A turbine shaping method based on weakening the trailing edge shock wave

Abstract

The present invention is a turbine shaping method based on weakening the trailing edge shock wave. The present invention relates to the field of turbine shaping technology. In view of the fact that turbine design methods are still imperfect, the present invention reduces the complexity of the design as much as possible. The present invention analyzes the trailing edge shock wave of the original blade profile, divides the trailing edge shock wave into an inner tail shock wave, an outer tail shock wave, and a reflected shock wave, and analyzes the intensity of the three shock waves under given working conditions to obtain an analysis result; after analyzing the shock wave intensity, a framework is established based on the specific analysis result. The present invention enables the blade grid to smoothly transition in the design, adjusts the wave system of the trailing edge of the blade grid, weakens the trailing edge shock wave, and reduces losses.

Description

Technical Field

[0001] The invention relates to the technical field of turbine shaping, in particular to a turbine shaping method based on weakening the trailing edge shock wave. Background Art

[0002] The design of aircraft engine fans and compressors is moving towards high Mach numbers and high blade tip tangential speeds. High relative Mach numbers at the blade tip can cause severe shock wave boundary layer interference, and the interaction between the shock wave and the boundary layer and changes in back pressure behind the cascade significantly affect the shape and intensity of the shock wave. Aircraft gas turbine engines primarily utilize reaction-type turbines, where the gas accelerates and expands in both the rotor and stator ducts. Transonic turbines typically have a subsonic inlet flow and a supersonic outlet flow. A transonic region exists in the cascade duct, and the flow phenomena within the turbine rotor and stator are very similar to those in the nozzle. Shock waves are typically absent in the turbine cascade duct under design conditions, but due to uneven incoming flow or changes in operating conditions, the back pressure in the cascade duct often differs from that under design conditions. The flow field within a transonic turbine cascade under varying backpressures resembles that of a Laval nozzle. Point j represents the design operating condition, where the nozzle exit pressure equals the downstream backpressure. As the backpressure increases, the exit pressure falls below it, leading to the appearance of a shock wave. The shock wave's position depends on the ratio of the exit pressure to the backpressure. As the backpressure decreases, the shock wave moves downstream from the nozzle channel. Conversely, if the backpressure falls below the nozzle exit pressure, an expansion wave system appears.

[0003] With the continuous development of aircraft engines, the demand for high thrust-to-weight ratios continues to increase. As a key component of aircraft engines, marine gas turbines, and marine turbochargers, the turbine's performance is crucial to the safe and stable operation of the entire engine. Modern turbine technology is moving towards increasing turbine inlet temperature and pressure, while reducing the number of stages, thereby increasing engine load. Increasing load refers to increasing the single-stage pressure drop ratio or load factor. Increasing the pressure drop ratio can reduce the number of turbine stages, thereby reducing the number of blade rows and reducing weight. Reducing the number of turbine stages to a single stage increases the stage load and the Mach number of the outflow, inevitably leading to partial or even complete supersonic flow in the flow channel. This supersonic flow creates complex shock wave structures within the turbine cascade channel, especially near the trailing edge of the blades. Losses caused by the trailing edge shock wave account for approximately one-third of the total losses. Reducing shock wave losses is a key approach to improving aircraft engine turbine starting design.

[0004] The shock wave control technologies at home and abroad mainly include the following aspects:

[0005] Optimize the blade profile;

[0006] Use cooling method;

[0007] Adopt unsteady control technology.

[0008] In most optimization results, trailing edge curvature is a crucial focus, representing the mainstream and most important optimization approach. While research has made some progress domestically and internationally on reducing shock wave intensity through blade profile modification, the current optimization design principles and technical framework are immature, and precise improvements to shock wave structure and intensity are still far from being achieved. Optimal transonic turbine performance is still a long way off. It is necessary to refine optimization design methods for shock wave reduction to promote the development of transonic turbines. Summary of the Invention

[0009] In view of the shortcomings of the existing technology, the present invention reduces the design complexity as much as possible in view of the imperfect turbine design method, enables the blade grid to have a smooth transition in the design, adjusts the blade grid trailing edge wave system, weakens the trailing edge shock wave, and reduces losses.

