Design method and system of elliptical hole composite deflection structure applied to groove blade tip

Abstract

The present invention provides a method and system for designing a composite deflection structure of an elliptical hole applied to a groove blade tip, wherein the design variables of the method include: a relative chord length of a design origin, a radial deflection angle, an axial deflection angle and a self-deflection angle of the elliptical hole; firstly, the position of the design origin is determined according to the relative chord length, and then the composite deflection direction is determined by the radial and axial deflection angles, and the cross-section of the formed hole is determined by the self-deflection angle in the vertical plane of the composite deflection direction, and finally, the hole is opened according to the composite deflection direction to complete the construction of the cooling hole; the parameterized composite deflection directions are orthogonal to each other, and a wider range of composite inclined cooling hole structure designs is covered with fewer variables, thereby reducing the design variables for carrying out gas-thermal optimization work of the composite deflection structure of the cooling hole; the composite deflection direction of the cooling hole is determined by inverse three-dimensional projection modeling, and the obtained composite deflection structure has a one-to-one correspondence with the design parameters, and has the advantages of clear directional characteristics and flexible parameter transformation.

Description

Technical Field

[0001] The invention belongs to the technical field of gas turbines and aeroengines, and in particular relates to a design method and system for an elliptical hole composite deflection structure applied to a groove blade tip. Background Art

[0002] Gas turbine is a kind of power machinery, which is widely used in important industrial fields such as aerospace, ground power generation, and national production. With the increasing demand for turbine efficiency and environmental protection, engineers will complete the flow design of turbine by continuously increasing the inlet temperature of turbine, which is also one of the most effective ways to improve the efficiency of gas turbine. At present, the inlet temperature of gas turbine has far exceeded the heat resistance limit of high-temperature metal materials. For example, the gas inlet temperature of a certain F-class heavy-duty gas turbine exceeds 1700K, and the aircraft engine exceeds 2000K. Therefore, in order to ensure the safe operation of the turbine, it is necessary to carry out cooling design and thermal protection for the parts that are in direct contact with the gas, such as blades, end walls, and casings. The currently mature and widely used cooling and protection technologies include: impingement cooling, convection cooling, film cooling, thermal barrier coating, etc. Among them, film cooling extracts part of the low-temperature intake air of the compressor, sprays and diffuses it on the metal wall to form a thermal protection layer, and because it is in direct contact with the high-temperature gas, it has significant and efficient cooling performance, which is widely used in turbine design.

[0003] In order to maintain the stable operation of the turbine rotor and prevent the rotor from rubbing against the casing due to thermal expansion, centrifugal stress, etc. during operation, a gap of 1% to 2% of the blade height is often designed at the blade tip. The main flow of gas is driven by the pressure difference on both sides of the blade to generate leakage flow in the blade tip gap, and due to the slit throttling effect of the gap, the leakage flow often has the characteristics of high temperature, high speed, and thin boundary layer, which increases the difficulty of blade tip thermal protection. In recent years, in order to reduce the leakage flow and further improve the turbine efficiency, the application of grooved blade tips has gradually become popular, that is, a secondary plane is cut downward in the middle of the blade tip, and the primary plane serves as a shoulder wall surrounding the secondary plane, which increases the primary throttling of the leakage flow to secondary throttling, which further complicates the blade tip flow field while reducing the leakage flow.

[0004] The traditional blade tip cooling design uses circular cooling holes. To effectively protect the blade tip from heat in a high-temperature gas environment, more air film holes need to be arranged and the cooling flow rate needs to be increased. The reason is that the cooling efficiency of vertically arranged circular cooling holes is low, and the inclined circular cooling holes are prone to outflow contraction, which limits the expansion of the air film coverage area. In addition, there are very few parameterized methods that can flexibly design cooling hole structures suitable for compound angle deflection of groove blade tips. Summary of the invention

[0005] In order to solve the problems existing in the prior art, the present invention designs a parameterization method for the composite deflection structure of an elliptical cooling hole suitable for the groove blade tip. Compared with the existing groove blade tip cooling hole design method, the present invention provides a wide range of composite angle inclined cooling hole design method, which can improve the internal flow field of the blade tip groove through optimized design, improve cooling efficiency, reduce leakage flow, and improve the aerodynamic and heat transfer performance of the blade. At the same time, the present invention performs parameterized design for the elliptical hole, which can significantly improve the air film cooling efficiency, expand the air film coverage range, and reduce the convective heat transfer coefficient compared with the traditional circular hole.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is: a design method of an elliptical hole composite deflection structure applied to a groove blade tip, comprising the following steps:

[0007] S1, shaping the bottom surface of the groove of the turbine moving blade, and determining the middle arc line and the derived middle arc line of the blade top according to the inner contour line formed by the outer contour line of the blade and the shoulder wall of the groove;

[0008] S2, the blade tip front line is made from the chord length line of the blade tip outer line, and the parallel line of the blade tip front line is made by given distance parameters, and the origin position of the cooling hole is determined according to the intersection of the parallel line of the blade tip front line and the mid-camber line or the derived mid-camber line;

[0009] S3, make a perpendicular line of the groove bottom surface from the origin of the supercooling hole, perform three-dimensional decomposition at the origin of the cooling hole according to the principle of three-dimensional projection, construct a composite deflection line by the inverse three-dimensional projection method, and respectively establish the perpendicular plane, tangent plane and parallel plane of the median arc line, or the perpendicular plane, tangent plane and parallel plane of the derived median arc line; specify the radial deflection angle and the axial deflection angle, respectively determine the radial deflection line in the perpendicular plane of the median arc line or the derived median arc line, and the axial deflection line in the tangent plane of the median arc line or the derived median arc line, and combine the perpendicular line of the groove bottom surface of finite length to determine the composite deflection line according to the principle of vector synthesis;

[0010] S4, in the vertical plane of the composite deflection line, the self-deflection angle of the major axis of the elliptical hole is specified to determine the forming section of the elliptical hole, and finally the forming hole is constructed in combination with the direction of the composite deflection line.

[0011] The bottom surface of the groove in S1 is a plane without curvature, and the bottom surface of the groove with curvature is projected as a plane without curvature.

[0012] In S1, a higher-order derived mid-arc line is generated between derived mid-arc lines or between a derived mid-arc line and an inner contour line of a groove.

[0013] In S1, the blade mid-arc line is drawn according to the moving trajectory of the center of the inscribed circle of the outer contour line, and the derived mid-arc line is drawn according to the moving trajectory of the center of the inscribed circle of the mid-arc line and the inner contour line.

[0014] The chord line of the blade top outer profile line is tangent to the leading and trailing edges of the outer profile line at the same time. The forehead line and the rear forehead line are made through the endpoints of the chord line. The forehead line and the rear forehead line are tangent to the leading and trailing edges of the outer profile line respectively, and are also perpendicular to the chord line.

[0015] The direction of the composite deflection angle is determined by the radial deflection angle and the axial deflection angle. The radial deflection angle is the angle between the perpendicular line of the cooling hole origin and the radial deflection line, and is located in the vertical plane of the median arc line or the derived median arc line. The axial deflection angle is the angle between the perpendicular line of the cooling hole origin and the axial deflection line, and is located in the tangent plane of the median arc line or the derived median arc line.

[0016] In S4, the self-deflection angle is located in the perpendicular plane of the composite deflection line.

[0017] In S4, the initial long axis direction of the elliptical hole should be parallel to the bottom surface of the groove. In the vertical plane of the composite deflection line of the supercooling hole origin, the intersection of the vertical plane and the bottom surface of the groove is taken as the initial long axis direction of the elliptical hole. The initial long axis direction of the elliptical hole is rotated counterclockwise in the vertical plane of the composite deflection line. The rotation angle is the self-deflection angle. The long axis direction of the elliptical hole after self-deflection is obtained to determine the final elliptical hole forming section.

