Microchannel topology optimized cooling structure

Abstract

The utility model relates to turbine blade cooling technical field discloses a kind of microchannel topology optimization cooling structure, including the cooling channel being arranged in blade, topologically optimized structure is arranged in cooling channel, cooling airflow enters cooling channel and contacts with topologically optimized structure, then is discharged;Cooling channel includes the first cooling cavity, second cooling cavity, third cooling cavity and fourth cooling cavity being arranged in blade and being communicated with outside, topologically optimized structure is respectively arranged in the first cooling cavity, third cooling cavity and fourth cooling cavity.The utility model improves the heat transfer performance of blade, increases the structural durability of blade, highlights the robustness and practicality of the blade in high-performance thermal mechanical application.

Description

Technical Field

[0001] This utility model relates to the field of turbine blade cooling technology, and in particular to a microchannel topology-optimized cooling structure. Background Technology

[0002] Turbine blades are the most critical components in core power equipment such as gas turbines and aero engines. They typically operate under extreme high temperatures and mechanical stresses, thus requiring advanced cooling structures with efficient cooling and reliable mechanical performance.

[0003] Traditional turbine blade cooling mainly relies on internal and external cooling technologies, such as impact cooling, film cooling, and ribbed channels. However, modern engine turbine blades have extremely high requirements for heat exchange and flow resistance when moving at high speeds, making it difficult to achieve the expected results by relying solely on existing cooling structure designs. This results in low design efficiency and a lack of significant improvement in blade temperature management capabilities, which directly determines the turbine's durability, efficiency, and operational safety.

[0004] Therefore, this invention designs a microchannel topology-optimized cooling structure to solve the above-mentioned technical problems. Utility Model Content

[0005] The purpose of this invention is to provide a microchannel topology-optimized cooling structure to solve the problems existing in the prior art.

[0006] To achieve the above objectives, the present invention provides the following solution: The present invention provides a microchannel topology-optimized cooling structure, including a cooling channel disposed within a blade, wherein a topology-optimized structure is disposed within the cooling channel, and cooling airflow enters the cooling channel and contacts the topology-optimized structure before being discharged.

[0007] The cooling channel includes a first cooling chamber, a second cooling chamber, a third cooling chamber, and a fourth cooling chamber disposed in the blade and connected to the outside. The topology-optimized structure is respectively disposed in the first cooling chamber, the third cooling chamber, and the fourth cooling chamber.

[0008] Preferably, the blade is provided with a twisted, serpentine connecting channel, which is connected to the first cooling chamber, the second cooling chamber and the third cooling chamber respectively.

[0009] Preferably, the cooling channel has a serpentine twist design.

[0010] Preferably, the blade disk at the bottom of the blade is provided with an independent second air inlet channel and a second air outlet channel, which are respectively connected to the fourth cooling chamber.

[0011] Preferably, the impeller is provided with an independent first air intake channel and a first air outlet channel, and the first air intake channel and the first air outlet channel are respectively connected to the connecting channel.

[0012] Preferably, the blade is arranged in an arc shape.

[0013] Preferably, the first cooling chamber, the second cooling chamber, the third cooling chamber, and the fourth cooling chamber are distributed along the leading edge to the trailing edge of the blade.

[0014] Preferably, the topology-optimized structure and the surface design of the cooling airflow are irregular.

[0015] Compared with the prior art, the present invention has the following advantages and technical effects: The present invention discloses a microchannel topology-optimized cooling structure, which allows the cooling airflow to stay inside the blade for a longer time through the serpentine flow channel, increasing the contact time with the high-temperature wall surface and thus increasing the cooling time; during cooling, the cooling airflow flows in from the third and fourth cooling chambers, and the cooling airflow entering the fourth cooling chamber cools the blade and then exits, thus cooling the blade; while the cooling airflow entering the third cooling chamber flows to the first and second cooling chambers, and flows through the blade inside the first and second cooling chambers, performing zoned cooling of different parts of the blade, improving the uniformity of cooling of the blade, and reducing non-uniform deformation caused by thermal stress. The first, third, and fourth cooling chambers through which the cooling airflow passes are designed with topology-optimized structures. These structures reduce ineffective fluid circulation, allowing the cooling airflow to flow more efficiently along the chamber walls. The irregular surfaces of the topology-optimized structures increase the local heat transfer area of ​​the blades, improving heat transfer efficiency. Simultaneously, the topology-optimized structures generate asymmetric disturbances in the cooling fluid, promoting the transition from laminar to turbulent flow, increasing the convective heat transfer coefficient, improving the blade's heat transfer efficiency, and reducing the blade temperature, thus mitigating the impact of excessively high blade temperature on operational efficiency. Furthermore, the topology-optimized structures within the first, third, and fourth cooling chambers strengthen the blade's structural strength between the cavities, extending the structural lifespan.

