Coupling parameterization design method and system for trailing edge double-slit and turbulent flow structure

Abstract

The invention relates to a coupling parameterization design method and system of a trailing edge double-slit and turbulent flow structure, and belongs to the field of turbine blade computer aided design. The method comprises the steps that on the basis of pressure side and suction side molded lines of a trailing edge cavity, an S1 flow surface technology is adopted for conducting parametric modeling on a half-crack structure and a full-crack structure; determining the distribution rule of the double slits along the blade height through blade height dimensionless processing; and spoiler column structures are arranged on the unfolding surfaces of the trailing edge cavity and the laminate cavity, so that a double-slit trailing edge system coupled with spoiler columns is formed. The system realizes automatic modeling of the process through a layering module. A laminate cavity is adopted as an air supply source, and a full-split-seam and half-split-seam coupled double-split-seam form is constructed: air is supplied to the full-split seam by the laminate cavity, and air is supplied to the half-split seam by the trailing edge cavity. The laminated plate cavity extends to the rear part of the suction side throat part in a breakthrough manner, so that the area is effectively cooled, the air film covering effect is enhanced through the turbulent flow columns, and the excellent cooling performance can still be maintained even if the slit width of the full-split slit is relatively small.

Description

Technical Field

[0001] The present invention belongs to the technical field of computer software-aided design of aero-engine and gas turbine turbine blades, and particularly relates to a parametric design method and system for coupling a double-split trailing edge and a spoiler structure. Background Art

[0002] With the continuous iterative development of aero-engine technology, the total inlet temperature of aero-engine turbines is increasing day by day. At present, the inlet temperature of advanced aero-engine turbines has exceeded 2200K, which is much higher than the temperature that the turbine blade material can withstand. Therefore, higher requirements are put forward for the cooling design of turbine blades. Since the trailing edge of the blade is relatively thin and it is not suitable for internal cooling, the trailing edge split is mostly used to reduce the temperature in the trailing edge area. However, since the cold air in the trailing edge area comes from the chamber, when the cold air enters the trailing edge split, the temperature of the cold air has been increased once, and the quality of the cold air has decreased, resulting in a decrease in the cooling effect. Therefore, higher requirements are put forward for the cooling effect of the trailing edge split.

[0003] The currently used trailing edge splits are mainly divided into two types: full split and half split, and their main cold air source is the chamber near the trailing edge. Comparing the two chambers, the cooling effect of the full split is better than that of the half split. However, due to the requirements of the aerodynamic characteristics of the turbine blade, the trailing edge thickness of the blade cannot be too thick, which causes difficulties in arranging the full split structure. If the slit width of the full split structure is too narrow, a good cooling effect cannot be achieved. The half split structure can avoid the problem of increasing the trailing edge thickness of the blade, but its cooling effect on the trailing edge area, especially the suction side trailing edge, is insufficient. At the same time, due to the characteristics of the main flow on the suction side of the turbine blade surface, which has a fast flow rate and a low pressure, after arranging the cooling holes, most of the cold air will flow out from this position, resulting in insufficient cooling of the pressure side surface. At the same time, due to the too fast flow rate, a greater mixing loss will be brought. Therefore, it is not suitable to arrange the cooling structure at the position behind the suction side, and it is also difficult to effectively cool this position.

[0004] The Chinese patent with the publication number CN 111156053 A discloses "a trailing edge split and deflected slot structure and cooling method based on a gas turbine blade". However, it focuses on considering the aerodynamic and cooling characteristics of the trailing edge. However, its structure is similar to the traditional semi-split slot, resulting in insufficient cooling in the region near the trailing edge on the suction side. At the same time, vibration may occur at the outlet of the trailing edge split slot, affecting the blade strength performance. The Chinese patent with the publication number CN 113374534 A discloses a "trailing edge split slot shaping method for turbine blades", which focuses on solving the problems of controlling dimensions such as the thickness of the suction side and pressure side at the trailing edge. However, there is a correlation between the outlet width of the trailing split slot and the narrowest part of its channel in this structure. This will lead to the need to extend the pressure side forward more to ensure the cold air flow at the trailing edge when the trailing edge is thinner, resulting in an overly large outlet cross-sectional area and greater aerodynamic losses. And the trailing edge split slot structure in the Chinese patent with the publication number CN115478904 A is too complex, bringing greater difficulties to manufacturing. Summary of the Invention