[0018] Based on the above invention concept, a system for designing a composite deflection structure of an elliptical hole applied to a groove blade tip is also provided, comprising a reference line acquisition module, an origin position acquisition module, a composite deflection line acquisition module and a forming hole construction module;

[0019] The reference line acquisition module is used to model the bottom surface of the groove of the turbine moving blade, and determine the middle arc line and the derived middle arc line of the blade top according to the inner contour line formed by the blade outer line and the groove shoulder wall;

[0020] The origin position acquisition module makes a blade tip front line according to the chord length line of the blade tip outer line, makes a line parallel to the blade tip front line given a distance parameter, and determines the origin position of the cooling hole according to the intersection of the line parallel to the blade tip front line and the mid-arc line or the derived mid-arc line;

[0021] The composite deflection line acquisition module is used to make a perpendicular line of the groove bottom surface from the origin of the supercooling hole, perform three-dimensional decomposition at the origin of the cooling hole according to the principle of three-dimensional projection, and construct the composite deflection line by the inverse three-dimensional projection method, and respectively establish the perpendicular plane, tangent plane and parallel plane of the middle arc line, or the three projection planes of the perpendicular plane, tangent plane and parallel plane of the derived middle arc line; specify the radial deflection angle and the axial deflection angle, respectively determine the radial deflection line in the perpendicular plane of the middle arc line or the derived middle arc line, and the axial deflection line in the tangent plane of the middle arc line or the derived middle arc line, and combine the perpendicular line of the groove bottom surface of finite length to determine the composite deflection line according to the principle of vector synthesis;

[0022] The forming hole construction module is used to specify the self-deflection angle of the long axis of the elliptical hole in the vertical plane of the composite deflection line, determine the forming section of the elliptical hole, and finally construct the forming hole in combination with the direction of the composite deflection line.

[0023] A computer device is also provided, including a processor and a memory, the memory is used to store a computer executable program, the processor reads the computer executable program from the memory and executes it, and when the processor executes the computer executable program, the elliptical hole composite deflection structure design method applied to the groove blade tip of the present invention can be realized

[0024] Compared with the prior art, the present invention has at least the following beneficial effects: the present invention performs parameterized design on the composite deflection structure of the groove blade tip cooling hole, combines the radial and axial deflection angles with reference to the mid-arc line or the derived mid-arc line, and the self-deflection angle peculiar to the elliptical hole, and adopts the inverse three-dimensional projection modeling method to determine the cooling hole structure. On the one hand, the parameterized composite deflection directions are orthogonal to each other, and a wider range of composite inclined cooling hole structure design is covered with fewer variables, which reduces the design variables for the aero-thermal optimization of the composite deflection structure of the cooling hole and saves computing resources. On the other hand, the composite deflection direction of the cooling hole is determined by inverse three-dimensional projection modeling, which does not rely on the specified order of the deflection direction, that is, regardless of whether any deflection angle parameter is specified first or changed, the obtained composite There is a one-to-one correspondence between the deflection structure and the design parameters, which has the advantages of clear directional characteristics and flexible parameter transformation, and meets the needs of carrying out aero-thermal optimization design of the composite deflection structure of the cooling hole suitable for the complex flow field of the blade tip; the present invention performs parameterized design on the elliptical hole. On the one hand, compared with the traditional circular hole, the elliptical hole adds the design variable of the self-deflection direction, which is conducive to carrying out optimization design to further improve the cooling efficiency, reduce the heat transfer coefficient and reduce the aerodynamic loss; on the other hand, compared with the traditional circular hole, the elliptical hole extends the hole circumference length of the outflow edge according to the increase of the aspect ratio, expands the air film coverage range, and reduces the jet height. Applying it to the groove blade tip cooling design is conducive to improving the cooling performance, reducing the cooling flow, and thus improving the turbine efficiency of the gas engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is the tip structure of the turbine blade.

[0026] Figure 2 This is a schematic diagram of the positioning of the cooling hole origin.

[0027] Figure 3 Schematic diagram of the three-dimensional decomposition of the deflection angle of the composite deflection structure.

[0028] Figure 4 This is a three-dimensional model diagram of the elliptical hole composite deflection structure.

[0029] Figure 5 This is the distribution cloud diagram of the groove blade tip film cooling efficiency.

[0030] In the attached drawings, 1-turbine moving blade; 11-groove shoulder wall; 12-groove bottom surface; 121-center arc line; 122-derived center arc line; 13-cooling hole; 131-vertical line of groove bottom surface; 132-radial deflection line; 133-axial deflection line; 134-compound deflection line; 135-initial long axis direction; 136-self-deflection long axis direction. DETAILED DESCRIPTION

[0031] In order to make the technical methods and implementation effects of the present invention clearer, the technical solutions involved in the implementation of the present invention will be explained more clearly and in detail in combination with the application drawings of the present invention. The specific implementation methods illustrated in the application drawings are only some implementation cases of the present application. The explanations with reference to the drawings are exemplary in nature, and the purpose is to specifically explain the present application, and cannot be understood as limitations on the present application. Based on the implementation methods disclosed in the present application, other implementation cases established by ordinary technicians in this field without creative work are all within the scope of protection of the present application. The specific implementation methods of the present application will be described in detail below based on the implementation cases in the drawings.

