Compressor blade with Venturi tube micro-channel cooling structure

Abstract

The invention discloses a compressor blade with a venturi tube micro-channel cooling structure, which realizes uniform distribution of cooling air and forms a stable air film cooling layer on the surface of the blade by arranging arc-shaped fine channels and fine pores on the tip of the blade and combining the series design of adjacent channels, thereby obviously improving the cooling effect. The inner wall of the channel is of a sharkskin microcosmic placoid scale structure, friction resistance is reduced, the airflow turbulence characteristic is enhanced, and therefore the heat exchange performance is optimized. The grooves penetrating through the surface of the blade prolong the service life of the blade by changing the flowing path of the air flow and destroying the formation of a liquid film cooling layer, and enhance the cooling effect and the contact between the air flow and the surface of the blade through linkage with the small channels, thereby further improving the heat exchange performance. And the micropores of the damping boss not only provide a damping effect, but also can effectively release cooling air, so that the combination of cooling and structural stability is improved. While the cooling effect is optimized, the working efficiency of the blade is remarkably improved, and the service life of the blade is remarkably prolonged.

Description

Technical Field

[0001] The invention belongs to the field of compressor blades, and in particular relates to a compressor blade with a venturi tube microchannel cooling structure. Background Art

[0002] As an efficient and clean power generation device, gas turbines are gradually increasing their share of power generation as the world actively pursues the goals of carbon peak and carbon neutrality. The efficient operation of gas turbines is inseparable from the stable operation of their core components, the blades, which often need to continue to operate in a high temperature environment far higher than the tolerance limit of their own materials. In order to ensure that the blades can maintain normal operation under extreme conditions, effective cooling measures must be taken.

[0003] Although the working 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. As the temperature of the front inlet of the gas turbine continues to increase, the cooling demand of the compressor blades also increases. Since the compressor blades need to withstand significant heat loads and aerodynamic forces during the compression process, especially at the trailing edge, the structure is complex and the space is narrow, making it difficult to accommodate too many cooling structures. Common cooling technologies include impingement cooling, fin spoiler and column rib spoiler. Among them, column rib cooling channels are widely used at the trailing edge of compressor blades due to their compactness and efficient cooling capacity, so as to achieve structural support and effective cooling in a limited space.

[0004] However, as the inlet temperature of heavy-duty gas turbines continues to rise, the cooling of blades faces unprecedented challenges. The traditional column fin structure gradually weakens its enhanced heat exchange effect when the inlet Reynolds number increases, and it is difficult to meet the growing cooling needs.

[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 deficiencies of the prior art and provide a compressor blade with a venturi tube microchannel cooling structure, thereby solving the problems raised in the above-mentioned background technology.

[0007] In order to solve the above technical problems, the basic concept of the technical solution adopted by the present invention is:

[0008] A compressor blade with a venturi tube microchannel cooling structure, comprising: a blade, the blade having a blade root and a blade tip, the blade tip being provided with a plurality of arc-shaped fine channels arranged in parallel, the fine channels being provided with fine pores, the fine pores being connected with adjacent fine channels, and being used for guiding cooling air to the blade surface to form a stable air film cooling layer;

[0009] The small channels are arranged along the longitudinal direction and arc shape of the blade and are consistent with the surface structure of the blade. The surface of the blade is provided with a plurality of grooves running from the root to the tip of the blade. The blade is also provided with a shock-absorbing boss, and the inner wall of the small channel is provided with a plurality of linearly arranged vortex generators.

[0010] Optionally, there is a curved transition between the blade root and the blade tip, and the degree of curvature is 15°-45°.

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

[0012] Optionally, a transverse cooling channel is provided inside the shock-absorbing boss, and the cooling channel is connected to the small channel. A plurality of micropores are provided on the surface of the shock-absorbing boss, and the micropores are evenly distributed on the boss surface and connected to the inside of the cooling channel.

[0013] Optionally, the air outlet of the micropore is inclined 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 the depth of the groove changes when it is ejected.

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

[0015] Optionally, shield scales are provided around the inner walls of the small channels and cooling channels to form a shark skin bionic structure.

[0016] Optionally, the fine pores are composed of two gradually expanding sections and one gradually contracting section, wherein the gradually contracting section is located between the two gradually expanding sections.

