Variable geometry turbine guide vane and intelligent control method thereof

Abstract

The application belongs to the technical field of engines, and specifically discloses a variable-geometry turbine guide vane and an intelligent control method thereof. The variable-geometry turbine guide vane comprises an inner edge plate, an outer edge plate, a blade assembly and a driving assembly. The inner edge plate and the outer edge plate are annular. The outer edge plate is arranged at the circumferential outer portion of the inner edge plate. A flow-through space is formed between the outer edge plate and the inner edge plate. A plurality of blade assemblies are arranged in the flow-through space at intervals in the circumferential direction. The blade assembly comprises a fixed blade and a movable blade. The fixed blade and the movable blade are arranged in the circumferential direction and the axial direction of the flow-through space in sequence. The outer circumferential wall of the inner edge plate is provided with a first sliding groove. The inner circumferential wall of the outer edge plate is provided with a second sliding groove. The two ends of the movable blade are arranged in the first sliding groove and the second sliding groove, respectively. The driving assembly is arranged on the outer edge plate and connected with the plurality of blade assemblies, respectively. The first sliding groove and the second sliding groove are matched with a preset track. The application reduces the leakage loss on the basis of realizing accurate change of the turbine flow-through capacity, and improves the working efficiency of the turbine.

Description

Technical Field

[0001] This invention belongs to the field of engine technology, specifically relating to a variable geometry turbine guide and its intelligent control method. Background Technology

[0002] Variable geometry turbine guide vanes alter the flow rate through the guide vane by changing the turbine blade opening, thus varying the turbine's flow capacity. However, existing variable geometry turbine guide vanes still suffer from several technical drawbacks: First, the large assembly clearance between the blades and the inner and outer edge plates leads to significant airflow leakage losses under high pressure ratio conditions, severely impacting aerodynamic efficiency. Second, the insufficient flow area of ​​the cold air passage results in low cooling efficiency, making it difficult to meet the heat dissipation requirements under high-temperature conditions. Furthermore, traditional control methods suffer from significant hysteresis, leading to insufficient response performance under transient conditions and hindering precise flow regulation. Summary of the Invention

[0003] This invention aims to at least partially address one of the technical problems in related art. To this end, embodiments of the invention propose a variable geometry turbine guide that can reduce leakage losses.

[0004] This invention also proposes an intelligent control method for a variable geometry turbine guide.

[0005] The variable geometry turbine guide of this invention includes an inner edge plate, an outer edge plate, multiple blade assemblies, and a drive assembly. Both the inner and outer edge plates are annular. The outer edge plate is disposed circumferentially outside the inner edge plate, forming an annular flow space between them. Multiple blade assemblies are circumferentially spaced within the flow space. Each blade assembly includes a fixed blade and a movable blade, arranged sequentially along the circumferential and axial directions of the flow space. The outer peripheral wall of the inner edge plate has a first groove, and the inner peripheral wall of the outer edge plate has a second groove. The two ends of the movable blade are respectively disposed within the first groove and the second groove. The drive assembly is disposed on the outer edge plate and connected to the multiple blade assemblies to drive the movable blade to slide along a preset trajectory. Both the first groove and the second groove match the preset trajectory.

[0006] It is understandable that by forming a flow channel between adjacent blade assemblies to guide the airflow, the drive assembly can drive the movable blades to slide, thereby changing the flow cross-section of the flow channel through the movement of the movable blades, thus regulating the airflow rate. The inner and outer edge plates are respectively provided with a first groove and a second groove corresponding to the movable blades, which allows the movable blades to slide close to the bottom walls of the first groove and the second groove. No gaps are formed between the movable blades and the inner peripheral wall of the outer edge plate, or between the movable blades and the outer peripheral wall of the inner edge plate, which is conducive to the airflow bypassing the movable blades and passing through the flow channel, thereby reducing flow loss.