[0032] The present invention proposes a parametric design method for an elliptical cooling hole on a groove blade tip, which is beneficial to carrying out aero-thermal optimization of the groove blade tip and can provide a technical reference for the optimization design of improving the aero-thermal performance of the groove blade tip.

[0033] The parametric design method of the composite deflection structure of the elliptical cooling hole suitable for the groove blade tip of the present invention specifically comprises the following steps:

[0034] S1, determine the center camber line and derived center camber line of the blade tip according to the projection of the blade outer contour line and the inner contour line.

[0035] S2, determine the blade tip front line according to the chord length of the blade tip outer profile line. Determine the cooling hole origin position according to the intersection of the line parallel to the blade tip front line and the mid-camber line or the derived mid-camber line.

[0036] S3, draw a vertical line of the bottom surface of the groove of finite length from the origin of the supercooling hole, perform three-dimensional decomposition at the origin of the cooling hole according to the principle of three-dimensional projection, and establish three projection surfaces: the vertical surface of the middle arc line, the section of the middle arc line, and the parallel surface of the middle arc line. Determine the radial deflection line in the vertical surface of the middle arc line according to the specified radial deflection angle, and determine the axial deflection line in the section of the middle arc line according to the specified axial deflection angle. Finally, combine the vertical line of the bottom surface of the groove of finite length and determine the composite deflection line according to the principle of vector synthesis.

[0037] S4, in the vertical plane of the composite deflection line, the direction when the major axis of the ellipse is parallel to the bottom surface of the groove is taken as the initial direction, the self-deflection angle in the major axis direction is specified, the forming section of the elliptical hole is determined, and finally the forming hole is constructed according to the direction of the composite deflection line.

[0038] Specifically, Figure 1 As shown, (a) is a three-dimensional structure of a blade with a grooved blade top, (b) is a schematic diagram of a center arc line, and (c) is a schematic diagram of a derived center arc line. First, the plane of the turbine moving blade 1 is projected in the radial direction to obtain the outer contour line of the grooved blade top and the inner contour line surrounded by the groove shoulder wall 11. The blade center arc line 121 is drawn according to the moving trajectory of the center point of the inscribed circle of the outer contour line. The derived center arc line 122 is drawn according to the moving trajectory of the center point of the center arc line 121 and the inscribed circle of the inner contour line. Considering the multiple derived center arc lines generated according to the moving trajectory of the derived center arc line and the center arc line or the inscribed circle of the inner contour line, it is theoretically possible to obtain multiple derived center arc lines of an infinite number of groove bottom surfaces. In this case, only the center arc line is used as an example.

[0039] like Figure 2 As shown, the blade chord length line is drawn according to the outer shape line of the blade, and the length is C l , the chord line is tangent to both the leading and trailing edges of the outer shape line. The front and rear forehead lines are made through the endpoints of the chord line, and are tangent to the leading and trailing edges of the outer shape line respectively. Specify the length from the front forehead line of the blade l , make a line parallel to the frontal line of the blade and intersect the middle arc line, and designate the intersection position as the origin position of the cooling hole 13. The position parameter is based on the relative chord length. l / C l express.

