Design method and device of cold air injection structure and cold air injection structure
By designing the air-conditioning injection structure, the air-conditioning injection parameters and cascade energy loss model of the turbine blades are optimized, and the problems of surface thickening and fluid separation caused by the extension shock wave in the trailing edge of the turbine blade are solved, and the turbine efficiency and blade life of the gas turbine are improved.
Patent Information
- Application Number
- CN202510542643.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-28
- Publication Date
- 2025-08-12
AI Technical Summary
In gas turbine design, the thickening of the surface layer and fluid separation caused by the extension shock wave in the trailing edge of the turbine blade increase the loss of the blade type and trail loss, affecting the turbine performance.
Design the air-conditioning injection structure, by determining the distribution parameters of the extension shock wave in the tail edge of the adjacent blades of the turbine blade, optimizing the grooved parameters of the air-conditioning injection structure on the suction surface, and combining the cascade energy loss simulation model, the initial design parameters are optimized to obtain the target design parameters, including the target structure parameters and the air-conditioning blowing ratio.
It effectively suppresses the thickening of the surface layer and fluid separation caused by the excitation wave in the tail edge, reduces aerodynamic losses, improves turbine efficiency, extends the life of the blade, and avoids unnecessary airflow losses and energy consumption.
Smart Images
Figure CN120470701A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of gas turbine design, and in particular to a design method and device for a cold air injection structure, and a cold air injection structure. Background Art
[0002] In the design of advanced heavy-duty gas turbines, to improve turbine component power and efficiency, designers need to significantly increase the aerodynamic loads on the turbine blades. This design trend forces the turbine cascade flow path into a transonic regime during operation. Transonic flow generates two shock waves at the trailing edge of the blade: an inward-extending shock wave and an outward-extending shock wave. The inward-extending shock wave intersects with the suction surface of the adjacent blade on the pressure side of the blade, forming an adverse pressure gradient. This increases the boundary layer thickness on the suction surface of the blade and may even cause separation. This not only increases profile losses but also indirectly increases wake losses, thus affecting overall turbine performance. Summary of the Invention
[0003] The present application aims to solve one of the technical problems in the related art at least to a certain extent.
[0004] To this end, one purpose of the present application is to propose a design method for a cold air injection structure, including: determining the distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of the turbine blade on the suction surface of the turbine blade; determining the slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters; obtaining the initial design parameters of the cold air injection structure, and establishing a blade energy loss simulation model of the gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio; optimizing and simulating the initial design parameters based on the blade energy loss simulation model in combination with the slotting parameters to obtain the target design parameters when the blade energy loss meets the preset conditions, the target design parameters including the target structural parameters and the target cold air blowing ratio.
[0005] According to one embodiment of the present application, the cold air injection structure includes a first wall surface, a second wall surface, a cold air injection slot, and a third wall surface, wherein the cold air injection slot is used to inject cold air.
[0006] According to one embodiment of the present application, the first wall surface intersects with the suction surface to form an intersection line; the second wall surface intersects with the first wall surface to form an intersection line; the cold air injection slot intersects with the second wall surface to form an intersection line; the third wall surface intersects with the cold air injection slot to form an intersection line, and the third wall surface intersects with the suction surface to form an intersection line.
[0007] According to one embodiment of the present application, the third wall surface adopts a B-spline curve.
[0008] According to one embodiment of the present application, the target structural parameters include: the width of the cold air injection slot; the thickness between the second wall and the suction surface; the width of the second wall; and the axial length of the slot line corresponding to the cold air injection structure along the axial direction.
[0009] According to one embodiment of the present application, a method for determining the intersection line formed by the intersection of the third wall surface and the suction surface includes: taking each point on the slot line as a starting point, drawing a straight line along the axial direction toward the suction surface based on the axial length; and constructing the intersection line between the third wall surface and the suction surface based on the intersection of the straight line and the suction surface.
[0010] The second purpose of the present application is to propose a design device for a cold air injection structure, comprising: a first determination module for determining the distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of the turbine blade on the suction surface of the turbine blade; a second determination module for determining the slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters; a parameter acquisition module for acquiring the initial design parameters of the cold air injection structure, and establishing a blade energy loss simulation model of the gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio; a parameter optimization module for optimizing and simulating the initial design parameters based on the blade energy loss simulation model in combination with the slotting parameters to obtain the target design parameters when the blade energy loss meets the preset conditions, and the target design parameters include target structural parameters and a target cold air blowing ratio.
[0011] The third purpose of the present application is to propose a cold air injection structure, which is designed and generated using the above-mentioned design method of the cold air injection structure.
[0012] The fourth object of the present application is to provide a turbine blade, characterized in that the turbine blade is provided with a cold air injection structure designed and generated using the design method of the above-mentioned cold air injection structure.
[0013] The fifth object of the present application is to propose an electronic device, comprising: at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores instructions that can be executed by the at least one processor, and the instructions are executed by the at least one processor to implement the design method of the cold air injection structure as described in the embodiment of the first aspect of the present application.
[0014] The sixth object of the present application is to provide a non-transitory computer-readable storage medium, wherein the computer instructions are used to implement the design method of the cold air injection structure as described in the embodiment of the first aspect of the present application.
[0015] The seventh object of the present application is to provide a computer program product, comprising a computer program, which, when executed by a processor, implements the design method of the cold air injection structure as described in the embodiment of the first aspect of the present application.