[0007] In this embodiment, in the direction of airflow, the fixed blade is located upstream and the movable blade is located downstream. The flow space is divided into an upstream section and a downstream section corresponding to the fixed blade and the movable blade. The inner edge plate and the outer edge plate of the upstream section gradually move away from each other, and the inner edge plate and the outer edge plate of the downstream section are parallel to each other.

[0008] In this embodiment, the leading edge of the movable blade has a negative angle of attack α, where α is 3° to 5°.

[0009] In this embodiment, the driving assembly includes a driving ring and linkage components. The driving ring is spaced apart on the outer periphery of the outer edge plate and is used to connect with an external driving component to drive the drive component to rotate around the axis of the driving ring within a preset range. Multiple linkage components are provided, and the multiple linkage components are arranged sequentially along the circumference of the driving ring. The input end of each linkage component is connected to the driving ring, and the output end of the linkage component is connected to the movable blade.

[0010] In this embodiment, the linkage component includes a linkage rod. One end of the linkage rod is rotatably connected to the outer edge plate via a first shaft, and the other end is connected to the drive ring via a second shaft. The drive ring is used to drive the linkage rod to rotate around the first shaft within a preset angle range. The middle part of the linkage rod is connected to the movable blade via a third shaft, and the outer edge plate is provided with a clearance hole corresponding to the third shaft.

[0011] In this embodiment, the linkage component further includes a sealing plate, and the outer peripheral wall of the outer edge plate is provided with a third sliding groove. The sealing plate is slidably disposed in the third sliding groove, and the third shaft passes through the sealing plate.

[0012] In this embodiment, the preset angle range is -9° to 6°.

[0013] In this embodiment, along the axial direction of the flow space, the total length of the fixed blade and the movable blade of a set of blade assemblies is Δx1, the overlap distance between the movable blade and the fixed blade of the set of blade assemblies is Δx2, and the overlap AO = Δx2 / Δx1 = 0% to 5%.

[0014] In this embodiment, in the circumferential direction of the flow space, in two adjacent sets of the blade assemblies, the distance between the leading edge of one set of fixed blades and the leading edge of another set of fixed blades is s, and the distance between the leading edge of one set of movable blades and the trailing edge of another set of fixed blades is t, with an intercept ratio PP = t / s = 90% to 95%.

[0015] In this embodiment, a cooling airflow channel is provided inside the movable blade, and air film holes communicating with the cooling airflow channel are provided on the end face and side wall of the movable blade.

[0016] In this embodiment, both the movable blade and the fixed blade are bent-twisted blades.

[0017] In this embodiment, the inner edge plate adopts a non-axisymmetric end wall shape to reduce airflow loss.

[0018] The control method for the variable geometry turbine guide in this embodiment includes the following steps: predicting the optimal angle information of the moving blade and the predicted flow rate of the turbine; calculating the actual flow rate of the turbine based on the optimal angle information; calculating the deviation between the actual flow rate of the turbine and the predicted flow rate; if the deviation is within a preset range, the optimal angle information meets the requirements; if the deviation is greater than or less than the preset range, the optimal angle information is adjusted. Attached Figure Description

[0019] Figure 1 This is a partial structural diagram of the movable blade of the variable geometry turbine guide in the initial position according to Embodiment 1 of the present invention.

[0020] Figure 2 This is a partial structural schematic diagram of the movable blade of the variable geometry turbine guide in the first extreme position according to Embodiment 1 of the present invention.

[0021] Figure 3 This is a partial structural schematic diagram of the movable blade of the variable geometry turbine guide in the second extreme position according to Embodiment 1 of the present invention.

[0022] Figure 4 This is a partial structural schematic diagram of the variable geometry turbine guide of Embodiment 1 of the present invention from another perspective.

[0023] Figure 5 This is a partial exploded view of the variable geometry turbine guide of Embodiment 1 of the present invention.

[0024] Figure 6 This is a schematic diagram of the inner edge plate and blade assembly according to Embodiment 1 of the present invention.

[0025] Figure 7 This is a schematic diagram of the outer edge plate and the sealing plate of Embodiment 1 of the present invention.