[0017] The blade structure of the present invention adopts a streamlined design, aiming to optimize the gas compression process through the synergistic effect of the dynamic and static blades, and significantly improve the pressure ratio and flow characteristics of the compressor. The blade consists of two parts: the root and the tip, and a plurality of parallel arc-shaped small channels are designed in the tip area. These arc-shaped channels are distributed along the streamline direction of the blade surface, reducing the separation and turbulence of the airflow, thereby reducing the flow loss in the high-pressure area, making the airflow flow more stable, and improving the pressure energy and kinetic energy of the gas. The blade in the present application presents a smooth arc-shaped profile as a whole. This structure meets the core characteristics of the streamlined design, namely reducing the flow resistance and separation of the airflow;

[0018] In addition, the multiple parallel arc-shaped small channels on the blade surface conform to the streamline design principle. These channels follow the natural curvature of the blade and are arranged along the streamline direction. This arc-shaped channel not only guides the smooth flow of cooling air, but also reduces the interference of air flow on the surface, allowing the cooling air to adhere to the blade surface to form a stable air film cooling layer;

[0019] Finally, the groove runs through the entire blade surface from the root to the tip, presenting a smooth S-shaped curve. The S-shaped curve design guides the cooling air to flow along the blade surface, avoiding direct jet impact of the airflow and helping to maintain the streamlined distribution of the cooling airflow.

[0020] By adopting the blades of the present application, the pressure ratio of the compressor can be improved, and the improvement of the pressure ratio is due to the optimization of the streamlined design, which reduces the total pressure loss in the axial flow section diffuser and maintains a relatively uniform pressure distribution in the compressor. The circumferential pressure distortion reduced by the streamlined design at the compressor outlet makes the flow characteristics of the airflow in various areas more stable, reduces the excessive angle of attack of the leading edge of the diffuser blade, avoids the problem of increased adverse pressure gradient, and thus improves the overall compression ratio.

[0021] In addition, the design of small channels helps to evenly distribute the cooling gas on the blade surface, ensuring that the airflow adheres to the blade surface and reducing flow separation. In the high-pressure area, by rationally designing the streamlined blade surface structure, the airflow can adhere more closely to the blade, reducing flow losses and improving flow efficiency. In the low-pressure area, the airflow flows more smoothly, further reducing flow losses. This structural improvement optimizes the flow characteristics of the airflow in the compressor, thereby improving the overall efficiency and kinetic energy conversion efficiency of the blade.

[0022] After 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 the advantages described below at the same time:

[0023] The present invention significantly improves the cooling efficiency by setting up arc-shaped fine channels and fine pores inside them at the blade tip, combined with the series design of adjacent channels, to ensure that the cooling air is evenly distributed and a stable air film cooling layer is formed on the blade surface. At the same time, the grooves running through the blade surface optimize the flow path of the cooling airflow and enhance the local heat exchange effect; the shock-absorbing boss releases cooling air through the micropores while providing a vibration reduction function, realizing the integration of cooling and structural stability; in addition, the vortex generator in the channel generates turbulence, further enhancing the heat exchange performance. The overall design effectively reduces the thermal load and vibration fatigue of the blade, and improves the operating efficiency and service life of the blade in high temperature and high pressure environments.

[0024] The specific implementation modes of the present invention are further described in detail below with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The drawings described below are only some embodiments. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0026] In the figure:

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

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

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

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

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

[0032] Figure 6 This is one of the simulation comparison diagrams of the micro pores of the present invention and the prior art;

[0033] Figure 7 This is the second simulation comparison diagram of the micro pores of the present invention and the prior art;

[0034] Figure 8 This is the third simulation comparison diagram of the micro pores of the present invention and the prior art;

[0035] Fig. 9 It is the velocity contour diagram of the blade in operation;

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

[0037] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0038] 1. Blade; 2. Blade root; 3. Blade tip; 4. Tiny channel; 5. Tiny pores; 6. Grooves; 7. Shock-absorbing boss; 8. Vortex generator; 9. Cooling channel; 10. Micropores; 11. Tapered section; 12. Expanded section; 13. Shield scales.

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

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

[0041] See also Figure 1-10As shown, in this embodiment, a compressor blade with a venturi tube microchannel cooling structure is provided, including a blade 1, wherein the blade 1 has a blade root 2 and a blade tip 3, wherein the blade tip 3 is provided with a plurality of arc-shaped fine channels 4 arranged in parallel, wherein the fine channels 4 are provided with micropores 5, and the micropores 5 are connected to adjacent fine channels 4, and are used to guide cooling air to the surface of the blade 1 to form a stable air film cooling layer; through the combination of the arc-shaped fine channels 4 and the micropores 5, an efficient and uniform cooling solution is provided 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 accurately guide the cooling air to the surface of the blade 1, forming a continuous and stable air film cooling layer in a high temperature environment, effectively isolating the high temperature airflow, and significantly reducing the heat load of the blade 1. Such a design not only improves the heat resistance of the blade 1, but also reduces the material damage caused by thermal stress, thereby extending the service life of the blade 1, while ensuring the efficient and stable operation of the gas turbine under extreme working conditions.