[0010] The present invention provides a turbine shaping method based on weakening the trailing edge shock wave, and the present invention provides the following technical solutions:

[0011] A turbine shaping method based on weakening the trailing edge shock wave comprises the following steps:

[0012] The original blade's trailing edge shock wave is analyzed, and the trailing edge shock wave is divided into inner tail shock wave, outer tail shock wave and reflected shock wave. Under given working conditions, the intensity of the three shock waves is analyzed to obtain the analysis results.

[0013] After analyzing the shock wave intensity, a framework is established based on the specific analysis situation.

[0014] Preferably, under given working conditions, the intensities of the three shock waves are analyzed, and the following results are obtained during the analysis:

[0015] Case 1: When the intensity of the reflected shock wave is stronger than that of the other two shock waves, a control frame is established near the shock wave reflection point on the suction side. A control frame is established within the range of 20% upstream and 20% downstream of the reflection point, and free-form surface modeling is performed on the curvature at the control frame.

[0016] Preferably, when the reflected shock wave is stronger than the inner and outer tail shock waves, a control 3×3×3 frame is established near the reflection point. However, considering that the control points do not appear inside the entity, only the wrapped entity is selected. The actual number of control points on the frame is 24.

[0017] In order to maintain the closedness of the frame, 26 points are set; the reflection point at 50% of the blade height is the midpoint of the frame. This point is only a positioning point and does not participate in the FFD; the frame takes the upstream 20% and the downstream 20% along the chord length as the front and rear boundaries; the upper and lower boundaries are set within the range of no more than 2.5-5% of the blade height distance between the blade top and the blade root; and the structure near the suction side reflection point is modified by applying a certain displacement vector in the X, Y, and Z directions to the control point.

[0018] Preferably, under given working conditions, the intensities of the three shock waves are analyzed, and the following results are obtained during the analysis:

[0019] Case 2: When the intensity of the reflected shock wave is not high, but the intensity of the inner and outer tail shock waves is high, it is necessary to establish a control frame at the trailing edge of the original blade profile and change the shape of the trailing edge through free-form surface deformation to weaken the trailing edge strength.

[0020] Preferably, for case 2, the intensity of the inner tail shock wave and the outer tail shock wave is higher than the intensity of the reflected shock wave, then a control frame is established near the trailing edge, which wraps the entire trailing edge part. Similarly, there is no situation where the control point appears inside the entity. The free surface modeling takes the trailing edge point at 50% of the blade height as the center point, and the front and rear boundaries are set at a distance of 5% of the chord length from the center point. The upper and lower boundaries are the same as above. The ffd method changes the shape of the trailing edge and the curvature parameters.

[0021] Preferably, under given working conditions, the intensities of the three shock waves are analyzed, and the following results are obtained during the analysis:

[0022] Case 3: When the shock wave intensity cannot be reduced through free-form surface deformation, it proves that the shock wave intensity is related to the throat area where the tail and suction sides of the pressure surfaces of the two adjacent blades are located, that is, it is related to the upstream flow. At this time, it is necessary to establish the pressure side trailing edge and the suction side near the throat in the same framework and improve the shape through free-form surface deformation.

[0023] Preferably, for case 3, a control framework is established for the throat composed of two adjacent blades, and the center point is created with the center line of the flow channel at 50% of the blade height. The boundary is set based on the suction surface and pressure surface area designed to wrap the throat. The curvature of the pressure surface is increased, but the curvature of the pressure surface cannot be too large, otherwise the loss caused by the derivative effect will be greater than the loss of weakening the trailing edge shock wave; when the framework cannot perform free-form surface modeling at this moment, it is necessary to increase control points and refine the control surface.

[0024] A turbine shaping system based on weakening the trailing edge shock wave, the system comprising:

[0025] An analysis module, wherein the analysis module analyzes the trailing edge shock wave of the original blade profile, divides the trailing edge shock wave into an inner tail shock wave, an outer tail shock wave, and a reflected shock wave, and analyzes the intensity of the three shock waves under given operating conditions to obtain an analysis result;

[0026] The framework establishment module analyzes the shock wave intensity and then establishes the framework according to the specific analysis results.

[0027] A computer-readable storage medium stores a computer program, which is executed by a processor to implement a turbine shaping method based on weakening the trailing edge shock wave.

[0028] A computer device comprises a memory and a processor, wherein the memory stores a computer program and the processor implements a turbine shaping method based on weakening the trailing edge shock wave when executing the computer program.