[0026] Figure 8 This is a schematic diagram of the internal cooling airflow channel layout of the active blade in Embodiment 1 of the present invention.

[0027] Figure 9 This is a schematic diagram of the structure of the active blade of Embodiment 1 of the present invention, which adopts a bent and twisted blade design.

[0028] Figure 10 This is a schematic diagram of the structure of the inner edge plate of Embodiment 1 of the present invention, which adopts a non-axisymmetric end wall shape.

[0029] Figure 11 This is a schematic diagram of the distribution structure of the blade assembly according to Embodiment 1 of the present invention.

[0030] Figure 12 This is a flowchart of the intelligent control method for a variable geometry turbine guide according to Embodiment 1 of the present invention.

[0031] Figure 13 This is a partial structural schematic diagram of the variable geometry turbine guide of Embodiment 2 of the present invention.

[0032] Figure label:

[0033] 1. Outer edge plate; 2. Inner edge plate; 3. Fixed blade; 4. Movable blade; 5. Guide channel; 6. Sealing plate; 7. Linkage rod; 8. First shaft; 9. Second shaft; 10. Drive ring; 11. Third shaft; 12. Third slide groove; 13. Air film hole; 14. First slide groove; 15. Second slide groove; 16. Upstream section; 17. Downstream section; 18. First extreme position; 19. Second extreme position; 20. Axis of the first shaft; 21. Intermediate blade; 22. Fourth shaft; 23. Rocker arm. Detailed Implementation

[0034] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0035] Example 1

[0036] In this embodiment, as Figures 1 to 7As shown, the variable geometry turbine guide includes an inner edge plate 2, an outer edge plate 1, multiple blade assemblies, and a drive assembly. Both the inner edge plate 2 and the outer edge plate 1 are annular. The outer edge plate 1 is disposed outside the circumference of the inner edge plate 2, and an annular flow space is formed between the outer edge plate 1 and the inner edge plate 2. Multiple blade assemblies are circumferentially spaced within the flow space. Each blade assembly includes a fixed blade 3 and a movable blade 4. The fixed blade 3 and the movable blade 4 are arranged sequentially along the circumference and axial direction of the flow space. The outer peripheral wall of the inner edge plate 2 is provided with a first groove 14, and the inner peripheral wall of the outer edge plate 1 is provided with a second groove 15. The two ends of the movable blade 4 are respectively disposed in the first groove 14 and the second groove 15. The drive assembly is disposed on the outer edge plate 1 and connected to the multiple blade assemblies to drive the movable blade 4 to slide along a preset trajectory. The first groove 14 and the second groove 15 are both matched with the preset trajectory.

[0037] Specifically, such as Figure 1 As shown, airflow guide channels 5 are formed between two adjacent sets of blade assemblies. Multiple airflow guide channels 5 formed by multiple blade assemblies guide the airflow into the turbine blades at a specific angle and speed to improve the turbine's working efficiency and performance.

[0038] It is understandable that by forming a flow channel 5 between adjacent blade assemblies to guide the airflow, the drive assembly can drive the movable blade 4 to slide, thereby changing the flow cross section of the flow channel 5 through the movement of the movable blade 4, thus regulating the airflow. The inner edge plate 2 and the outer edge plate 1 are respectively provided with a first groove 14 and a second groove 15 corresponding to the movable blade 4, so that the movable blade 4 can slide close to the bottom wall of the first groove and the bottom wall of the second groove. No gaps are formed between the movable blade 4 and the inner peripheral wall of the outer edge plate 1, and between the movable blade 4 and the outer peripheral wall of the inner edge plate 2, which is conducive to the airflow bypassing the movable blade 4 and passing through the flow channel 5, thereby reducing flow loss.

[0039] In this embodiment, as Figure 4 In the airflow direction, the fixed blade 3 is located upstream and the movable blade 4 is located downstream. The flow space is divided into an upstream section 16 and a downstream section 17 corresponding to the fixed blade 3 and the movable blade 4. The inner edge plate 2 and the outer edge plate 1 of the upstream section 16 gradually move away from each other, while the inner edge plate 2 and the outer edge plate 1 of the downstream section 17 are parallel to each other.