[0040] refer to Figure 3 , where (a) is a schematic diagram of the radial deflection angle and the axial deflection angle, and (b) is a schematic diagram of the self-deflection angle of the elliptical hole. Considering that the characteristics of the composite deflection structure can be blurred into the composite deflection in the radial section and the axial section, the radial deflection angle ( α ) and axial deflection angle ( β ) describes the composite deflection direction. The composite deflection structure is decomposed in three dimensions at the origin of the cooling hole, as shown in Figure 3 As shown in (a), the composite deflection line is constructed by the inverse three-dimensional projection method: the vertical line 131 of the bottom surface of the groove is made through the origin of the cooling hole. The vertical line 131 has a finite length. A parallel surface of the middle arc line is made through the end of the vertical line as the vertical projection surface of the composite deflection line. The vertical line 131 through the bottom surface of the groove is made into the vertical surface of the middle arc line. The deflection within the vertical surface of the middle arc line is called radial deflection. According to the radial deflection angle ( α ) to determine the radial deflection line 132, which is the projection of the composite deflection line on the vertical plane of the middle arc. The vertical line 131 through the bottom of the groove is used to make a section of the middle arc. The deflection in the section of the middle arc is called the axial deflection. According to the axial deflection angle ( β) determine the axial deflection line 133, which is the projection of the composite deflection line on the middle arc section. According to the vertical projection of the radial deflection line and the axial deflection line in the plane parallel to the middle arc, the vertical projection line of the composite deflection line is determined according to the vector synthesis principle. Finally, the vertical line 131 of the groove bottom surface is vector synthesized with the vertical projection line of the determined composite deflection line to draw a composite deflection line 134, which is the composite deflection direction.

[0041] Considering the design requirements of expanding the coverage of the air film and improving the cooling performance of the air film, according to the characteristics of the elliptical cooling hole, the initial long axis direction of the elliptical hole should be parallel to the bottom surface of the groove, so as to increase the circumference of the outlet hole of the cooling hole. Therefore, in the vertical plane of the composite deflection line of the supercooling hole origin, the intersection of the vertical plane and the bottom surface of the groove is taken as the initial long axis direction 135 of the elliptical hole. The initial long axis direction 135 of the elliptical hole is rotated counterclockwise in the vertical plane of the composite deflection line, such as Figure 3 (b) shows that the rotation angle is the self-deflection angle ( γ ), obtain the long axis direction 136 of the elliptical hole after self-deflection, so as to determine the final elliptical hole forming section. The elliptical hole forming section is established along the composite deflection line direction, such as Figure 4 shown.

[0042] Figure 5 The cooling effect of the compound deflected elliptical hole is demonstrated, where (a) is the film cooling effect of the traditional circular cooling hole without a deflection angle, and (b) is the cooling effect of the compound deflected elliptical cooling hole. Compared with the traditional circular cooling hole without a deflection angle, the compound deflected elliptical cooling expands the coverage of the air film, enhances the wall adhesion effect of the cooling flow, and significantly improves the film cooling efficiency. It can reduce the cooling flow used in the overcooling zone and thus improve the turbine efficiency.

[0043] In particular, the recommended setting range of the radial deflection angle of the cooling hole is -60° ~ 60°, and the radial deflection angle should be adjusted according to the blade thickness; the recommended setting range of the axial deflection angle is -60° ~ 60°, and the axial deflection angle should be adjusted according to the relative position of the cooling hole and the shoulder wall to avoid the forming hole penetrating the blade body; the recommended setting range of the self-deflection angle is -15° ~ 15°. Too large a self-deflection angle will cause a large deformation of the elliptical cooling hole outlet.

[0044] Based on the above invention concept, a system for designing a composite deflection structure of an elliptical hole applied to a groove blade tip is also provided, comprising a reference line acquisition module, an origin position acquisition module, a composite deflection line acquisition module and a forming hole construction module;

[0045] The reference line acquisition module is used to model the bottom surface of the groove of the turbine moving blade, and determine the middle arc line and the derived middle arc line of the blade top according to the inner contour line formed by the blade outer line and the groove shoulder wall;

[0046] The origin position acquisition module makes a blade tip front line according to the chord length line of the blade tip outer line, makes a line parallel to the blade tip front line given a distance parameter, and determines the origin position of the cooling hole according to the intersection of the line parallel to the blade tip front line and the mid-arc line or the derived mid-arc line;

[0047] The composite deflection line acquisition module is used to make a perpendicular line of the groove bottom surface from the origin of the supercooling hole, perform three-dimensional decomposition at the origin of the cooling hole according to the principle of three-dimensional projection, and construct the composite deflection line by the inverse three-dimensional projection method, and respectively establish the perpendicular plane, tangent plane and parallel plane of the middle arc line, or the three projection planes of the perpendicular plane, tangent plane and parallel plane of the derived middle arc line; specify the radial deflection angle and the axial deflection angle, respectively determine the radial deflection line in the perpendicular plane of the middle arc line or the derived middle arc line, and the axial deflection line in the tangent plane of the middle arc line or the derived middle arc line, and combine the perpendicular line of the groove bottom surface of finite length to determine the composite deflection line according to the principle of vector synthesis;

[0048] The forming hole construction module is used to specify the self-deflection angle of the long axis of the elliptical hole in the vertical plane of the composite deflection line, determine the forming section of the elliptical hole, and finally construct the forming hole in combination with the direction of the composite deflection line.