[0042] The small channel 4 is arranged along the longitudinal direction and arc shape of the blade 1 and is consistent with the surface structure of the blade 1. The surface of the blade 1 is provided with a plurality of grooves 6 that run from the blade root 2 to the blade tip 3. The blade 1 is also provided with a shock-absorbing boss 7, and the inner wall of the small channel 4 is provided with a plurality of vortex generators 8 that are arranged in a linear manner. Through the longitudinal and arc-shaped arrangement of the small channel 4, the cooling structure can perfectly match the external aerodynamic shape of the blade 1, ensuring that the cooling air is evenly distributed on the entire surface of the blade 1, thereby optimizing the overall heat dissipation effect. The groove 6 design that runs through the blade root 2 to the blade tip 3 further guides the flow of cooling air and improves the heat exchange efficiency. The shock-absorbing boss 7 not only improves the structural stability of the blade 1, but also provides additional cooling capacity through the internal cooling channel 9, significantly reducing the fatigue damage of the blade 1 caused by vibration during high-speed operation. In addition, the linear vortex generator 8 arranged on the inner wall of the channel can generate turbulent airflow, strengthen the heat exchange between the cooling air and the inner wall of the channel, and effectively improve the cooling performance of the blade 1.

[0043] In this embodiment, there is a curved transition between the blade root 2 and the blade tip 3, and the degree of curvature is 15° to 45°. Preferably, the degree of curvature is 30°. The 30° angle achieves an optimal balance between mechanical and aerodynamic performance. The degree of curvature of 30° is sufficient to effectively disperse the stress borne by the blade 1 during operation, reduce local stress concentration, and improve the fatigue resistance of the blade 1. At the same time, through the bending angle of the blade, the airflow can flow more smoothly along the surface of the blade. The setting of this bending angle can effectively avoid the phenomenon of airflow separation. Airflow separation usually leads to irregular airflow and the formation of vortices, thereby increasing the friction and resistance of air flow and causing energy waste. The bending angle can keep the airflow in contact with the surface of the blade, reducing this separation phenomenon.

[0044] In addition, the optimization of the bending angle can also reduce aerodynamic losses. Aerodynamic losses refer to the energy loss caused by friction and uneven flow when the airflow flows on the surface of the blade. Through the bending design, the airflow can flow more smoothly, reducing unnecessary resistance, so that the airflow can more efficiently complete the process of compressing and accelerating the gas.

[0045] Ultimately, this design not only improves the stability and flow efficiency of the airflow, but also improves the efficiency of the entire gas turbine. The airflow is smoother, energy loss is reduced, and the efficiency of the entire system can be improved. This is like optimizing the path of flowing water, allowing water to flow faster and with less effort, thereby improving overall efficiency.

[0046] In this embodiment, the shape of the groove 6 fits the curve of the pressure surface of the blade 1, and the surface roughness of the groove 6 is 20 to 50 microns. Preferably, the surface roughness of the groove 6 is 50 microns. The curved groove 6 that fits the pressure surface of the blade 1 can effectively guide the cooling air to be distributed along the optimized flow path, avoiding the impact and dispersion problems caused by the straight-line injection of the airflow, thereby improving the 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 makes the airflow no longer flow smoothly, but creates turbulence. This turbulence helps the air to better contact the blade surface and can take away more heat.

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

[0048] In addition, by setting a through groove on the blade surface, the stability of the liquid mold cooling layer can be effectively broken, causing the cooling airflow to be disturbed and changing its flow path. In this way, the cooling airflow no longer forms an overly stable liquid film layer on the blade surface, thereby reducing the residence time of the liquid substance on the blade surface. This disturbance can promote a more uniform distribution of the cooling airflow and form a more unstable air film layer on the surface, making it difficult for the liquid to accumulate on the surface.

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

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

[0051] In this embodiment, the air outlet of the micropore 10 is inclined 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. The cooling air can be ejected into the groove 6 at an optimized angle, effectively enhancing the guidance and adhesion of the airflow. The 30° inclination 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 air film cooling layer on the surface of the blade 1. In addition, the design of the gradually shallowing groove 6 can guide the cooling air to gradually diffuse, making the airflow distribution more uniform, and further improving the cooling efficiency.