[0040] Specifically, at the junction of the upstream section 16 and the downstream section 17, both the inner edge plate 2 and the outer edge plate 1 are in a smooth transition, which is conducive to the smooth passage of airflow and reduces flow loss.

[0041] Understandably, in the upstream section 16, the gradual expansion of the flow space reduces sudden changes in airflow as it enters the guide vane from the combustion chamber, avoiding the generation of violent shock waves and turbulence. This helps reduce energy loss and allows the airflow to enter more smoothly. In the downstream section 17, the inner edge plate 2 and the outer edge plate 1 are parallel to each other, allowing the end face of the movable blade 4 to be in close contact with the inner walls of the first and second slide grooves, thereby helping to reduce airflow loss.

[0042] In this embodiment, the leading edge of the movable blade 4 has a negative angle of attack α, where α is 3° to 5°.

[0043] For example, the negative angle of attack α can be 3°, 3.5°, 4°, 4.5°, or 5°. If the negative angle of attack is too large or too small, it can easily cause airflow separation, which is not conducive to reducing airflow loss.

[0044] Understandably, setting a negative angle of attack of 3° to 5° at the leading edge of the movable blade 4 can reduce the direct impact of the airflow when entering the movable blade 4, allowing the airflow to transition more smoothly to the surface of the movable blade 4. This helps reduce energy loss, improve aerodynamic efficiency, and also helps to keep the airflow close to the surface of the movable blade 4, reducing airflow separation, thus allowing the airflow to pass through more smoothly and improving overall performance.

[0045] In this embodiment, as Figure 4 and Figure 5 As shown, the drive assembly includes a drive ring 10 and linkage components. The drive ring is spaced apart on the circumferential outside of the outer edge plate 1. Multiple linkage components are provided, and the multiple linkage components are arranged sequentially along the circumference of the drive ring. The input end of each linkage component is connected to the drive ring 10, and the output end of the linkage component is connected to the movable blade 4.

[0046] Specifically, the drive ring is connected to an external drive component, which drives the drive ring to rotate within a preset range around its axis. The specific structure of the drive component is conventional prior art and will not be described in detail here.

[0047] It is understandable that when an external driving component pushes the driving ring to rotate, the driving ring can drive the movable blades 4 to slide along a preset trajectory through the linkage component. The linkage component can link all the movable blades 4, so that all the movable blades 4 can be driven to move by the same driving component, which helps to simplify the overall structure and make the overall structure more compact.

[0048] In this embodiment, as Figure 4 and Figure 5As shown, the linkage component includes a linkage rod 7. One end of the linkage rod 7 is rotatably connected to the outer edge plate 1 via a first shaft 8, and the other end is connected to the drive ring via a second shaft 9. The drive ring is used to drive the linkage rod 7 to rotate around the first shaft 8 within a preset angle range. The middle part of the linkage rod 7 is connected to the movable blade 4 via a third shaft 11. An avoidance hole is provided on the outer edge plate 1 corresponding to the third shaft 11.

[0049] Specifically, a first shaft 8 is provided on the outer circumferential surface of the outer edge plate 1, and one end of the linkage rod 7 is rotatably connected to the first shaft 8. A second shaft 9 is provided at the end of the linkage rod 7 opposite to the first shaft 8, and the second shaft 9 is connected to the drive ring. One end of a third shaft 11 is connected to the middle of the linkage rod 7, and the other end passes through a clearance hole and is connected to the end face of the movable blade 4 facing the outer edge plate 1. For example, two third shafts 11 can be provided, and the two third shafts 11 are spaced apart on both sides of the linkage rod 7 along the moving direction of the linkage rod 7, and the outer edge plate 1 is provided with clearance holes corresponding to the two third shafts 11. In detail, the shape of the clearance hole matches the movement trajectory of the third shaft 11 to avoid interference of the clearance hole with the movement of the third shaft 11 and thus affecting the movement of the movable blade 4.