[0005] To solve or mitigate the problems mentioned in the background art, the present invention provides a parametric design method for coupling a trailing edge double split slot and a spoiler structure, which supplies gas through a double-layer wall blade lamina cavity and a trailing edge cavity respectively, realizing a double split slot form that couples a full split slot and a semi-split slot. Since the present invention couples two split slot structures, even if the opening of the full split slot structure is narrow, a good cooling effect can be maintained. At the same time, due to the extension of the arrangement position of the lamina cavity, better cooling can also be achieved at the position behind the suction side throat.

[0006] In view of the above expectations, in the first aspect, the present invention proposes a parametric design method for coupling a trailing edge double split slot and a spoiler structure, including the following steps: Perform S1 stream surface shaping on the semi-split slot structure in the double split slot structure through the pressure side and suction side profiles of the trailing edge cavity; Use the lamina cavity close to the trailing edge as the gas supply cavity to perform S1 stream surface shaping on the full split slot structure involved in the double split slot structure; Nondimensionalize the blade along the blade height direction, and determine the distribution of the trailing edge split slot along the blade height direction through the distance from the trailing edge split slot to the upper and lower end walls of the blade; Based on the trailing edge cavity and the lamina cavity, nondimensionally expand and arrange the spoiler columns at the trailing edge split slot; thus obtaining a double split slot trailing edge structure with a combined arrangement of a coupled spoiler structure.

[0007] Furthermore, for the S1 stream surface modeling of the half-split structure in the double-split structure through the pressure side and suction side profiles of the trailing edge chamber, the following steps are included: Take the suction side profile of the blade outer wall surface, and offset it inward according to the same thickness distribution law of the inner wall surface of the blade chamber as the suction side profile of the half-split structure. Determine the opening width of the trailing edge half-split according to design experience, and further offset it inward based on the offset profile. The offset distance is the opening width. Take the pressure side profile of the blade outer wall surface, and also offset it inward according to the same thickness distribution law of the inner wall surface of the blade chamber. Solve the intersection point of the pressure side inner wall profile of the trailing edge split part and the pressure side inner wall profile of the chamber part after offset, and use this intersection point as the inflection point between the trailing edge chamber through-section part and the trailing edge split. The pressure side part of the trailing edge split is composed of the offset suction side profile before the inflection point and the twice-offset pressure side profile after the inflection point. The suction side part is composed of the offset suction side profile.

[0008] Furthermore, a tail cut is performed at the position of the trailing edge arc.

[0009] Furthermore, for the S1 stream surface modeling of the full-split structure involved in the double-split structure with the lamina chamber near the trailing edge as the air supply chamber, the following steps are included: Arrange a lamina chamber in the area near the trailing edge on the suction side. The near-trailing-edge side of the lamina chamber extends along the outer wall surface profile of the suction side towards the trailing edge until it passes through the trailing edge, and a split is opened on the trailing fillet to form the full-split structure in the double-split. The width of the double-split is the same as the width of the lamina chamber.

[0010] Furthermore, the blade is dimensionless processed along the blade height direction. The distribution of the trailing edge split along the blade height direction is determined by the distance from the trailing edge split to the upper and lower end walls of the blade, including: The blade height is 1, and the number of trailing edge splits is determined. Respectively, give the distance from the split at the uppermost position to the blade flow path casing and the distance from the split at the lowermost position to the blade flow path hub surface to determine the range of the opening positions of the trailing edge splits. Solve the opening positions of each trailing edge split through the interpolation method. The sum of the spacings between all trailing edge splits is the same as the initially delimited distribution range of the trailing edge splits. After determining the distribution position of each trailing edge split, give the height of each trailing edge split along the blade height. Complete the parametric layout of the trailing edge split along the blade height.

[0011] Furthermore, the interpolation method can be selected according to the actual layout of the trailing edge splits. If there is no special requirement, linear interpolation is selected. If a relatively dense distribution near the blade root side is required, quadratic function interpolation is used.