[0052] In this embodiment, the vortex generator 8 is a protrusion with a deflection angle. By arranging a protrusion structure with a deflection angle in the cooling channel 9, the cooling air flow can be effectively guided and strong turbulence can be formed in a local area. This turbulence increases the contact time and heat exchange 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, shield scales 13 are provided on the inner wall periphery of the small channel 4 and the cooling channel 9 to form a shark skin bionic structure. The microscopic shield scale structure of shark skin has unique surface characteristics and can greatly improve the flow characteristics of the fluid. Simulating this structure on the inner wall of the cooling channel of the blade can effectively reduce the friction resistance between the cooling air and the inner wall of the channel. The microstructure (such as shield scales) on the surface of shark skin can form tiny vortices during the flow process. These vortices help the airflow to maintain higher kinetic energy, reduce the direct contact between the airflow and the channel wall, and thus reduce friction 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 to be more evenly distributed on the surface of the blade, avoiding the situation of local concentration or excessive flow of the airflow, thereby improving the cooling effect.

[0054] The microstructure that imitates shark skin not only effectively reduces the friction resistance of the airflow and improves the stability of the airflow, but also enhances the turbulent characteristics, allowing the cooling air to more efficiently exchange heat with the blade surface, thereby improving the cooling effect and overall working efficiency of the gas turbine.

[0055] In addition, the fish scale scutes and microstructures can increase the thermal conductivity of the fluid, allowing heat to transfer faster from high-temperature areas to low-temperature areas. The fish scale scutes and microstructures increase the total volume of the heat exchange surface, thereby improving heat transfer efficiency.

[0056] In this embodiment, the fine pores 5 are composed of two gradually expanding sections 12 and one gradually contracting section 11, wherein the gradually contracting section 11 is located between the two gradually expanding sections 12. The gradually contracting section 11 is the inner wall of the channel that gradually contracts from the normal diameter of the channel to the middle, forming a contraction section, and the airflow is accelerated in this area. The gradually expanding section 12 is closely received by the contraction section, and the channel gradually expands back to the normal diameter. This expansion section is designed to guide the airflow to decelerate and form a local vortex zone at the same time. The air is forced to flow faster in the gradually contracting section, and the increase in flow rate causes a significant drop in static pressure. The air flow rate in the gradually expanding section slows down, and the static pressure increases to a level higher than the pressure at the inlet, thereby achieving supercharging. The cooperation of the gradually contracting section and the gradually expanding section can achieve efficient supercharging without any mechanical moving parts, which makes the system more reliable and low-maintenance.

[0057] More specifically, the results of the Venturi tube microchannel cooling structure of the present application compared with the fine pores of the prior art straight-through structure can be seen in Figure 6-8 shown.

[0058] The present invention is not limited to the above-mentioned embodiments. Anyone should be aware that any structural changes made under the enlightenment of the present invention, and any technical solutions that are the same or similar to the present invention, fall within the protection scope of the present invention. The technology, shape, and structural parts not described in detail in the present invention are all well-known technologies.

Claims

1. A compressor blade with a venturi microchannel cooling structure, characterized in that: include: The blade (1) comprises a blade root (2) and a blade tip (3), the blade tip (3) being provided with a plurality of arc-shaped fine channels (4) arranged in parallel, the fine channels (4) being provided with fine pores (5), the fine pores (5) being connected to adjacent fine channels (4), and every two adjacent fine channels (4) being connected in series; The fine channels (4) are arranged in the longitudinal direction and in an arc shape of the blade (1) and are consistent with the surface structure of the blade (1). The surface of the blade (1) is provided with a plurality of grooves (6) extending from the blade root (2) to the blade tip (3). The blade (1) is also provided with a plurality of shock-absorbing bosses (7), and the inner wall of the fine channel (4) is provided with a plurality of vortex generators (8) arranged in a linear manner.

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

3. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: The shape of the groove (6) fits the curve of the pressure surface of the blade (1), and the surface roughness of the groove (6) is 20 to 50 microns.

4. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: A transverse cooling channel (9) is arranged inside the shock-absorbing boss (7), and the cooling channel (9) is connected to the fine channel (4). A plurality of micropores (10) are arranged on the surface of the shock-absorbing boss (7), and the micropores (10) are evenly distributed on the boss surface and are connected to the inside of the cooling channel (9).

5. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: The air outlet of the micropore (10) is inclined at 30 degrees 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.

6. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: The vortex generator (8) is a protrusion with a deflection angle.

7. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: Shield scales (13) are arranged on the inner wall periphery of the fine channel (4) and the cooling channel (9) to form a shark skin bionic structure.

8. The compressor blade with a venturi microchannel cooling structure according to claim 1, characterized in that: The fine pores (5) are composed of two gradually expanding sections (12) and a gradually contracting section (11), wherein the gradually contracting section (11) is located between the two gradually expanding sections (12).

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