[0050] It should be noted that, since the drive ring drives the linkage rod 7 to rotate around the first axis 8 within a preset angle range, the motion trajectory of the third axis 11 connected to the linkage rod 7 is a semi-circular arc, thereby driving the movable blade 4 to form a semi-circular arc motion trajectory through the third axis 11. Figure 11 As shown in the figure, d represents the throat width of the guide channel 5. When the movable blade 4 slides upstream along the slide rail, the throat width d increases; when it slides downstream, the throat area decreases. This variable geometry turbine guide adjusts the turbine's work capacity by limiting the throat's flow capacity, thereby improving the engine's efficiency under different operating conditions.

[0051] In this embodiment, as Figure 4 and Figure 5 As shown, the linkage component also includes a sealing plate 6. The outer peripheral wall of the outer edge plate 1 is provided with a third sliding groove 12. The sealing plate 6 is slidably disposed in the third sliding groove 12, and the third shaft 11 passes through the sealing plate 6.

[0052] Specifically, a third groove is provided on the outer peripheral wall of the outer edge plate 1 corresponding to each movable blade 4, so that a sealing plate 6 can be installed in each third groove.

[0053] It is understandable that when the third shaft 11 moves, a clearance hole needs to be set on the corresponding outer edge plate 1. However, the airflow in the flow space will flow out through the clearance hole. By setting a sealing plate 6 that moves with the third shaft 11, it will not affect the movement of the moving blade 4 driven by the third shaft 11, and the sealing plate 6 can block the clearance hole, reducing the airflow in the flow space from the clearance hole, thereby helping to reduce flow loss.

[0054] In this embodiment, the preset angle range is -9° to 6°.

[0055] For example, the movable blade 4 can rotate around the first axis 8 at -9°, -5°, -3°, 1°, 0°, 2°, 4° or 6°, etc. The specific rotation angle of the movable blade 4 can be set according to actual needs and is not limited here.

[0056] It should be noted that, as Figure 11 As shown, the movable blade 4 has a first limit position 18 and a second limit position 19. At the first limit position 18, the movable blade 4 rotates upstream by +6°, and the throat width is at its maximum. At the second limit position 19, the movable blade 4 rotates downstream by -9°, and the throat width d is at its minimum. This preset angle range can achieve a flow control capability of 70% to 120% while ensuring that the efficiency does not decrease significantly. Furthermore, the relative position of the limit position and the initial position of the movable blade 4 will change depending on the position of the axis 20 of the first shaft. When selecting the setting position of the first shaft 8, a position that minimizes the size of the first and second chutes can be selected to reduce flow loss.

[0057] In this embodiment, as Figure 11 As shown, in the axial direction of the flow space, the total length of the fixed blade 3 and the movable blade 4 of a set of blades is Δx1, and the overlap distance between the movable blade 4 and the fixed blade 3 of the set of blades is Δx2. The overlap AO = Δx2 / Δx1 = 0%~5%.

[0058] For example, AO can be set to 0%, 1%, 2%, 3%, 4%, or 5%, etc. If the moving blade 4 and the fixed blade 3 do not overlap, airflow leakage will occur, increasing energy loss. If the overlap A0 is too large, it will not be conducive to reducing energy loss.

[0059] Understandably, by setting the overlap AO to 0%–5%, the overlap between the fixed blade 3 and the movable blade 4 can effectively reduce airflow leakage between adjacent blades, helping to maintain flow within the airflow guide channel 5 and reducing energy loss. Furthermore, it allows for a smooth transition of airflow from upstream to downstream, reducing turbulence and unevenness in the airflow, enabling more continuous airflow guidance and reducing the likelihood of airflow separation.

