Micro pipeline provided with anti-aerosol particle deposition bionic tail fin turbulent flow structure and arranged on turbine blade, turbine, aero-engine and gas turbine

Abstract

The invention provides a micro pipeline with an anti-aerosol particle deposition bionic tail fin turbulent flow structure and arranged on turbine blades, a turbine, an aero-engine and a gas turbine, and belongs to the field of power equipment. The problem that a turbulent flow structure on an inner cooling channel of an existing turbine blade cannot restrain particle deposition in the channel is solved. The bionic caudal fin comprises a cooling channel and a plurality of bionic caudal fin turbulent flow structures, each bionic caudal fin turbulent flow structure comprises two sand dune-shaped structures, the two sand dune-shaped structures are fixedly arranged on the upper wall and the lower wall of the cooling channel correspondingly, the two sand dune-shaped structures are arranged correspondingly, and cold air is separated at the front edge when flowing through the bionic caudal fin turbulent flow structures. And the central airflow continues to flow backwards along the surfaces of the bionic tail fin turbulent flow structures, and due to the fact that the flowing area is gradually reduced, the local velocity gradient of the airflow is increased, and the boundary layer is thinned, strong horizontal shear motion is formed between the bionic tail fin turbulent flow structures, and particles are stripped from the wall faces by the airflow. And the deposition of particles can be inhibited.

Description

Technical Field

[0001] The present invention belongs to the technical field of power equipment, and in particular relates to a micro-pipe, a turbine, an aeroengine and a gas turbine which are provided with a bionic tail fin spoiler structure for resisting aerosol particle deposition and are arranged on turbine blades. Background Art

[0002] For aircraft engines and gas turbines that are in long-term service in all weather and all areas, impurities such as sand and dust particles, volcanic ash or salt mist aerosols in the environment are mixed in the air and enter the engine through the air inlet, deposit in the cooling channel inside the blade, and gradually form a certain deposition morphology. The deposition of particles will not only affect the aerodynamic efficiency of the turbine blades, but also change their heat transfer performance, and even directly affect the service life of the turbine blades. Therefore, in order to ensure the safe and reliable operation of the turbine blades under high heat load conditions, it is necessary to design a suitable structure to enhance heat exchange, and at the same time, it should be avoided that a large amount of particles are deposited on the structure to affect the pipeline flow and heat transfer characteristics.

[0003] Relevant researchers have found that the heat transfer performance of the channel under the same Reynolds number increases with the smaller diameter. The arrangement of numerous tiny cooling channels (100μm to 1mm) close to the gas side on the inner wall of the turbine blade improves the heat transfer coefficient on the one hand, and increases the surface area for heat transfer on the other hand, greatly improving the cooling performance of the tiny channels and making the blade cooling more uniform, thereby significantly improving the thermal stress caused by uneven heat transfer in large-scale cooling methods and improving the reliability and service life of the turbine blades.

[0004] However, the existing turbulent structure on the inner cooling channel of the turbine blade cannot suppress the deposition of particles in the channel, thereby preventing a large amount of particles from being deposited in the micro channel or even clogging it, thereby affecting the flow and heat transfer characteristics of the pipeline. Summary of the invention

[0005] In view of this, in order to solve the problem that the turbulence structure on the internal cooling channel of the existing turbine blades cannot suppress the deposition of particles in the channel, thereby preventing the particles from being deposited in large quantities in the micro-channel or even clogging, affecting the flow and heat transfer characteristics of the pipeline, the present invention proposes a micro-pipe, turbine, aircraft engine and gas turbine with an anti-aerosol particle deposition bionic tail fin turbulence structure and arranged on the turbine blade.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

[0007] A micro-duct with a bionic tail fin spoiler structure for resisting aerosol particle deposition and arranged on a turbine blade, comprising:

[0008] Cooling channels;

[0009] Multiple bionic fin spoiler structures, and multiple said bionic fin spoiler structures are arranged at intervals along the extending direction of the cooling channel. The bionic fin spoiler structure includes two dune-shaped structures, and the two dune-shaped structures are respectively fixedly arranged on the upper wall and the lower wall of the cooling channel, and the two dune-shaped structures are arranged correspondingly. When the cold air flows through the bionic fin spoiler structure, it separates at the front edge, and the central air flow continues to flow backward along the surface of the bionic fin spoiler structure. Due to the gradually decreasing flow area, the local velocity gradient of the air flow increases, the boundary layer thins, and a strong horizontal shear motion is formed between the bionic fin spoiler structures, so that the particles are stripped from the wall surface by the air flow.