[0016] This invention improves the heat transfer performance of the blade, increases its structural durability, and highlights its robustness and practicality in high-performance thermomechanical applications. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort. In the drawings:

[0018] Figure 1 This is a schematic diagram of the blade with a microchannel topology-optimized cooling structure according to this utility model;

[0019] Figure 2 This is a frontal sectional view of the blade of this utility model;

[0020] In the diagram: 1. Blade; 2. Topology-optimized structure; 3. Cooling channel; 4. First cooling chamber; 5. Second cooling chamber; 6. Third cooling chamber; 7. Fourth cooling chamber. Detailed Implementation

[0021] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0022] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0023] Reference Figures 1 to 2 As shown, this embodiment provides a microchannel topology-optimized cooling structure, including a cooling channel 3 disposed in a blade 1, a topology-optimized structure 2 disposed in the cooling channel 3, a cooling airflow entering the cooling channel 3 and contacting the topology-optimized structure 2, and then exiting;

[0024] The cooling channel 3 includes a first cooling chamber 4, a second cooling chamber 5, a third cooling chamber 6 and a fourth cooling chamber 7 disposed in the blade 1 and connected to the outside. The first cooling chamber 4, the third cooling chamber 6 and the fourth cooling chamber 7 are respectively provided with topology optimization structures 2.

[0025] This invention discloses a microchannel topology-optimized cooling structure. The serpentine flow channel allows the cooling airflow to stay inside the blade 1 for a longer time, increasing the contact time with the high-temperature wall surface and thus increasing the cooling time. During cooling, the cooling airflow flows in from the third cooling chamber 6 and the fourth cooling chamber 7. The cooling airflow entering the fourth cooling chamber 7 cools the blade 1 and then exits, thus cooling the blade 1. Meanwhile, the cooling airflow entering the third cooling chamber 6 flows to the first cooling chamber 4 and the second cooling chamber 5, passing through the interior of the blade 1 along the first cooling chamber 4 and the second cooling chamber 5, and performing zoned cooling on different parts of the blade 1, improving the uniformity of cooling the blade 1 and reducing non-uniform deformation caused by thermal stress. The first cooling chamber 4, the third cooling chamber 6, and the fourth cooling chamber 7 through which the cooling airflow flows are designed with topology-optimized structures 2. This reduces ineffective fluid circulation of the cooling airflow, allowing the cooling airflow to flow more efficiently along the walls of the cooling chambers. The irregular surface of the topology-optimized structure 2 increases the local heat transfer area of ​​the blade 1, improving heat transfer efficiency. Simultaneously, the topology-optimized structure 2 generates asymmetric disturbances to the cooling fluid, promoting the transition of the cooling airflow from laminar to turbulent flow, increasing the convective heat transfer coefficient, improving the heat transfer efficiency of the blade 1, and reducing the temperature of the blade 1, thus mitigating the impact of excessively high blade 1 temperature on operating efficiency. Furthermore, the topology-optimized structure 2, located in the first cooling chamber 4, the third cooling chamber 6, and the fourth cooling chamber 7, strengthens the structural strength of the blade 1 between the cavities, extending the structural service life. This invention improves the heat transfer performance of the blade 1, increases its structural durability, and highlights its robustness and practicality in high-performance thermomechanical applications.

[0026] Further optimization involves incorporating a serpentine connecting channel within blade 1, which connects to the first cooling chamber 4, the second cooling chamber 5, and the third cooling chamber 6. This serpentine design alters the airflow path within blade 1, allowing for more thorough contact between the cooling airflow and all parts of blade 1. Simultaneously, during blade 1 cooling, external cooling airflow first enters the connecting channel and then the third cooling chamber 6 to cool blade 1. The cooling airflow from the third cooling chamber 6 then re-enters the first and second cooling chambers 4 and 5 via the connecting channel, further altering the airflow path within blade 1 and ensuring more complete contact between the cooling airflow and all parts of blade 1. This allows for zoned cooling of different parts of blade 1, improving the uniformity of cooling and reducing non-uniform deformation caused by thermal stress.

[0027] Further optimization of the design involves a serpentine twisting design for cooling channel 3. The first cooling chamber 4, second cooling chamber 5, third cooling chamber 6, and fourth cooling chamber 7 of cooling channel 3 are all designed in a serpentine shape, extending the flow path of the cooling airflow within the channel. Simultaneously, the serpentine cooling channel 3 also creates irregular turbulence in the cooling airflow, accelerating the heat exchange rate with the walls of cooling channel 3 and improving the cooling efficiency inside blade 1.