[0060] In this embodiment, as Figure 11 As shown, in the circumferential direction of the flow space, in two adjacent sets of blade assemblies, the distance between the leading edge of one set of fixed blades 3 and the leading edge of another set of fixed blades 3 is s, and the distance between the leading edge of one set of movable blades 4 and the trailing edge of another set of fixed blades 3 is t. The intercept ratio PP = t / s = 90%~95%.

[0061] For example, the intercept ratio (PP) can be 90%, 91%, 92%, 93%, 94%, or 95%, etc. If the intercept ratio (PP) is too large, it may cause the airflow to accelerate rapidly upstream, increasing impact and friction losses. If the intercept ratio (PP) is too small, it may cause an uneven transition between upstream and downstream airflow, increasing the risk of airflow separation and hindering the reduction of energy loss.

[0062] Understandably, by setting the intercept ratio PP to 90%–95%, the airflow can be gradually accelerated as it enters the guide channel 5, ensuring a more uniform airflow distribution into the turbine, which helps improve turbine efficiency. It also reduces sudden changes in airflow between upstream and downstream, minimizing airflow separation.

[0063] In this embodiment, as Figure 5 and Figure 8 , Figure 9 As shown, a cooling airflow channel is provided inside the movable blade 4, and air film holes 13 communicating with the cooling airflow channel are provided on the end face and side wall of the movable blade 4.

[0064] Specifically, the third shaft 11 is axially provided with an air intake channel communicating with the cooling airflow channel, so as to deliver cooling gas to the cooling airflow channel through the air intake channel. When each movable blade 4 is connected to two third shafts 11, each third shaft 11 is provided with an air intake channel, and a cooling airflow channel is provided for each movable blade 4 corresponding to its air intake channel, so as to improve the cooling effect on the movable blade 4. The cooling channels are distributed in a serpentine pattern to improve the cooling effect.

[0065] It is understandable that by setting a cooling airflow channel on the movable blade 4, and by supplying cooling airflow into the cooling airflow channel, the cooling airflow is ejected through the air film hole 13 after passing through the cooling airflow channel. At the same time, the movable blade 4 can be cooled, and the airflow leakage between the movable blade 4 and the outer edge plate 1 can be reduced by spraying air into the end of the movable blade 4.

[0066] In this embodiment, as Figure 9 As shown, both the movable blade 4 and the fixed blade 3 are bent and twisted blades. By bending and twisting the blades, the fluid flow state and pressure distribution on both sides of the blades are changed to reduce bottom leakage loss.

[0067] In this embodiment, as Figure 10As shown, the inner edge plate adopts a non-axisymmetric endwall design to reduce airflow loss. Specifically, the inner peripheral wall of the outer edge plate 1 in the circumferential direction of the first slide groove is provided with a first curved surface that smoothly transitions to the first slide groove. The pressure difference on both sides of the movable blade 4 is adjusted by setting the first curved surface. Similarly, the outer peripheral wall of the inner edge plate 2 in the circumferential direction of the second slide groove is provided with a second curved surface. The pressure difference on both sides of the movable blade 4 is adjusted by setting the second curved surface. By reducing the pressure difference on both sides of the movable blade 4, the flow loss is reduced. Specifically, the specific shapes of the first and second curved surfaces will change according to the actual application scenario. Those skilled in the art can set them according to actual needs, so no limitation is made here.

[0068] The intelligent control method for the variable geometry turbine guide in this embodiment includes the following steps:

[0069] S100 predicts the optimal angle information for the moving blades and the predicted flow rate of the turbine.

[0070] S200 calculates the actual flow rate of the turbine based on the optimal angle information;

[0071] S300 calculates the deviation between the actual flow rate and the predicted flow rate of the turbine.

[0072] S400: Determine if the deviation is within the preset range. If the deviation is within the preset range, the optimal angle information meets the requirements. If the deviation is greater than or less than the preset range, adjust the optimal angle information.

[0073] Specifically, the control of the movable blades works collaboratively through a deep learning-based open-loop and closed-loop control program, with deep learning technology permeating the entire control process. Specifically, such as... Figure 12 As shown, the open-loop control module and the closed-loop control module respectively utilize deep reinforcement learning and deep regression neural networks to achieve precise adjustment of the active blade 4.