[0029] The present invention has the following beneficial effects:

[0030] Compared with the prior art, the present invention has the following advantages:

[0031] While meeting design requirements, this invention establishes a holistic design for conventional aircraft engine turbines. Rather than simply modifying the blade profile curve at a specific blade height to create a smooth surface, this method utilizes FFD (Free Form Deformation) to further optimize existing turbine design methods. Rather than intercepting the blade profile curve at continuous blade height to determine all specific parameters, this method selects a moving point and applies vector displacement, influencing the deformation of the controlled surface near that point. This is expected to produce a turbine blade cascade shape that is different from previous designs, providing a new approach to turbine design based on reducing trailing edge shock waves. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0033] Figure 1 Shown is a design concept and flow chart based on a turbine shaping method that weakens the trailing edge shock wave;

[0034] Figure 2 A schematic diagram showing the control framework established for 20% upstream and 20% downstream of the suction side reflection point, i.e., step 2;

[0035] Figure 3 Shown is the control frame at the trailing edge;

[0036] Figure 4 The control frame at the throat, shown as a combination of the pressure and suction sides. DETAILED DESCRIPTION

[0037] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0038] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0040] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0041] The present invention is described in detail below with reference to specific embodiments. Specific embodiment one:

[0043] according to Figures 1 to 4 As shown, the specific optimization technical solution adopted by the present invention to solve the above technical problems is: the present invention relates to a turbine shaping method based on weakening the trailing edge shock wave.

[0044] A turbine shaping method based on weakening the trailing edge shock wave comprises the following steps:

[0045] The original blade's trailing edge shock wave is analyzed, and the trailing edge shock wave is divided into inner tail shock wave, outer tail shock wave and reflected shock wave. Under given working conditions, the intensity of the three shock waves is analyzed to obtain the analysis results.

[0046] After analyzing the shock wave intensity, a framework is established based on the specific analysis situation.

[0047] While meeting design requirements, this invention establishes a holistic design for conventional aircraft engine turbines. Rather than simply modifying the blade profile curve at a specific blade height to create a smooth surface, this method utilizes FFD (Free Form Deformation) to further optimize existing turbine design methods. Rather than intercepting the blade profile curve at continuous blade height to determine all specific parameters, this method selects a moving point and applies vector displacement, influencing the deformation of the controlled surface near that point. This is expected to produce a turbine blade cascade shape that is different from previous designs, providing a new approach to turbine design based on reducing trailing edge shock waves. Specific embodiment two:

[0049] The difference between the second embodiment of the present application and the first embodiment is that:

[0050] Under given working conditions, the intensity of the three shock waves is analyzed, and the following results are obtained during the analysis:

[0051] Case 1: When the intensity of the reflected shock wave is stronger than that of the other two shock waves, a control frame is established near the shock wave reflection point on the suction side. A control frame is established within the range of 20% upstream and 20% downstream of the reflection point, and free-form surface modeling is performed on the curvature at the control frame. Specific embodiment three:

[0053] The only difference between the third embodiment of the present application and the second embodiment is that:

[0054] When the reflected shock wave is stronger than the inner and outer tail shock waves, a 3×3×3 control frame is established near the reflection point. However, considering that the control points do not appear inside the entity, only the wrapped entity is selected. The actual number of control points on the frame is 24.

[0055] In order to maintain the closedness of the frame, 26 points are set; the reflection point at 50% of the blade height is the midpoint of the frame. This point is only a positioning point and does not participate in the FFD; the frame takes the upstream 20% and the downstream 20% along the chord length as the front and rear boundaries; the upper and lower boundaries are set within the range of no more than 2.5-5% of the blade height distance between the blade top and the blade root; and the structure near the suction side reflection point is modified by applying a certain displacement vector in the X, Y, and Z directions to the control point. Specific embodiment four:

[0057] The only difference between the fourth embodiment of the present application and the third embodiment is that:

[0058] Under given working conditions, the intensity of the three shock waves is analyzed, and the following results are obtained during the analysis:

[0059] Case 2: When the intensity of the reflected shock wave is not high, but the intensity of the inner and outer tail shock waves is high, it is necessary to establish a control frame at the trailing edge of the original blade profile and change the shape of the trailing edge through free-form surface deformation to weaken the trailing edge strength. Specific embodiment five:

[0061] The only difference between the fifth embodiment of the present invention and the fourth embodiment is that:

[0062] For case 2, the intensity of the inner and outer tail shock waves is higher than that of the reflected shock wave. A control frame is established near the trailing edge, which wraps the entire trailing edge. Similarly, there is no control point appearing inside the solid. The free-form surface modeling takes the trailing edge point at 50% of the blade height as the center point, and the front and rear boundaries are set at a distance of 5% of the chord length from the center point. The upper and lower boundaries are the same as above. The FFD method changes the shape and curvature parameters of the trailing edge. Specific embodiment six:

[0064] The only difference between the sixth embodiment of the present invention and the fifth embodiment is that:

[0065] Under given working conditions, the intensity of the three shock waves is analyzed, and the following results are obtained during the analysis:

[0066] Case 3: When the shock wave intensity cannot be reduced through free-form surface deformation, it proves that the shock wave intensity is related to the throat area where the tail and suction sides of the pressure surfaces of the two adjacent blades are located, that is, it is related to the upstream flow. At this time, it is necessary to establish the pressure side trailing edge and the suction side near the throat in the same framework and improve the shape through free-form surface deformation. Specific embodiment seven:

[0068] The only difference between the seventh embodiment of the present invention and the sixth embodiment is that:

[0069] For Case 3, a control framework is established for the throat composed of two adjacent blades, and the center point is created with the centerline of the flow channel at 50% of the blade height. The boundary is set based on the suction and pressure surface areas designed to wrap the throat. The curvature of the pressure surface is increased, but the curvature of the pressure surface cannot be too large, otherwise the loss caused by the derivative effect will be greater than the loss caused by weakening the trailing edge shock wave. When the framework cannot be free-formed at this moment, it is necessary to add control points and refine the control surface. Specific embodiment eight:

[0071] The only difference between the eighth embodiment of the present invention and the seventh embodiment is that:

[0072] The present invention provides a turbine shaping system based on weakening the trailing edge shock wave, the system comprising:

[0073] An analysis module, wherein the analysis module analyzes the trailing edge shock wave of the original blade profile, divides the trailing edge shock wave into an inner tail shock wave, an outer tail shock wave, and a reflected shock wave, and analyzes the intensity of the three shock waves under given operating conditions to obtain an analysis result;

[0074] The framework establishment module analyzes the shock wave intensity and then establishes the framework according to the specific analysis results. Specific embodiment nine:

[0076] The only difference between the ninth embodiment of the present invention and the eighth embodiment is that:

[0077] The present invention provides a computer-readable storage medium on which a computer program is stored. The program is executed by a processor to implement a turbine shaping method based on weakening the trailing edge shock wave.

[0078] The method comprises the following steps:

[0079] The original blade's trailing edge shock wave is analyzed, and the trailing edge shock wave is divided into inner tail shock wave, outer tail shock wave and reflected shock wave. Under given working conditions, the intensity of the three shock waves is analyzed to obtain the analysis results.

[0080] After analyzing the shock wave intensity, a framework is established based on the specific analysis situation. Specific embodiment ten:

[0082] The only difference between the tenth embodiment of the present invention and the ninth embodiment is that:

[0083] The present invention provides a computer device, comprising a memory and a processor, wherein the memory stores a computer program, and the processor implements a turbine shaping method based on weakening the trailing edge shock wave when executing the computer program.

[0084] The method comprises the following steps:

[0085] The original blade's trailing edge shock wave is analyzed, and the trailing edge shock wave is divided into inner tail shock wave, outer tail shock wave and reflected shock wave. Under given working conditions, the intensity of the three shock waves is analyzed to obtain the analysis results.

[0086] After analyzing the shock wave intensity, a framework is established based on the specific analysis situation. Specific embodiment eleven:

[0088] The only difference between the eleventh embodiment of the present invention and the tenth embodiment is that:

[0089] In view of the fact that the turbine design method is still imperfect, the present invention provides a design scheme for the turbine blade cascade blade profile, which reduces the design complexity as much as possible, enables the blade cascade to have a smooth transition in the design, adjusts the blade cascade trailing edge wave system, weakens the trailing edge shock wave, and reduces losses.

[0090] This invention uses FFD (Free-Form Deformation) to change the blade curvature to optimize the blade cascade design. A control framework is established for the turbine blade cascade as a whole, and control points are set. The density of control points can be set according to the degree of design refinement.

[0091] Select to set 26 points. After setting the points, select the vector direction of the points to be changed for the parameters to be changed later (pressure surface curvature, suction surface curvature) and move them.