[0010] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, the planar two-dimensional structure of the dune-shaped structure is formed by the internal tangency of concentric semi-circles and semi-ellipses, and the dune-shaped structure is formed by sweeping the fan-shaped area formed by the vertex of the semi-minor axis of the semi-ellipse and the quadrant point of the semi-circle of its planar two-dimensional structure by 180° along the boundary lines of the circle and the ellipse.

[0011] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, the length of the major axis 2a of the ellipse on the plane t = 0.3 mm, and the length of the minor axis b t = 0.08 mm.

[0012] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, the distance between two adjacent bionic fin spoiler structures is 4 mm.

[0013] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, the cross-section of the cooling channel is rectangular.

[0014] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, the widths of the inlet and the outlet of the cooling channel are both 1.5 mm, and the heights are both 0.2 mm. The equivalent diameter D of the inlet of the cooling channel h = 0.352 mm.

[0015] As a preferred scheme of the above-mentioned microchannel of the turbine blade provided with the bionic fin spoiler structure for anti-aerosol particle deposition, 4 said bionic fin spoiler structures are arranged in every 20 mm length of the cooling channel.

[0016] The present invention also provides a turbine, which includes the above-mentioned microchannels with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades. The number of the microchannels with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades is multiple, and the multiple microchannels with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades are spaced apart and disposed on the turbine blades.

[0017] The present invention further provides an aeroengine, which includes the above-mentioned turbine.

[0018] The present invention also provides a gas turbine, which includes the above-mentioned turbine.

[0019] Compared with the prior art, the beneficial effects of a microchannel with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades, a turbine, an aeroengine and a gas turbine provided by the present invention are as follows:

[0020] The present invention provides a microchannel with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades, a turbine, an aeroengine and a gas turbine. The microchannel with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades can increase the fluid disturbance in the channel. When the gas flows through the area of the bionic fin spoiler structure, due to the reduction of the flow area and the increase of the velocity gradient, a strong horizontal shear motion is formed. At the same time, a transverse secondary flow is generated at the front end of the dune-shaped structure, so that some of the particulate matter mixed in the gas moves towards both sides of the cooling channel when flowing through the bionic fin spoiler structure, and it is more difficult for the particulate matter to adhere and deposit on the channel surface, having a good deposition inhibition effect. In addition, as the gas flow rate at the inlet of the cooling channel increases, the larger particles have higher energy and are not easily deposited due to energy loss caused by collision. At the same time, the flow velocity is relatively large, and it is easier to blow the particles away. The structure of the microchannel with the bionic fin spoiler structure is simple and compact, and can be processed and manufactured by 3D printing method, having good application prospects. Description of the Drawings

[0021] The drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0022] Figure 1 is a schematic structural diagram of a microchannel with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades provided by a specific embodiment of the present invention;

[0023] Figure 2 is a schematic dimension diagram of a dune-shaped structure of a microchannel with the anti-aerosol particle deposition bionic fin spoiler structure and disposed on the turbine blades provided by a specific embodiment of the present invention;

[0024] Figure 3 It is the local deposition rate contour map of particles with different particle sizes at Re = 3000 obtained by numerical simulation in a smooth channel and a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade;

[0025] Figure 4 It is the overall deposition rate result of particles with different particle sizes at Re = 3000 obtained by numerical simulation in a smooth channel and a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade;

[0026] Figure 5 It is the dimensionless velocity contour map and streamline map in a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade obtained by numerical simulation;

[0027] Figure 6 It is the local deposition rate contour map of particles with different particle sizes in two channels at different inlet Reynolds numbers obtained by numerical simulation;

[0028] Figure 7 It is the overall deposition rate result of particles with different particle sizes in two channels at different inlet Reynolds numbers obtained by numerical simulation.