[0074] The open-loop control module employs a deep reinforcement learning algorithm. This algorithm searches data from the operating characteristic maps of the engine compressor, turbine, combustion chamber, and other components to find the optimal angle information for the movable blade 4. The neural network model of the deep reinforcement learning algorithm is pre-trained using a large amount of simulation data. During the training phase, a proximal strategy is used to optimize the deep reinforcement learning algorithm, continuously adjusting network weights to improve prediction accuracy. Ultimately, it predicts the optimal angle information of the movable blade 4 based on the input engine operating state and uses this optimal angle information as the input value for the closed-loop control program. Due to the time lag in the engine's dynamic response, there may be a deviation between the actual flow rate and the predicted flow rate of the turbine. Therefore, the closed-loop control module needs to perform real-time correction. The closed-loop control module uses a deep regression neural network to process the flow deviation in real time and accurately adjust the rotation angle of the movable blade. The inputs to the deep regression neural network include: real-time flow deviation, the current rotation angle of the movable blade 4, and engine operating state parameters. These inputs are processed by the deep regression neural network model to output the optimal rotation angle adjustment. To capture the transient response characteristics of the engine, the neural network uses a long short-term memory time series processing network, enabling the deep regression neural network model to dynamically track and predict the temporal changes of the system.

[0075] Furthermore, the deep learning model is trained on a virtual engine platform to simulate the performance of a real engine under various operating conditions. During training, a large amount of historical and real-time operating data is collected, and transfer learning is used to combine these two types of data. This allows the deep learning model to better adapt to changing real-world conditions and improve its generalization ability. Transfer learning significantly improves training efficiency by transferring knowledge gained from previous tasks to the current task. During optimization, an adaptive learning rate adjustment strategy is employed, combined with gradient descent and Adam optimization algorithms to ensure fast and stable model convergence.

[0076] In this embodiment, by pre-predicting the optimal angle information of the movable blade and the predicted flow rate of the turbine, the actual flow rate of the turbine is calculated based on the optimal angle information. By judging the deviation between the predicted flow rate and the actual flow rate, the rotation angle of the movable blade 4 is adjusted, which is beneficial to accurately adjust the rotation angle of the movable blade 4, reduce flow loss, and improve the adjustment efficiency of the movable blade 4.

[0077] Example 2

[0078] like Figure 13 As shown, the specific structure and working principle of this embodiment are basically the same as those of Embodiment 1. The specific difference is that the blade assembly also includes an intermediate blade 21, which is disposed between the fixed blade 3 and the movable blade 4. The intermediate blade 21 is connected to the drive assembly, which can drive the movable blade 4 and the intermediate blade 21 to move together.

[0079] Specifically, the drive assembly also includes a rocker arm 23. One end of the rocker arm 23 is connected to the linkage rod 7, and the other end is connected to the intermediate blade 21 via a fourth shaft 22. When the linkage rod 7 rotates, it can drive the fourth shaft 22 to rotate via the rocker arm 23, thereby driving the intermediate blade 21 to rotate. The rotation of the intermediate blade 21 can adjust the flow cross-section of the guide channel 5. Those skilled in the art can set the specific arrangement of the intermediate blade 21 according to actual needs, and no limitation is made here. In this embodiment, by setting the intermediate blade 21, the adjustment range of the guide channel 5 can be increased, which is beneficial to meeting the needs of various working conditions.

[0080] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and are not intended to 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 invention.