[0092] The specific steps include:

[0093] Step 1: First, analyze the original blade's trailing edge shock. Trailing edge shocks are divided into inner tail shocks, outer tail shocks, and reflected shocks. Under given operating conditions, the intensities of these three shock waves are analyzed. The analysis broadly falls into three scenarios.

[0094] Case 1: If the intensity of the reflected shock wave is stronger than the other two shock waves, a control frame is established near the shock wave reflection point on the suction side, such as establishing a control frame within the range of 20% upstream and 20% downstream of the reflection point, such as Figure 1 As shown, free-form surface modeling is performed for the curvature at the control frame.

[0095] Case 2: The reflected shock wave is not strong, but the inner and outer tail shock waves are strong. In this case, it is necessary to establish a control framework at the trailing edge of the original blade, such as Figure 2 As shown, the shape of the trailing edge is then changed by free-form surface deformation to weaken the trailing edge strength, for example, the trailing edge is changed into an ellipse, a rectangle or other shapes.

[0096] Case 3: If the shock wave intensity is not reduced by free-form surface deformation in the above two cases, it proves that the shock wave intensity is related to the throat area where the pressure side and suction side of the two adjacent blades are located, that is, it is related to the upstream flow. In this case, it is necessary to build the pressure side trailing edge and the suction side near the throat into the same framework and improve the shape through free-form surface deformation. The established framework is as follows Figure 3 As shown,

[0097] Step 2: After analyzing the shock wave intensity, further explain where and how to establish the frame.

[0098] For case 1, when the reflected shock wave is stronger than the inner and outer tail shock waves, a control 3×3×3 frame is established near the reflection point. However, considering that the control point does not appear inside the entity, only the wrapped entity is selected, and the actual number of control points on the frame is 24. In order to maintain the closedness of the frame, 26 points are set. The reflection point at 50% of the blade height is taken as the midpoint of the frame (this point is only a positioning point and does not participate in ffd); the frame is taken along the chord length, with 20% upstream and 20% downstream as the front and rear boundaries; the upper and lower boundaries are set within the range of no more than 2.5-5% of the blade height distance between the blade top and the blade root. For example Figure 1 By applying a certain displacement vector in the X, Y, and Z directions to the control point, the structure near the reflection point on the suction side is modified.

[0099] For case 2, the intensity of the inner and outer tail shock waves is higher than that of the reflected shock wave. A control frame is then established near the trailing edge. This control frame wraps the entire trailing edge. Similarly, there is no control point inside the solid. The steps for free-form surface modeling are similar to those for case 1. The trailing edge point at 50% of the blade height is taken as the center point, and the front and rear boundaries are set at a distance of 5% of the chord length from the center point. The upper and lower boundaries are the same as above. The ffd method is used to change the shape, curvature and other parameters of the trailing edge. The control frame is as follows: Figure 2 shown.

[0100] For case 3, the intensity of the trailing edge shock wave is not weakened after changing the reflection point and the related parameters of the trailing edge, which proves that the intensity of the trailing edge shock wave is related to the upstream flow. In a transonic turbine, the outer tail shock wave has a greater impact on the total shock wave loss than the inner tail shock wave. Increasing the upstream shock wave intensity can effectively weaken the intensity of the outer tail shock wave downstream, thereby reducing the total shock wave loss. At this time, it is necessary to establish a control framework for the throat composed of two adjacent blades, create a center point with the center line of the flow channel at 50% of the blade height, and set the boundary based on the suction surface and pressure surface area designed to wrap the throat. Increase the curvature of the pressure surface, but the curvature of the pressure surface cannot be too large, otherwise the loss caused by the derivative effect will be greater than the loss of weakening the trailing edge shock wave. If the framework cannot perform free-form surface modeling well at this moment, it is necessary to add control points and refine the control surface. The control framework is as follows Figure 3 shown.

[0101] For the refinement of the blade profile of the pressure side and the suction side, more definition points can be added and multi-point optimization design can be performed to make the turbine blade design more reasonable.

[0102] This application utilizes the free-form deformation (FFD) method to optimize the design of engine turbine blade cascades. The above description is merely illustrative of the principles and effectiveness of this application and does not limit the specific design parameters of the turbine. Therefore, anyone with ordinary skill in the art can make any adjustments and modifications without departing from the technical principles described in this application.