[0012] Further, the spoiler structure at the trailing edge slit is arranged in a dimensionless manner based on the trailing edge chamber and the lamina chamber, including: the chamber connecting the trailing edge slit and the lamina chamber is treated in the same way. On the S1 flow surface, taking the starting position of the chamber close to the leading edge as 0 and the ending position of the chamber close to the trailing edge as 1, the cross-section of the chamber is dimensionless processed, and the dimensionless value of the distribution position of the spoiler is given to complete the positioning of the spoiler on the cross-section of the chamber; in the blade height direction, similar to the definition form of the trailing edge slit, the blade height is dimensionless processed, and the distances from the uppermost spoiler to the casing of the blade flow passage and from the lowermost spoiler to the hub surface of the blade flow passage are given respectively to determine the distribution ranges of the uppermost spoiler and the lowermost spoiler. The specific positions of the centers of each spoiler in the middle are determined by the interpolation method. Finally, the diameter of each spoiler is given to complete the positioning of the spoiler along the blade height direction, and adjacent rows of spoilers are arranged at intervals and cross-arranged.

[0013] In a second aspect, the present invention provides a parametric design system for a trailing edge double slit and spoiler structure, including a semi-slit structure design module, a full-slit structure design module for the lamina chamber, and a spoiler design module; The semi-slit structure design module is used to perform S1 flow surface modeling on the semi-slit structure in the double-slit structure through the pressure side and suction side profiles of the trailing edge chamber; The full-slit structure design module for the lamina chamber is used to perform S1 flow surface modeling on the full-slit structure involved in the double-slit structure with the lamina chamber close to the trailing edge as the air supply chamber; The spoiler design module is used to perform dimensionless processing on the blade along the blade height direction, determine the distribution of the trailing edge slit along the blade height direction through the distances from the trailing edge slit to the upper and lower end walls of the blade; arrange the spoiler structure at the trailing edge slit in a dimensionless manner based on the trailing edge chamber and the lamina chamber, and then obtain the double-slit trailing edge structure with the combined arrangement of the coupled spoiler structure.

[0014] In a third aspect, the present invention can also provide a computer device, including a processor and a memory. The memory is used to store computer-executable programs. The processor reads the computer-executable programs from the memory and executes them. When the processor executes the computer-executable programs, it can implement the parametric design method for the coupled trailing edge double slit and spoiler structure of the present invention.

[0015] At the same time, a computer-readable storage medium is provided. A computer program is stored in the computer-readable storage medium. When the computer program is executed by the processor, it can implement the parametric design method for the coupled trailing edge double slit and spoiler structure of the present invention.

[0016] Compared with the current trailing edge slotting technology, the present invention has at least the following advantages: First, the proposed trailing edge double slot structure is defined in a parametric manner, with clear physical meanings for all parameters and no interference; the above parametric definition can be used to conveniently optimize the structure finely. Second, due to the low pressure at the position behind the throat, arranging film holes at this position will cause most of the cold air to flow out from this position, resulting in insufficient cooling on the pressure side. At the same time, the gas flow velocity is large at the position behind the throat, and the mixing of cold air and the mainstream will bring greater aerodynamic losses. For these two reasons, a lamellar cavity cannot be arranged at the position behind the throat for more effective cooling; while the present invention adopts the form of double slots, which can avoid the above problems and cool more fully the high-temperature areas that are not easily cooled at the tail, especially the suction side position behind the throat; in the present invention, the turbulators and the trailing edge slots adopt the same blade height definition form, which is convenient to realize the mutual cooperation between the turbulators and the trailing edge slots in the blade height direction and between the full slot and the half slot of the double slots, thereby obtaining a better cooling effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the above-mentioned invention content, the following drawings are given. The drawings are based on a certain blade and adopt a specific implementation case of the present invention. Relevant designers can use these drawings as a reference to apply the present invention to various different air-cooled turbine blades.