[0049] In addition, the present invention can also provide a computer device, including a processor and a memory, the memory is used to store a computer executable program, the processor reads part or all of the computer executable program from the memory and executes it, and when the processor executes part or all of the computer executable program, it can implement the elliptical hole composite deflection structure design method applied to the groove blade top described in the present invention.

[0050] The computer device may be a laptop computer, a desktop computer or a workstation.

[0051] The processor can be a central processing unit (CPU), a graphics processing unit (GPU) / digital signal processor (DSP), an application-specific integrated circuit (ASIC), or an off-the-shelf field-programmable gate array (FPGA).

[0052] The memory of the present invention may be an internal storage unit of a laptop computer, a desktop computer or a workstation, such as a memory or a hard disk; or an external storage unit, such as a mobile hard disk or a flash memory card.

[0053] The above contents are only for explaining the technical idea of ​​the present invention and cannot be used to limit the protection scope of the present invention. Any changes made on the basis of the technical solution in accordance with the technical idea proposed by the present invention shall fall within the protection scope of the claims of the present invention.

Claims

1. A design method for an elliptical hole composite deflection structure applied to a groove blade tip, characterized in that: The following steps are involved: S1, shaping the bottom surface of the groove of the turbine moving blade (1), and determining the middle arc line (121) and the derived middle arc line (122) of the blade tip according to the inner contour line formed by the blade outer profile line and the groove shoulder wall (11); S2, a blade tip front line is made from the chord length line of the blade tip outer profile line, a line parallel to the blade tip front line is made with a given distance parameter, and the origin position of the cooling hole (13) is determined according to the intersection of the line parallel to the blade tip front line and the mid-arc line (121) or the derived mid-arc line (122); S3, draw a perpendicular line to the bottom surface of the groove through the origin of the cooling hole (13), perform three-dimensional decomposition at the origin of the cooling hole (13) according to the principle of three-dimensional projection, construct a composite deflection line by the inverse three-dimensional projection method, and respectively establish the vertical plane, tangent plane and parallel plane of the middle arc line (121), or the vertical plane, tangent plane and parallel plane of the derived middle arc line (122); specify the radial deflection angle and the axial deflection angle, respectively determine the radial deflection line (132), the middle arc line (132) in the vertical plane of the middle arc line (121) or the derived middle arc line (122) The axial deflection line (133) in the section of the (121) or the derived mid-arc line (122) is combined with the finite length groove bottom surface perpendicular line (131) to determine the composite deflection line (134) according to the vector synthesis principle; the radial deflection angle and the axial deflection angle are used to determine the direction of the composite deflection angle, the radial deflection angle is the angle between the cooling hole origin perpendicular line and the radial deflection line, and is located in the vertical plane of the mid-arc line or the derived mid-arc line, and the axial deflection angle is the angle between the cooling hole origin perpendicular line and the axial deflection line, and is located in the section of the mid-arc line or the derived mid-arc line; S4, in the vertical plane of the composite deflection line (134), specify the self-deflection angle of the major axis of the elliptical hole, determine the forming section of the elliptical hole, and finally construct the forming hole in combination with the direction of the composite deflection line (134), and the self-deflection angle is located in the vertical plane of the composite deflection line; the initial major axis direction of the elliptical hole should be parallel to the bottom surface of the groove, in the vertical plane of the composite deflection line of the origin of the supercooling hole, the intersection line of the vertical plane and the bottom surface of the groove is used as the initial major axis direction (135) of the elliptical hole, and the initial major axis direction (135) of the elliptical hole is rotated counterclockwise in the vertical plane of the composite deflection line, and the rotation angle is the angle of the self-deflection angle, and the major axis direction (136) of the elliptical hole after self-deflection is obtained to determine the final forming section of the elliptical hole.