[0029] In the figure:

[0030] 1. Cooling channel; 2. Dune-shaped structure; 3. Inlet. Specific implementation manners

[0031] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. It should be noted that, without conflict, the embodiments and features in the embodiments of the present invention can be combined with each other. The described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments.

[0032] In the description of the present invention, unless otherwise clearly defined and limited, the terms "connected", "connected", and "fixed" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or integrated; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the internal communication of two components or the interaction relationship between two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0033] In the present invention, unless otherwise clearly specified or limited, the first feature being "on" or "under" the second feature may include the direct contact between the first and second features, or may include the situation where the first and second features are not in direct contact but in contact through additional features therebetween. Moreover, the first feature being "above", "over" and "on top of" the second feature includes that the first feature is directly above and obliquely above the second feature, or merely indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature being "under", "beneath" and "underneath" the second feature includes that the first feature is directly below and obliquely below the second feature, or merely indicates that the horizontal height of the first feature is less than that of the second feature.

[0034] In the description of this embodiment, the orientation or positional relationships such as "up", "down", "right" and the like are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of description and simplifying the operation, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present invention. In addition, the terms "first" and "second" are only used for distinction in description and have no special meaning.

[0035] Existing research has found that sharks can effectively control the spatio-temporal structure of the external flow field through various means such as the overall streamline structure, flexible deformation of fins, undulatory oscillation, and body surface scales, and have excellent self-cleaning ability, and impurities are not easy to deposit and grow on their body surfaces. Therefore, without increasing the cold air flow rate, designing a turbulator structure with certain flow heat transfer ability and suppression of particle deposition is of great significance for the safe and stable operation of the blade.

[0036] See Figure 1-7 To illustrate this embodiment, the present invention provides a microchannel, a turbine, an aeroengine and a gas turbine provided with a bionic fin turbulator structure for resisting aerosol particle deposition and arranged on a turbine blade. The microchannel provided with the bionic fin turbulator structure for resisting aerosol particle deposition and arranged on the turbine blade includes a cooling channel 1 and a plurality of bionic fin turbulator structures. The plurality of bionic fin turbulator structures are arranged at intervals along the extending direction of the cooling channel 1. The bionic fin turbulator structure includes two dune-shaped structures 2. The two dune-shaped structures 2 are respectively fixedly arranged on the upper wall and the lower wall of the cooling channel 1, and the two dune-shaped structures 2 are arranged correspondingly. When the cold air flows through the bionic fin turbulator structure, it separates at the front edge, and the central air flow continues to flow backward along the surface of the bionic fin turbulator structure. Since the flow area gradually decreases, the local velocity gradient of the air flow increases, the boundary layer thins, and a strong horizontal shear motion is formed between the bionic fin turbulator structures, so that the particles are stripped from the wall surface by the air flow.

[0037] Optionally, the planar two-dimensional structure of the dune-shaped structure 2 is formed by the inscribed combination of concentric semi-circles and semi-ellipses. The dune-shaped structure 2 is formed by sweeping the fan-shaped area formed by the short semi-axis vertex of the semi-ellipse and the quadrant point of the semi-circle of its planar two-dimensional structure at 180° along the circular and elliptical boundary lines.

[0038] In order to maximize the flow heat transfer characteristics of the microchannels of the turbine blade while reducing the influence of particle deposition, a bionic tail fin spoiler structure that can prevent particle deposition is designed in this embodiment and arranged in the cooling channel 1 of the turbine blade. The bionic tail fin spoiler structure is simplified and designed with reference to the shape of the tail fin of sharks in nature. Compared with a smooth surface, when the cooling gas flows through the cooling channel 1 with the bionic tail fin spoiler structure arranged, it can effectively increase the contact area between the fluid and it, and at the same time break the flow and heat transfer boundary layers, promoting the mixing of hot and cold fluids. At the same time, the reduction of the area of the flow region increases the local velocity gradient of the flow field, increases the local wall shear stress, and makes it easier for particles to peel off the wall, which helps to inhibit particle deposition.