[0081] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0082] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0083] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0084] In this invention, the terms "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., refer to a specific feature, structure, material, or characteristic described in connection with that embodiment or example, which is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0085] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A variable geometry turbine guide, characterized in that, include: The inner edge plate and the outer edge plate are both annular, the outer edge plate is disposed outside the circumference of the inner edge plate, and an annular flow space is formed between the outer edge plate and the inner edge plate; Multiple blade assemblies are arranged circumferentially in the flow space. Each blade assembly includes a fixed blade and a movable blade. The fixed blade and the movable blade are arranged sequentially along the circumference and axial direction of the flow space. The outer peripheral wall of the inner edge plate is provided with a first groove, and the inner peripheral wall of the outer edge plate is provided with a second groove. The two ends of the movable blade are respectively located in the first groove and the second groove. A drive assembly is disposed on the outer edge plate and connected to the plurality of blade assemblies respectively to drive the movable blade to slide along a preset trajectory, wherein the first slide groove and the second slide groove are both matched with the preset trajectory; The driving component includes: A drive ring is spaced apart on the outer periphery of the outer edge plate. The drive ring is used to connect with an external drive component so that the drive component drives the drive to rotate around the axis of the drive ring within a preset range. The linkage component is provided in multiple ways, and the multiple linkage components are arranged sequentially along the circumference of the drive ring. The input end of each linkage component is connected to the drive ring, and the output end of the linkage component is connected to the movable blade. The linkage component includes: A linkage rod is provided, one end of which is rotatably connected to the outer edge plate via a first shaft, and the other end of which is connected to the drive ring via a second shaft. The drive ring is used to drive the linkage rod to rotate around the first shaft within a preset angle range. The middle part of the linkage rod is connected to the movable blade via a third shaft. An avoidance hole is provided on the outer edge plate corresponding to the third shaft.

2. The variable geometry turbine guide according to claim 1, characterized in that, In the direction of airflow, the fixed blade is located upstream and the movable blade is located downstream. The flow space is divided into an upstream section and a downstream section corresponding to the fixed blade and the movable blade. The inner edge plate and the outer edge plate of the upstream section gradually move away from each other, and the inner edge plate and the outer edge plate of the downstream section are parallel to each other.

3. The variable geometry turbine guide according to claim 1, characterized in that, The leading edge of the movable blade has a negative angle of attack α, where α is 3° to 5°.

4. The variable geometry turbine guide according to claim 1, characterized in that, The linkage component also includes a sealing plate, and the outer peripheral wall of the outer edge plate is provided with a third sliding groove. The sealing plate is slidably disposed in the third sliding groove, and the third shaft passes through the sealing plate.

5. The variable geometry turbine guide according to claim 1, characterized in that, The preset angle range is -9° to 6°.

6. The variable geometry turbine guide according to claim 1, characterized in that, In the axial direction of the flow space, the total length of the fixed blade and the movable blade of one set of blade assemblies is Δx1, the overlap distance between the movable blade and the fixed blade of one set of blade assemblies is Δx2, and the overlap AO = Δx2 / Δx1 = 0%~5%.

7. The variable geometry turbine guide according to claim 1, characterized in that, In the circumferential direction of the flow space, in two adjacent sets of blade assemblies, the distance between the leading edge of one set of fixed blades and the leading edge of the other set of fixed blades is s, and the distance between the leading edge of one set of movable blades and the trailing edge of the other set of fixed blades is t, with an intercept ratio PP = t / s = 90% to 95%.

8. The variable geometry turbine guide according to claim 1, characterized in that, The movable blade is provided with a cooling airflow channel, and the end face and side wall of the movable blade are provided with air film holes that communicate with the cooling airflow channel.

9. The variable geometry turbine guide according to claim 1, characterized in that, Both the movable blade and the fixed blade are bent-twisted blades.

10. The variable geometry turbine guide according to claim 1, characterized in that, The inner edge plate adopts a non-axisymmetric endwall design to reduce airflow loss.

11. A smart control method for a variable geometry turbine guide according to any one of claims 1 to 10, characterized in that, Includes the following steps: Predict the optimal angle information of the active blades and the predicted flow rate of the turbine; Calculate the actual flow rate of the turbine based on the optimal angle information; The deviation between the actual flow rate and the predicted flow rate of the turbine is calculated. If the deviation is within the preset range, the optimal angle information meets the requirements. If the deviation is greater than or less than the preset range, the optimal angle information is adjusted.

Images