[0018] Figure 1 Schematic diagram of the three-dimensional model of the parametric layout of the coupling of the trailing edge double slot and the turbulator structure proposed by the present invention; Figure 2 Schematic cross-sectional view of the trailing edge double slot structure proposed by the present invention, which respectively includes a half slot structure led out from the trailing edge chamber and a full slot structure led out from the lamellar chamber; Figure 3 Schematic diagram of the half slot structure led out from the trailing edge chamber in the trailing edge double slot structure proposed by the present invention; Figure 4 Schematic diagram of the full slot structure led out from the lamellar chamber in the trailing edge double slot structure proposed by the present invention; Figure 5 Parameter schematic diagram of the layout of the trailing edge slot structure along the blade height direction.

[0019] Figure 6 Layout parameter schematic diagram of the trailing edge slot coupling turbulator structure.

[0020] Description of the reference numerals: 1. Half slot structure; 11. Suction side profile of the half slot structure; 12. Intersection point; 13. Pressure side inner wall profile of the trailing edge slot part; 14. Pressure side inner wall profile of the chamber part; 2. Full slot structure; 21. Lamellar chamber; 3. Blade suction side; 4. Blade pressure side; 5. Turbulator. DETAILED DESCRIPTION OF THE INVENTION To more clearly illustrate the specific implementation methods and parameter selection suggestions in the actual cases of the present invention, the following provides a specific implementation case of implementing the present invention in a certain blade profile in combination with the attached drawings given by the present invention. The specific implementation case given below aims to explain and clarify the specific application methods of the present invention in actual aero-engine and gas turbine turbine blades, rather than limiting the specific content of the present invention. Simple adjustments and modifications made by relevant technicians without creativity to the selected parameters based on the present invention should be included within the protection scope of the patent application of the present invention.

[0021] The present invention proposes a double-split trailing edge structure with a coupled spoiler structure arrangement. The following introduces the specific implementation measures of the present invention in combination with the examples given in the attached drawings.

[0022] The present invention is applied to a turbine blade with a coupled trailing edge double-split and spoiler structure, provided with a gas supply cavity, and a cooling structure including a laminated cavity, impact holes, film holes, and trailing edge split seams; different from general turbine blades, in the present invention, a laminated cavity is also arranged in the area near the trailing edge after the throat of the turbine blade, but instead of performing film cooling outward through the film holes, it supplies gas to the trailing edge split seam structure together with the trailing edge gas supply cavity.

[0023] The double-layer wall blade laminated cavity and the trailing edge chamber are supplied with gas to achieve the coupling of full split seams and half split seams.

[0024] The present invention includes parametric design of three modules. The first module is the parametric design of the half split seam structure connected to the trailing edge chamber; the second module is the parametric modeling of the full split seam structure connected to the laminated cavity; the third module is, on the basis of completing the first two modules, relying on the chamber structure connected by the trailing edge split seam, to perform the dimensionless arrangement of turbulators, and to complete the coupled modeling design of the turbulator structure and the trailing edge split seam structure by selecting parameters.

[0025] The present invention extends the laminated cavity to the rear of the suction side throat, and through the combined gas supply of the full split seam (gas supply from the laminated cavity) and the half split seam (gas supply from the trailing edge chamber), expands the cooling coverage range. The turbulators are arranged based on the dimensionless method to optimize the air flow disturbance and film uniformity, and reduce the dependence on the width of the split seam. The rapid iteration of the laminated cavity and the split seam structure is realized through parametric modeling, reducing the design complexity.

[0026] To implement the three modules mentioned in the above present invention, the following four detailed steps are planned to complete the parametric design method of the double-split and spoiler structure given in the present invention. The three-dimensional visual effect after modeling is as shown in the attached Figure 1 as given. For each cross-section of the double-split structure, the profile line after modeling is as shown in the attached Figure 2 . The four detailed steps given by the present invention with a certain blade profile as a reference are specifically as follows: Step 1: Perform S1 stream surface modeling on the semi-slit structure in the double-slit structure mentioned in the present invention through the pressure side and suction side profiles of the trailing edge chamber.

