster and with less effort, thereby increasing overall performance.

[0046] In this embodiment, the groove 6 is shaped to conform to the curve of the pressure surface of the blade 1, and the surface roughness of the groove 6 is 20 to 50 micrometers, preferably 50 micrometers. The groove 6, conforming to the curve of the pressure surface of the blade 1, effectively guides the cooling air along an optimized flow path, avoiding the impact and dispersion problems caused by straight airflow, thereby improving cooling efficiency. When the surface of the groove has a certain roughness, the rougher the surface, the more contact the cooling air has with the groove surface. The rough surface causes the airflow to no longer flow smoothly, but rather generates turbulence. This turbulence helps the air to better contact the blade surface, carrying away more heat.

[0047] When the roughness reaches 50 micrometers, the irregularity of the groove surface increases significantly. This will significantly increase the contact area between the airflow and the surface. A larger contact area means that the airflow can contact the surface more extensively, making the flow of cooling air more turbulent and generating more eddies. These eddies increase the contact area between the air and the blade surface, allowing the air to more effectively absorb the heat from the blade surface and enhance heat exchange.

[0048] Furthermore, by creating through grooves on the blade surface, the stability of the liquid film cooling layer can be effectively disrupted, causing disturbances in the cooling airflow and altering its flow path. This prevents the cooling airflow from forming an overly stable liquid film layer on the blade surface, thus reducing the residence time of liquid substances on the blade surface. This disturbance promotes a more uniform distribution of the cooling airflow and the formation of a less stable gas film layer on the surface, making it difficult for liquid to accumulate.

[0049] In this way, the cooling airflow reduces contact with the blade surface and the chance of liquid accumulation, thus effectively reducing the risk of corrosion. This not only improves the durability of the blades but also extends their service life and reduces maintenance costs.

[0050] In this embodiment, the damping boss 7 has a transverse cooling channel 9 inside, and the cooling channel 9 is connected to the microchannel 4. The surface of the damping boss 7 has a plurality of micropores 10, which are evenly distributed on the surface of the boss and connected to the interior of the cooling channel 9. Through the connection between the transverse cooling channel 9 and the microchannel 4, cooling air can flow into the damping boss 7 efficiently and be sprayed onto the surface of the blade 1 through the evenly distributed micropores 10, forming a stable air film cooling layer. This not only significantly improves the cooling effect in the boss area but also protects the structural integrity of the blade 1 during high-temperature operation. Furthermore, by absorbing vibration and dispersing stress, the damping boss 7 improves the stability and fatigue resistance of the blade 1 under high-speed operation, thereby extending the service life of the blade 1.

[0051] In this embodiment, the outlet of the micro-orifice 10 is tilted at 30° and faces the groove 6, wherein the groove 6 gradually becomes shallower from the inlet to the outlet, so that the cooling air gradually diffuses as it is ejected with the change in depth of the groove 6. The cooling air can be injected into the groove 6 at an optimized angle, effectively enhancing the airflow's directionality and adhesion. The 30° tilt angle allows the cooling air to smoothly adhere to the inner wall of the groove 6, reducing turbulence and scattering during injection and ensuring that the cooling airflow forms a stable film cooling layer on the surface of the blade 1. In addition, the gradually shallowing design of the groove 6 guides the cooling air to gradually diffuse, making the airflow distribution more uniform and further improving cooling efficiency.

[0052] In this embodiment, the vortex generator 8 is a protrusion with a deflection angle. By arranging a protruding structure with a deflection angle within the cooling channel 9, the cooling airflow can be effectively guided, and strong turbulence can be formed in local areas. This turbulence enhances the contact time and heat transfer efficiency between the cooling air and the inner wall of the channel, thereby significantly improving the overall cooling performance of the blade 1.

[0053] In this embodiment, the inner walls of the fine channels 4 and cooling channels 9 are provided with shield scales 13 to form a shark skin-inspired structure. The microscopic shield scale structure of shark skin has unique surface characteristics that can significantly improve the flow characteristics of fluids. Simulating this structure on the inner wall of the cooling channel of the blade can effectively reduce the frictional resistance between the cooling air and the inner wall of the channel. The fine structure of the shark skin surface (such as shield scales) can form tiny vortices during the flow process. These vortices help the airflow maintain higher kinetic energy and reduce the direct contact between the airflow and the channel wall, thereby reducing frictional losses. It can be seen that by simulating the microscopic shield scale structure of shark skin on the channel wall, the turbulence of the airflow is increased, which can improve the cooling efficiency. Specifically, the enhancement of turbulence can help the cooling air be distributed more evenly on the blade surface, avoiding local concentration or excessive flow of airflow, thereby improving the cooling effect.