[0028] Further optimization involves installing independent second intake and second exhaust channels on the blade disk at the bottom of blade 1, both of which are connected to the fourth cooling chamber 7. The blade disk also features independent first intake and first exhaust channels, which are connected to connecting channels. These channels are independently arranged within the blade disk, with the second intake and exhaust channels connected to the fourth cooling chamber 7, forming independent cooling airflow paths. This ensures sufficient and smooth cooling airflow to the fourth cooling chamber 7, guaranteeing stable supply and discharge of cooling airflow in this area. It also prevents interference between airflows from different cooling chambers, optimizing the overall cooling system's stability and enabling better zoned cooling of different parts of blade 1. The first intake channel and the first exhaust channel are connected to the serpentine connecting channel, which in turn connects to the first cooling chamber 4, the second cooling chamber 5, and the third cooling chamber 6, respectively. During cooling, the external cooling airflow enters the connecting channel through the first intake channel, and the cooling airflow in the connecting channel enters the first cooling chamber 4, the second cooling chamber 5, and the third cooling chamber 6 to reach different positions of the blade 1, cooling different areas of the blade 1. The cooling airflow after cooling the blade 1 flows back into the connecting channel and is discharged through the first exhaust channel, forming a circulation channel for the cooling airflow. This ensures the stability and continuity of the airflow in the connecting channel, making it easier to control the cooling airflow in the connecting channel. Combined with other channel structures, the flow and distribution of the cooling airflow in the blade 1 can be more precisely adjusted, optimizing cooling and structural performance.

[0029] Further optimization of the design resulted in an arc-shaped blade 1. The arc-shaped blade 1 is designed to fit the actual working environment of the turbine blade 1 and adapt to the aerodynamic characteristics. At the same time, it provides reasonable space for the internal cooling channel 3 and structural layout, which helps to improve the overall performance of the blade 1 and ensure the mechanical stability of the blade 1 under extreme conditions. The arc-shaped blade 1, together with the internal cooling structure, enhances the overall reliability, allowing the cooling channel 3 and topology to fully cover the critical areas of the blade 1 and avoid cooling blind spots.

[0030] Further optimization of the design involves distributing the first cooling chamber 4, the second cooling chamber 5, the third cooling chamber 6, and the fourth cooling chamber 7 along the leading edge to the trailing edge of the blade 1. This distribution ensures that the cooling chambers cover the critical paths of the high-temperature region of the blade 1, guaranteeing complete cooling coverage from the intake side to the exhaust side. This avoids localized high-temperature concentration, achieves orderly cooling of the entire blade 1, optimizes the temperature field distribution, reduces thermal stress, minimizes non-uniform deformation caused by thermal stress, and improves the temperature management capability of the blade 1.

[0031] Further optimization involves designing the surface of the topology-optimized structure 2 and the cooling airflow as an irregular shape. This irregular shape at the contact surface generates asymmetric disturbances in the cooling airflow, promoting the transition from laminar to turbulent flow. The turbulent state significantly improves the convective heat transfer coefficient, enhancing the cooling effect. Simultaneously, it increases the actual heat transfer area, reduces ineffective fluid circulation, and improves cooling efficiency.

[0032] In the description of this utility model, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model 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. Therefore, they should not be construed as limitations on this utility model.

[0033] The embodiments described above are merely preferred embodiments of the present utility model and are not intended to limit the scope of the present utility model. Various modifications and improvements made to the technical solutions of the present utility model by those skilled in the art without departing from the spirit of the present utility model should fall within the protection scope defined by the claims of the present utility model.

Claims

1. A microchannel topology-optimized cooling structure, characterized in that: It includes a cooling channel (3) disposed in the blade (1), wherein a topology optimization structure (2) is disposed in the cooling channel (3), and the cooling airflow enters the cooling channel (3) and contacts the topology optimization structure (2) and then exits; The cooling channel (3) includes a first cooling chamber (4), a second cooling chamber (5), a third cooling chamber (6) and a fourth cooling chamber (7) disposed in the blade (1) and connected to the outside. The topology optimization structure (2) is respectively disposed in the first cooling chamber (4), the third cooling chamber (6) and the fourth cooling chamber (7).

2. The microchannel topology-optimized cooling structure according to claim 1, characterized in that: The blade (1) is provided with a twisted serpentine connecting channel, which is connected to the first cooling chamber (4), the second cooling chamber (5) and the third cooling chamber (6) respectively.

3. The microchannel topology-optimized cooling structure according to claim 1, characterized in that: The cooling channel (3) has a serpentine twist design.

4. The microchannel topology-optimized cooling structure according to claim 2, characterized in that: The blade (1) has an independent second air intake channel and a second air outlet channel on the blade disk at the bottom end. The second air intake channel and the second air outlet channel are respectively connected to the fourth cooling chamber (7).

5. The microchannel topology-optimized cooling structure according to claim 4, characterized in that: The impeller is provided with an independent first air intake channel and a first air outlet channel, which are respectively connected to the connecting channel.

6. The microchannel topology-optimized cooling structure according to claim 1, characterized in that: The blade (1) is arranged in an arc shape.

7. The microchannel topology-optimized cooling structure according to claim 1, characterized in that: The first cooling chamber (4), the second cooling chamber (5), the third cooling chamber (6) and the fourth cooling chamber (7) are distributed along the leading edge to the trailing edge of the blade (1).

8. The microchannel topology-optimized cooling structure according to claim 1, characterized in that: The topology optimization structure (2) and the surface design of the cooling airflow are irregular.

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