2. The design method of the elliptical hole composite deflection structure applied to the groove blade tip according to claim 1 is characterized in that: The bottom surface of the groove in S1 is a plane without curvature, and the bottom surface of the groove with curvature is projected as a plane without curvature.

3. The design method of the elliptical hole composite deflection structure applied to the groove blade tip according to claim 1, characterized in that: In S1, a higher-order derived mid-arc line is generated between derived mid-arc lines or between a derived mid-arc line and an inner contour line of a groove.

4. The design method of the elliptical hole composite deflection structure applied to the groove blade tip according to claim 1, characterized in that: In S1, a blade mid-arc line (121) is drawn according to the moving trajectory of the center of the inscribed circle of the outer contour line, and a derived mid-arc line (122) is drawn according to the moving trajectory of the center of the mid-arc line (121) and the inscribed circle of the inner contour line.

5. The design method of the elliptical hole composite deflection structure applied to the groove blade tip according to claim 1, characterized in that: The chord line of the blade top outer profile line is tangent to the leading and trailing edges of the outer profile line at the same time. The forehead line and the rear forehead line are made through the endpoints of the chord line. The forehead line and the rear forehead line are tangent to the leading and trailing edges of the outer profile line respectively, and are perpendicular to the chord line at the same time.

6. A design system for an elliptical hole composite deflection structure applied to a groove blade tip, characterized in that: It includes a reference line acquisition module, an origin position acquisition module, a composite deflection line acquisition module and a forming hole construction module; The reference line acquisition module is used to shape the bottom surface of the groove of the turbine moving blade (1), and determine the middle arc line (121) and the derived middle arc line (122) of the blade tip according to the inner contour line formed by the blade outer profile line and the groove shoulder wall (11); The origin position acquisition module makes a blade tip front line according to the chord length line of the blade tip outer profile line, makes a line parallel to the blade tip front line by given distance parameters, and determines the origin position of the cooling hole (13) according to the intersection of the line parallel to the blade tip front line and the mid-arc line (121) or the derived mid-arc line (122); The composite deflection line acquisition module is used to make a vertical line of the bottom surface of the groove through the origin of the cooling hole (13), perform three-dimensional decomposition at the origin of the cooling hole (13) according to the three-dimensional projection principle, and construct the composite deflection line by the inverse three-dimensional projection method, respectively establish the vertical plane, tangent plane and parallel plane of the middle arc line (121), or derive the vertical plane, tangent plane and parallel plane of the middle arc line (122); specify the radial deflection angle and the axial deflection angle, respectively determine the radial deflection line (132) in the vertical plane of the middle arc line (121) or the derived middle arc line (122) , an axial deflection line (133) in a section of a center arc line (121) or a derived center arc line (122), combined with a finite length groove bottom surface perpendicular line (131), to determine a composite deflection line (134) according to a vector synthesis principle; the direction of the composite deflection angle is determined by using a radial deflection angle and an axial deflection angle, wherein the radial deflection angle is the angle between the perpendicular line of the cooling hole origin and the radial deflection line, and is located in the perpendicular plane of the center arc line or the derived center arc line; and the axial deflection angle is the angle between the perpendicular line of the cooling hole origin and the axial deflection line, and is located in the section of the center arc line or the derived center arc line; The forming hole construction module is used to specify the self-deflection angle of the major axis of the elliptical hole in the vertical plane of the composite deflection line (134), determine the forming section of the elliptical hole, and finally build the forming hole in combination with the direction of the composite deflection line (134), and the self-deflection angle is located in the vertical plane of the composite deflection line; the initial major axis direction of the elliptical hole should be parallel to the bottom surface of the groove, and in the vertical plane of the composite deflection line of the origin of the supercooling hole, the intersection line of the vertical plane and the bottom surface of the groove is used as the initial major axis direction (135) of the elliptical hole, and the initial major axis direction (135) of the elliptical hole is rotated counterclockwise in the vertical plane of the composite deflection line, and the rotation angle is the self-deflection angle, and the major axis direction (136) of the elliptical hole after self-deflection is obtained to determine the final forming section of the elliptical hole.

7. A computer device, characterized in that: It includes a processor and a memory, the memory is used to store a computer executable program, the processor reads the computer executable program from the memory and executes it, and when the processor executes the computer executable program, it can implement the elliptical hole composite deflection structure design method applied to the groove blade top as described in any one of claims 1 to 5.

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