[0027] As shown in the appendix Figure 3 , first select several important cross-sections as characteristic cross-sections. For example, at least select three cross-sections at the blade root, blade mid-span, and blade tip. In the selected characteristic cross-sections, first take out the suction side profile 3 and the pressure side profile 4 under the current cross-section. Offset the suction side profile 3 towards the inner side of the blade by a distance t1 to obtain the suction side profile 11 of the semi-slit structure, and trim off the part that extends beyond the pressure side of the blade. It should be noted that the offset distance t1 here is not arbitrarily selected, but should be given according to the distribution law of the chamber wall thickness to ensure the smooth transition at the transition position between the trailing edge slit and the trailing edge chamber.

[0028] Furthermore, after obtaining the suction side profile 11 of the semi-slit structure, offset the suction side profile 11 of the semi-slit structure towards the inner side of the blade by t2 to obtain the pressure side profile of the semi-slit structure. The parameter t2 here is relatively crucial and determines the opening size of the trailing edge slit, and can be given corresponding parameters according to the need of cold air distribution.

[0029] Furthermore, take out the pressure side profile 4 of the blade under the current cross-section, and offset the pressure side profile towards the inner side of the blade by t3 to obtain the pressure side profile at the connection position with the trailing edge slit. Here, t3 is the same as t1, and selecting t3 to be the same as the distribution law of the chamber pressure side wall thickness makes the offset profile smoothly transition with the chamber section. On this basis, solve the intersection point 12 between the inner wall profile 14 of the pressure side of the chamber part after offset and the inner wall profile 13 of the pressure side of the trailing edge slit part, and use this position as the transition section between the connection part of the trailing edge chamber and the trailing edge slit. Trim the first half of the inner wall profile 13 of the pressure side of the trailing edge slit part and the second half of the inner wall profile 14 of the pressure side of the chamber part with the intersection point 12, and finally connect the remaining parts of the two profiles to obtain the trailing edge slit modeling profile of the selected cross-section after modeling.

[0030] Step 2: Use the lamina chamber near the trailing edge as the air supply chamber to perform S1 stream surface modeling on the full-slit structure involved in the double-slit of the present invention.

[0031] As shown in the appendix Figure 4Taking the example shown, similar to the method in Step 1, first extract the blade suction side profile 3, pressure side profile 4, trailing edge chamber profile, and the profile 21 of the lamina chamber near the trailing edge from several important cross-sections. Based on the existing profiles, extend the inner and outer profiles of the lamina chamber along the blade suction side profile 3 on the blade surface to the trailing edge of the blade to form a full split structure. It should be noted here that the width of the trailing edge split is consistent with the width of the lamina chamber. Therefore, in the actual design process, the width of the lamina chamber should not be too wide, and the trailing edge should not be too thin to avoid the trailing edge split completely cutting off the blade trailing edge and affecting the aerodynamic characteristics.

[0032] Step 3: Dimensionless process the blade in the blade height direction, and determine the distribution of the trailing edge split along the blade height direction based on the distance from the trailing edge split to the upper and lower end walls.

[0033] The parametric modeling profile of the trailing edge split on the S1 flow surface is obtained by solving Steps 1 and 2 above. Next, it is necessary to determine its modeling range in the blade height direction. The specific positioning method in the blade height direction is as shown in the appendix Figure 5 given. First, obtain the blade height L0 at the position of the trailing edge split, and perform dimensionless processing on it, with the blade height as unit 1. On this basis, determine the dimensionless distance β1 from the uppermost trailing edge split to the blade flow passage casing, then the actual distance from this trailing edge split to the blade flow passage casing is ; Similarly, determine the dimensionless distance β2 from the lowermost trailing edge split to the blade flow passage hub surface, then the actual distance from this trailing edge split to the blade flow passage hub surface is . Determine the distribution range of the opening position of the trailing edge split through the above content. Further, the distribution law of the trailing edge split within this range can be given according to different requirements to determine the opening position of each trailing edge split. The one given in the appendix Figure 5 is a linear equidistant distribution. After determining the opening position, give the dimensionless height β3 of the trailing edge split to determine the size of the trailing edge split in the blade height direction, so as to adjust the cooling range, cold air flow rate, etc. The actual height value of the trailing edge split is , and after completing the above content, the layout of the trailing edge split in the blade height direction is completed.