[0054] By mimicking the microstructure of shark skin, not only is the frictional resistance of airflow effectively reduced and the stability of airflow improved, but the turbulence characteristics are also enhanced, allowing the cooling air to exchange heat with the blade surface more efficiently, thereby improving the cooling effect and overall operating efficiency of the gas turbine.

[0055] Furthermore, the fish-scale shields and microstructures can improve the thermal conductivity of the fluid, allowing heat to be transferred more quickly from high-temperature regions to low-temperature regions. The fish-scale shields and microstructures increase the total volume of the heat exchange surface, thereby improving heat exchange efficiency.

[0056] In this embodiment, the micropores 5 are composed of two expanding sections 12 and one contracting section 11, with the contracting section 11 located between the two expanding sections 12. The contracting section 11 is a narrowing section where the inner wall of the channel gradually narrows from the normal diameter of the channel towards the center, and the airflow is accelerated in this region. The expanding section 12 immediately follows the contracting section, and the channel gradually expands back to its normal diameter. This expansion section is designed to guide the airflow to decelerate while forming a local vortex zone. In the contracting section, the air is forced to flow faster, and the increased flow velocity leads to a significant decrease in static pressure. In the expanding section, the airflow velocity slows down, and the static pressure increases to a level higher than the pressure at the inlet, thereby achieving pressurization. The cooperation of the contracting and expanding sections enables efficient pressurization without any moving mechanical parts, making the system more reliable and requiring less maintenance.

[0057] More specifically, the results of comparing the venturi tube microchannel cooling structure of this application with the micropores of the prior art's through-hole structure are shown in the attached diagram. Figure 6-8 As shown.

[0058] This invention is not limited to the embodiments described above. Anyone should understand that structural changes made under the guidance of this invention, and any technical solutions that are the same as or similar to this invention, fall within the protection scope of this invention. Technical aspects, shapes, and structures not described in detail in this invention are all publicly known technologies.

Claims

1. A compressor blade with a Venturi tube microchannel cooling structure, characterized in that, include: The blade (1) has two parts: the leaf root (2) and the leaf tip (3). The leaf root (2) and the leaf tip (3) are respectively located at both ends of the axial direction of the blade (1). The leaf tip (3) is provided with several parallel arc-shaped fine channels (4). The fine channels (4) are provided with micropores (5). The micropores (5) are connected to the adjacent fine channels (4), and every two adjacent fine channels (4) are connected in series. The small channels (4) are arranged longitudinally and arc-shaped along the blade (1) and are consistent with the surface structure of the blade (1). The surface of the blade (1) is provided with several grooves (6) that run from the blade root (2) to the blade tip (3). The blade (1) is also provided with multiple shock-absorbing bosses (7), and the inner wall of the small channels (4) is provided with several linearly arranged vortex generators (8). The shock-absorbing boss (7) is provided with a transverse cooling channel (9) inside, and the cooling channel (9) and the fine channel (4) are connected. The surface of the shock-absorbing boss (7) is provided with a number of micro holes (10), and the micro holes (10) are evenly distributed on the surface of the boss and connected to the interior of the cooling channel (9). The air outlet of the micropore (10) is tilted at 30° and faces the groove (6), wherein the groove (6) gradually becomes shallower from the inlet to the outlet, so that the cooling air will gradually diffuse as the depth of the groove (6) changes when it is ejected.

2. A compressor blade with a Venturi tube microchannel cooling structure according to claim 1, characterized in that, There is a curved transition between the leaf root (2) and the leaf tip (3), and the degree of curvature is 15°-45°.

3. A compressor blade with a Venturi tube microchannel cooling structure according to claim 1, characterized in that, The shape of the groove (6) conforms to the curve of the pressure surface of the blade (1), and the surface roughness of the groove (6) is 20 to 50 micrometers.

4. A compressor blade with a Venturi tube microchannel cooling structure according to claim 1, characterized in that, The eddy current generator (8) is a protrusion with a deflection angle.

5. A compressor blade with a Venturi tube microchannel cooling structure according to claim 1, characterized in that, The inner walls of the narrow channels (4) and cooling channels (9) are provided with shield scales (13) to form a sharkskin-inspired biomimetic structure.

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