[0039] The bionic fin spoiler structure with anti-aerosol particle deposition is arranged in the microchannel of the turbine blade. The cooling gas enters the cooling channel 1 with the bionic fin spoiler structure from the inlet 3. When it flows through the bionic fin spoiler structure, it separates at the front edge of the bionic fin spoiler structure. The central air flow continues to flow backward along the surface of the bionic fin spoiler structure. Due to the gradually decreasing flow area at the position where the bionic fin spoiler structure is set, the local velocity gradient of the air flow increases, the boundary layer thins, and a strong horizontal shear motion is formed between the bionic fin spoiler structures, enabling the particles to obtain a relatively high relative velocity in the flow field, being easily stripped from the wall by the air flow, and continuing to move forward along the flow direction. The air flows on both sides flow backward along the side edges of the bionic fin spoiler structure and form a low-speed recirculation zone at the rear of the bionic fin spoiler structure. Particles with a smaller particle size (2μm) have better fluidity and are more likely to move with the air flow to the recirculation zone at the trailing edge of the bionic fin spoiler structure. However, due to the lower collision probability between small-sized particles and the wall, the particles are not easily deposited in this area. On the contrary, particles with a diameter greater than 5μm have a larger inertia and are difficult to move with the air flow to the rear of the bionic fin spoiler structure and collide, and it is also difficult for them to deposit in the recirculation zone. It is found by comparison that for medium-sized particles, the deposition rate in the cooling channel 1 with the bionic fin spoiler structure is significantly decreased compared with the original smooth channel. When the particle sizes are 5μm and 10μm, the deposition rates in the cooling channel 1 are decreased by 7.08% and 7.41% respectively based on the smooth channel. Under the condition of a particle size of 10μm, there is no obvious particle deposition near the bionic fin spoiler structure in the cooling channel 1 with the bionic fin spoiler structure, and the particles are deposited in the areas on both sides of the channel. In addition, by changing the flow rate at the inlet 3 to increase the Reynolds number of the gas at the inlet 3, the collision probability between smaller-sized particles and the wall in the cooling channel 1 with the bionic fin spoiler structure increases, so the deposition rate increases compared with the smooth channel, but the overall change range of the deposition rates of the two channels is small. However, for particles with a diameter of 5μm, as the velocity at the inlet 3 continues to increase, the particles will obtain a greater initial kinetic energy and are still difficult to deposit even after multiple collisions, and the particle deposition rates in both channels will decrease. Therefore, as the air flow rate at the inlet 3 increases, the larger particles have higher energy and are not easily deposited due to energy loss caused by collisions. At the same time, the flow velocity is relatively large, making it easier to blow the particles away.

[0040] The structure of the bionic fin spoiler structure with anti-aerosol particle deposition arranged in the microchannel of the turbine blade is simple and compact, and can be processed and manufactured by 3D printing, having good application prospects.

[0041] The numerical simulation boundary conditions for the microchannel of the turbine blade with the bionic fin spoiler structure with anti-aerosol particle deposition provided in this embodiment are: the temperature of the dry air entering the inlet 33 is 700K, the pressure is 2MP, and each wall surface is a non-slip isothermal wall surface, T W= 900K. Numerical simulation is carried out under this condition to obtain Figure 3-Figure 7 , Figure 3 is the local deposition rate contour map of particles with different particle sizes at Re = 3000 in a smooth channel and a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade; Figure 4 is the overall deposition rate result of particles with different particle sizes at Re = 3000 in a smooth channel and a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade; Figure 5 is the dimensionless velocity contour map and streamline map in a microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade obtained by numerical simulation; Figure 6 is the local deposition rate contour map of particles with different particle sizes in two channels at different inlet 3 Reynolds numbers obtained by numerical simulation; Figure 7 is the overall deposition rate result of particles with different particle sizes in two channels at different inlet 3 Reynolds numbers obtained by numerical simulation.

[0042] Optionally, the major axis length 2a of the ellipse on the plane t = 0.3 mm, and the minor axis length b t = 0.08 mm.

[0043] Optionally, the distance between two adjacent bionic fin spoiler structures is 4 mm.

[0044] Optionally, the cross-section of the cooling channel 1 is rectangular.

[0045] Optionally, the widths of the inlet 3 and the outlet of the cooling channel 1 are both 1.5 mm, and the heights are both 0.2 mm.

[0046] Optionally, the equivalent diameter D of the inlet 3 of the cooling channel 1 h = 0.352 mm.