[0034] Step 4: Dimensionless expand the trailing edge chamber and the lamina chamber, and based on this, arrange the turbulator structure at the trailing edge split.

[0035] After completing the parametric modeling of the trailing edge split, based on this, carry out the parametric modeling of the turbulence structure matching with it. The modeling results in the specific implementation cases provided are as shown in Figure 6As shown in the figure. First, take the trailing edge cavity or the profile of the lamina cavity connected to the trailing edge split and perform dimensionless processing. The dimensionless processing method in the blade height direction is the same as that of the trailing edge split. The advantage of such an operation is that it is convenient to realize various mutual relationships between the trailing edge split and the turbulators. It is preferably considered that the turbulators close to the trailing edge split are directly opposite to the trailing edge split to increase the disturbance, thereby enhancing the cooling effect. On the S1 streamline, the length in the airfoil direction from the leading edge to the trailing edge is dimensionlessized, with the width W0 of the cavity as the unit 1. On this basis, the position of the turbulator is determined by giving the dimensionless value λ of the turbulator in this direction, and its actual arrangement position is . Different rows of turbulators can be arranged as needed. The present invention recommends two to three rows, and the adjacent rows of turbulators are arranged in a staggered pattern. The last row of turbulators adopts the same axial positioning form as the corresponding trailing edge split to ensure a better trailing edge cooling effect.

[0036] Thus, the specific implementation of the present invention in the given case in the provided drawings is completed.

[0037] Embodiment 2. The present invention also provides a parametric design system for a trailing edge double split and turbulator structure, including a semi-split structure design module, a full-split structure design module for the lamina cavity, and a turbulator design module; The semi-split structure design module is used to perform S1 streamline modeling on the semi-split structure in the double split structure through the pressure side and suction side profiles of the trailing edge cavity. The full-split structure design module for the lamina cavity is used to perform S1 streamline modeling on the full-split structure involved in the double split structure with the lamina cavity near the trailing edge as the air supply cavity. The turbulator design module is used to perform dimensionless processing on the blade in the blade height direction, determine the distribution of the trailing edge split in the blade height direction through the distances from the trailing edge split to the upper and lower end walls of the blade; arrange the turbulator structure at the trailing edge split based on the dimensionless expansion of the trailing edge cavity and the lamina cavity, and then obtain a double split trailing edge structure with a coupled turbulator structure jointly arranged.

[0038] The structure obtained by the present invention is respectively supplied with air through the double-layer wall blade lamina cavity and the trailing edge cavity. The cold air enters the trailing edge cavity from the air system, and the cold air flows in the blade height direction. Part of the cold air flows out through the impingement hole - lamina cavity - film hole structure on the blade surface to perform film cooling on the blade surface, and the remaining cold air is used for the trailing edge split cooling of the structure obtained by the present invention; a part of the remaining cold air enters the pressure side semi-split structure, and after passing through the turbulator, flows out from the outlet and mixes with the mainstream; another part of the cold air first enters the lamina cavity through the impingement hole on the inner wall of the lamina cavity near the trailing edge of the suction side, and then flows out from the full-split structure in the present invention.

[0039] In summary, the parametric design method for the coupling of trailing-edge double split slots and spoiler structures provided by the present invention is based on the profiles of the pressure side and suction side of the trailing-edge chamber. The S1 stream surface technology is used to parametrically model the half-split slot and full-split slot structures respectively. The distribution law of the double split slots along the blade height is determined through non-dimensionalization processing of the blade height. The spoiler post structures are arranged on the developed surfaces of the trailing-edge chamber and the lamina chamber to form a double split slot trailing-edge system with coupled spoiler posts. The system realizes the automatic modeling of the above process through a hierarchical module. The lamina chamber is used as the air supply source to construct a double split slot form that couples the full split slot and the half split slot: the full split slot is supplied with air from the lamina chamber, and the half split slot is supplied with air from the trailing-edge chamber. Breakthroughly, the lamina chamber is extended to the rear of the suction side throat, enabling effective cooling in this area. The spoiler posts enhance the film coverage effect, so that excellent cooling performance can still be maintained even when the opening width of the full split slot is small.