[0103] This invention provides a turbine shaping method based on weakening the trailing edge shock wave. By establishing a control framework and controlling the points on the control framework grid, the geometric shape of the object is controlled. This method can move and deform the primary cross-section while achieving a smooth transition of the secondary cross-section during the design process, providing a design strategy.

[0104] The above is merely a preferred embodiment of a turbine shaping method based on weakening the trailing edge shock wave. The scope of protection of a turbine shaping method based on weakening the trailing edge shock wave is not limited to the above embodiment. All technical solutions based on this concept fall within the scope of protection of the present invention. It should be noted that for those skilled in the art, various improvements and variations that do not depart from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A turbine shaping method based on weakening the trailing edge shock wave, characterized by: The method comprises the following steps: The original blade's trailing edge shock wave is analyzed, and the trailing edge shock wave is divided into inner tail shock wave, outer tail shock wave and reflected shock wave. Under given working conditions, the intensity of the three shock waves is analyzed to obtain the analysis results. After analyzing the shock wave intensity, a framework is established based on the specific analysis situation; The following results were obtained during the analysis: Case 1: When the intensity of the reflected shock wave is stronger than that of the other two shock waves, a control frame is established near the shock wave reflection point on the suction side. A control frame is also established within the range of 20% upstream and 20% downstream of the reflection point, and free-form surface modeling is performed on the curvature at the control frame.

2. The method according to claim 1, wherein: When the reflected shock wave is stronger than the inner and outer tail shock waves, a 3×3×3 control frame is established near the reflection point, and only the wrapped entity is selected. The actual number of control points on the frame is 24. To maintain the closedness of the frame, 26 points are set; the reflection point at 50% of the blade height is the midpoint of the frame. The midpoint of the frame is only a positioning point and does not participate in the FFD; the frame takes the upstream 20% and the downstream 20% along the chord length as the front and rear boundaries; the upper and lower boundaries are set within the range of no more than 2.5-5% of the blade height distance between the blade top and the blade root; and the structure near the suction side reflection point is modified by applying a certain displacement vector in the X, Y, and Z directions to the control point.

3. The method according to claim 1, wherein: The following results were obtained during the analysis: Case 2: When the intensity of the reflected shock wave is not high, but the intensity of the inner and outer tail shock waves is high, it is necessary to establish a control frame at the trailing edge of the original blade profile and change the shape of the trailing edge through free-form surface deformation to weaken the trailing edge strength.

4. The method according to claim 3, wherein: For case 2, a control frame is established near the trailing edge, which wraps the entire trailing edge. No control points appear inside the solid. The free-form surface modeling takes the trailing edge point at 50% of the blade height as the center point, and sets the front and rear boundaries at a distance of 5% of the chord length from the center point. The upper and lower boundaries are the same as above. The FFD method changes the shape and curvature parameters of the trailing edge.

5. The method according to claim 1, wherein: The following results were obtained during the analysis: Case 3: The pressure side trailing edge near the throat and the suction side are built in the same framework, and the shape is improved through free-form surface deformation.

6. The method according to claim 4, wherein: For Case 3, a control framework is established for the throat formed by two adjacent blades. The center point is created using the flow channel centerline at 50% of the blade height. The boundary is set based on the suction and pressure surface areas designed to wrap around the throat. If the framework cannot be free-form surface modeled at this point, it is necessary to add control points and refine the control surface.

7. A turbine shaping system based on weakening the trailing edge shock wave, characterized by: The system comprises: An analysis module, wherein the analysis module analyzes the trailing edge shock wave of the original blade profile, divides the trailing edge shock wave into an inner tail shock wave, an outer tail shock wave, and a reflected shock wave, and analyzes the intensity of the three shock waves under given operating conditions to obtain an analysis result; The following results were obtained during the analysis: Case 1: When the reflected shock wave is stronger than the other two shock waves, a control frame is established near the shock wave reflection point on the suction side. A control frame is also established within the range of 20% upstream and 20% downstream of the reflection point, and free-form surface modeling is performed on the curvature of the control frame. The framework establishment module analyzes the shock wave intensity and then establishes the framework according to the specific analysis results.

8. A computer-readable storage medium having a computer program stored thereon, characterized in that: The program is executed by a processor to implement the method according to any one of claims 1 to 6.

9. A computer device comprising a memory and a processor, wherein the memory stores a computer program, wherein: When the processor executes the computer program, the method according to any one of claims 1 to 6 is implemented.

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