[0047] Optionally, 4 bionic fin spoiler structures are arranged in every 20 mm length of the cooling channel 1.

[0048] The present invention also provides a turbine, including the above-mentioned microchannel with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade. The number of the microchannels with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade is multiple, and the multiple microchannels with an anti-aerosol particle deposition bionic fin spoiler structure arranged on a turbine blade are arranged at intervals on the turbine blade.

[0049] The present invention further provides an aeroengine, including the above-mentioned turbine.

[0050] The present invention also provides a gas turbine, including the above-mentioned turbine.

[0051] Obviously, the embodiments of the present invention disclosed above are only used to help explain the present invention. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and variations can be made. These embodiments are selected and specifically described in this specification in order to better explain the principles and practical applications of the present invention, so that those skilled in the relevant technical field can understand and utilize the present invention well. It is not necessary and impossible to enumerate all the embodiments here.

Claims

1. A microchannel with an anti-aerosol particle deposition bionic fin spoiler structure and disposed on a turbine blade, characterized in that, Comprising: A cooling channel (1); A plurality of bionic fin spoiler structures, which are arranged at intervals along the extending direction of the cooling channel (1). Each bionic fin spoiler structure includes two dune-shaped structures (2), and the two dune-shaped structures (2) are respectively fixedly arranged on the upper wall and the lower wall of the cooling channel (1), and the two dune-shaped structures (2) are arranged correspondingly. When the cold air flows through the bionic fin spoiler structure, it separates at the front edge, and the central air flow continues to flow backward along the surface of the bionic fin spoiler structure. Due to the gradually decreasing flow area, the local velocity gradient of the air flow increases, the boundary layer thins, and a strong horizontal shear motion is formed between the bionic fin spoiler structures, so that the particles are stripped from the wall surface by the air flow.

2. The microchannel with an anti-aerosol particle deposition bionic fin spoiler structure according to claim 1 and disposed on the turbine blade, wherein: The two-dimensional planar structure of the dune-shaped structure (2) is formed by the inscribed circle of a concentric semi-circle and semi-ellipse. The dune-shaped structure (2) is formed by sweeping the sector formed by the vertex of the semi-minor axis of the semi-ellipse and the quadrant point of the semi-circle of its two-dimensional planar structure by 180° along the boundary lines of the circle and the ellipse.

3. The microchannel with an anti-aerosol particle deposition bionic fin spoiler structure as claimed in claim 2 and disposed on a turbine blade, wherein: Among them, the major axis length 2a of the ellipse on the plane t = 0.3 mm, and the minor semi-axis length b t = 0.08 mm.

4. The microchannel of the turbine blade with the bionic fin spoiler structure for anti-aerosol particle deposition as claimed in claim 1, wherein: The distance between two adjacent bionic fin spoiler structures is 4 mm.

5. The microchannel with an anti-aerosol particle deposition bionic fin spoiler structure according to claim 1 and provided on a turbine blade, characterized in that: The cross-section of the cooling channel (1) is rectangular.

6. The microchannel with an anti-aerosol particle deposition bionic fin spoiler structure according to claim 1 and disposed on the turbine blade, wherein: The widths of the inlet (3) and the outlet of the cooling channel (1) are both 1.5 mm, and the heights are both 0.2 mm. The equivalent diameter D of the inlet (3) of the cooling channel (1) h = 0.352 mm.

7. The microchannel with an anti-aerosol particle deposition bionic fin spoiler structure according to claim 1 and disposed on the turbine blade, characterized in that: There are 4 bionic fin spoiler structures arranged in every 20 mm length of the cooling channel (1).

8. A turbine, characterized in that: Comprising the microchannels with bionic fin spoiler structures for anti-aerosol particle deposition as described in any one of claims 1-7 and arranged on the turbine blade. The number of the microchannels with bionic fin spoiler structures for anti-aerosol particle deposition and arranged on the turbine blade is multiple, and the multiple microchannels with bionic fin spoiler structures for anti-aerosol particle deposition and arranged on the turbine blade are arranged at intervals on the turbine blade.

9. An aeroengine, characterized in that: Comprising the turbine as described in claim 8.

10. A gas turbine, characterized in that: Comprising the turbine as described in claim 8.

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