[0040] On the other hand, the present invention provides a computer-readable storage medium, in which a computer program is stored. When the computer program is executed by a processor, it can implement the parametric design method for the coupling of the trailing-edge double split slots and spoiler structures of the present invention.

[0041] The present invention can also provide a computer device, including a processor and a memory. The memory is used to store computer-executable programs. The processor reads the computer-executable programs from the memory and executes them. When the processor executes the computer-executable programs, it can implement the parametric design method for the coupling of the trailing-edge double split slots and spoiler structures of the present invention.

[0042] The computer device can be a laptop computer, a desktop computer or a workstation.

[0043] The processor can be a central processing unit (CPU), a graphics processing unit (GPU), a digital signal processor (DSP), an application-specific integrated circuit (ASIC) or a field-programmable gate array (FPGA).

[0044] For the memory of the present invention, it can be an internal storage unit of a laptop computer, a desktop computer or a workstation, such as a memory or a hard disk; it can also use an external storage unit, such as a mobile hard disk or a flash card.

[0045] A computer-readable storage medium may include a computer storage medium and a communication medium. The computer storage medium includes volatile and non-volatile, removable and non-removable media implemented by any method or technology for storing information such as computer-readable instructions, data structures, program modules, or other data. The computer-readable storage medium may include: read-only memory (ROM), random access memory (RAM), solid state drives (SSD), or optical discs, etc. Among them, the random access memory may include resistive random access memory (ReRAM) and dynamic random access memory (DRAM).

[0046] The above content is only a specific implementation manner of the present invention, and the protection scope of the present invention cannot be limited thereby. Any simple adjustments and modifications made by relevant researchers and technicians in the technical field familiar with the present invention fall within the protection scope of the claims of the present invention.

Claims

1. A parametric design method for the coupling of trailing edge double split seams and flow disturbance structures, characterized in that It includes the following steps: Perform S1 stream surface modeling on the semi-split slot structure in the double split slot structure through the pressure side and suction side profiles of the trailing edge chamber; Take the lamina chamber near the trailing edge as the air supply chamber and perform S1 stream surface modeling on the full split slot structure involved in the double split slot structure; Nondimensionalize the blade in the blade height direction and determine the distribution of the trailing edge split slot in the blade height direction based on the distance from the trailing edge split slot to the upper and lower end walls of the blade; Arrange the spoiler columns at the trailing edge split slot based on the nondimensional expansion of the trailing edge chamber and the lamina chamber; thus, a double split slot trailing edge structure with a combined layout of the coupled spoiler structure is obtained.

2. The parametric design method for coupling the trailing-edge double split slots and the flow disturbing structure according to claim 1, wherein Performing S1 stream surface modeling on the semi-split slot structure in the double split slot structure through the pressure side and suction side profiles of the trailing edge chamber includes: taking the suction side profile of the blade outer wall surface, offsetting it inward according to the same thickness distribution law of the inner wall surface of the blade chamber as the suction side profile of the semi-split slot structure, determining the opening width of the trailing edge semi-split slot according to design experience, and further offsetting it inward based on the offset profile, with the offset distance being the opening width; taking the pressure side profile of the blade outer wall surface, also offsetting it inward according to the same thickness distribution law of the inner wall surface of the blade chamber, solving the intersection point of the pressure side inner wall profile of the trailing edge split slot part and the pressure side inner wall profile of the chamber part after offsetting, and taking the intersection point as the inflection point of the two parts of the trailing edge chamber through section and the trailing edge split slot. The pressure side part of the trailing edge split slot is composed of the suction side offset profile before the inflection point and the pressure side profile offset twice after the intersection point; the suction side part is composed of the suction side profile after offsetting.

3. The parametric design method for the coupling of the trailing edge double split slots and the flow disturbing structure according to claim 2, characterized in that Perform tail cutting at the position of the trailing arc.

4. The parametric design method for coupling the trailing edge double split slot and the spoiler structure according to claim 1, characterized in that Taking the lamina chamber near the trailing edge as the air supply chamber and performing S1 stream surface modeling on the full split slot structure involved in the double split slot structure includes: arranging a lamina chamber in the area near the trailing edge of the suction side, extending the near trailing edge side of the lamina chamber along the outer wall surface profile of the suction side towards the trailing edge until it passes through the trailing edge, and opening a split slot on the trailing fillet to form the full split structure in the double split slot. The width of the double split slot is the same as the width of the lamina chamber.

5. The parametric design method for coupling the trailing edge double split slot and the flow disturbing structure according to claim 1, characterized in that Nondimensionalize the blade in the blade height direction and determine the distribution of the trailing edge split slot in the blade height direction based on the distance from the trailing edge split slot to the upper and lower end walls of the blade includes: Taking the blade height as 1 and determining the number of trailing edge split slots; Respectively specify the distance from the split slot at the uppermost position to the blade flow path casing and the distance from the split slot at the lowermost position to the blade flow path hub surface to determine the range of the opening positions of the trailing edge split slots; Solve the opening positions of each trailing edge split slot through interpolation. The sum of the spacings between all trailing edge split slots is the same as the initially defined trailing edge split slot distribution range; After determining the distribution position of each trailing edge split slot, specify the height of each trailing edge split slot in the blade height direction; Complete the parametric layout of the trailing edge split slot in the blade height direction.

6. The parametric design method for coupling the trailing edge double split and spoiler structure according to claim 1, wherein The interpolation method can be selected according to the actual layout of the trailing edge split slot. If there is no special requirement, linear interpolation is selected. If a relatively dense arrangement near the blade root side is required, quadratic function interpolation is used.

7. The parametric design method for coupling the trailing-edge double split slots and the flow disturbance structure according to claim 1, characterized in that Based on the trailing edge chamber and the lamina chamber, a non-dimensionalized deployment arrangement of turbulators at the trailing edge split is as follows: The chambers connecting the trailing edge split and the lamina chamber are treated in the same way. On the S1 flow surface, taking the starting position of the chamber near the leading edge as 0 and the ending position of the chamber near the trailing edge as 1, the cross-section of the chamber is non-dimensionally processed, and the non-dimensional values of the distribution positions of the turbulators are given to complete the positioning of the turbulators on the cross-section of the chamber. In the blade height direction, similar to the definition form of the trailing edge split, the blade height is non-dimensionally processed, and the distances from the uppermost turbulator to the casing of the blade passage and from the lowermost turbulator to the hub surface of the blade passage are given respectively to determine the distribution ranges of the uppermost and lowermost turbulators. The specific positions of the centers of each turbulator in the middle are determined by the interpolation method. Finally, the diameter of each turbulator is given to complete the positioning of the turbulators along the blade height direction, and adjacent rows of turbulators are arranged at intervals and cross-arranged.

8. A parametric design system for trailing edge double split slots and flow disturbance structures, characterized in that, It includes a semi-split structure design module, a full-split structure design module of the lamina chamber, and a turbulator design module; The semi-split structure design module is used to perform S1 flow surface modeling on the semi-split structure in the double-split structure through the pressure side and suction side profiles of the trailing edge chamber; The full-split structure design module of the lamina chamber is used to perform S1 flow surface modeling on the full-split structure involved in the double-split structure with the lamina chamber near the trailing edge as the air supply chamber; The turbulator design module is used to non-dimensionally process the blade along the blade height direction, determine the distribution of the trailing edge split along the blade height direction through the distances from the trailing edge split to the upper and lower end walls of the blade; based on the trailing edge chamber and the lamina chamber, a non-dimensionalized deployment arrangement of turbulators at the trailing edge split is carried out, and then a double-split trailing edge structure with a coupled turbulator structure jointly arranged is obtained.

9. A computer device, characterized in that, It includes a processor and a memory. The memory is used to store computer-executable programs. The processor reads part or all of the computer-executable programs from the memory and executes them. When the processor executes part or all of the computer-executable programs, it can implement the trailing edge double-split and turbulator structure coupling parametric design method described in any one of claims 1-7.

10. A computer-readable storage medium, characterized in that, A computer program is stored in a computer-readable storage medium. When the computer program is executed by a processor, it can implement the trailing edge double-split and turbulator structure coupling parametric design method described in any one of claims 1-7.

Images