[0016] The present application achieves at least the following beneficial effects: the design method of the cold air injection structure introduced in the present application can effectively perform local cooling, avoid damage to the turbine blades due to overheating in a high-temperature environment, extend the service life of the blades, and meet the needs of blade surface cooling; at the same time, the cold air injection structure designed in the present application can effectively suppress the boundary layer thickening and fluid separation caused by the inward shock wave of the trailing edge, reduce aerodynamic losses, and improve the overall efficiency of the turbine; meet the needs of blade cooling without introducing too much additional active jets, avoiding unnecessary airflow losses and energy consumption. BRIEF DESCRIPTION OF THE DRAWINGS
[0017] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:
[0018] Figure 1 This is a schematic diagram of a design method for a cold air injection structure shown in an embodiment of the present application.
[0019] Figure 2 This is a schematic diagram showing a cold air injection structure designed on a turbine blade according to an embodiment of the present application.
[0020] Figure 3 This is a schematic diagram of a cold air injection structure shown in an embodiment of the present application.
[0021] Figure 4 This is a schematic cross-sectional view of a cold air injection structure on a turbine blade along the radial direction, shown in one embodiment of the present application.
[0022] Figure 5 This is a schematic diagram for introducing target structure parameters according to an embodiment of the present application.
[0023] Figure 6 This is a schematic diagram showing another cold air injection mechanism designed on a turbine blade according to an embodiment of the present application.
[0024] Figure 7 This is a verification diagram shown in an embodiment of the present application.
[0025] Figure 8 This is a schematic diagram of a design device for a cold air injection structure shown in one embodiment of the present application.
[0026] Figure 9 This is a schematic diagram of an electronic device shown in one embodiment of the present application.
[0027] Meaning of the reference numerals:
[0028] 1-Suction surface of turbine blade; 2-First wall surface; 3-Second wall surface; 4-Cold air injection slot; 5-Third wall surface; 6-Pressure surface of turbine blade; 7-Leading edge of turbine blade; 8-Trailing edge of turbine blade; 9-Slot line of cold air injection structure; 10-Other wall surfaces formed by cold air injection structure and suction surface. DETAILED DESCRIPTION
[0029] The following describes in detail embodiments of the present application, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.
[0030] Figure 1 This is a schematic diagram of a design method for a cold air injection structure shown in this application. Figure 1 As shown, the design method of the cold air injection structure includes the following steps:
[0031] S101, determining distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of the turbine blade on the suction surface of the turbine blade.
[0032] S102: Determine slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters.
[0033] The slotting parameters include the slotting position of the slotting line and the slotting length corresponding to the slotting line.
[0034] When setting the slotting parameters, it should be considered that the jet position of the cold air jet structure is near the upstream of the intersection of the suction surface of the turbine blade and the trailing edge inward extension shock wave generated by the adjacent blade.
[0035] S103, obtaining initial design parameters of the cold air injection structure, and establishing a blade cascade energy loss simulation model of the gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio.
[0036] The initial design parameters of the cold air injection structure may be fixed parameters.
[0037] Among them, a gas turbine blade energy loss simulation model can be established based on the relevant design parameters of the gas turbine.
[0038] S104 , optimizing and simulating the initial design parameters based on the cascade energy loss simulation model and the slotting parameters to obtain target design parameters when the cascade energy loss meets preset conditions, the target design parameters including target structural parameters and a target cooling air blowing ratio.
[0039] The initial design parameters are optimized and simulated based on the blade energy loss simulation model combined with the slotting parameters. The design parameters corresponding to the lowest blade energy loss or when the preset range is met are taken as the target design parameters. The final cold air injection structure is designed based on the target design parameters combined with the slotting parameters.
[0040] The target air blowing ratio refers to the ratio of the cooling air flow guided by the cold air injection structure for cooling the gas turbine to the overall air flow of the gas turbine.
[0041] The design method of the cold air injection structure introduced in the embodiment of the present application can effectively perform local cooling, avoid damage to the turbine blades due to overheating in a high-temperature environment, extend the service life of the blades, and meet the needs of blade surface cooling; at the same time, the cold air injection structure designed in the present application can effectively suppress the boundary layer thickening and fluid separation caused by the inward shock wave of the trailing edge, reduce aerodynamic losses, and improve the overall efficiency of the turbine; meet the needs of blade cooling without introducing too many additional active jets, avoiding unnecessary airflow losses and energy consumption.
[0042] To further explain the cold air injection structure, Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 Provide a detailed introduction.
[0043] The following first introduces the meaning of the possible numbers involved: 1-suction surface of the turbine blade; 2-first wall surface; 3-second wall surface; 4-cold air injection slot; 5-third wall surface; 6-pressure surface of the turbine blade; 7-leading edge of the turbine blade; 8-trailing edge of the turbine blade; 9-slot line of the cold air injection structure; 10-other wall surfaces formed by the cold air injection structure and the suction surface.
[0044] Figure 2 This is a schematic diagram of a cold air injection structure designed on a turbine blade as shown in this application. Figure 2 As shown, the cold air injection structure ( Figure 2 The six rectangular structures in the figure represent the cooling air injection structure. The cooling air injection structure can be designed at multiple locations along the blade height direction on the suction surface of the turbine blade. The slot line 9 of the cooling air injection structure (the slot line refers to Figure 2 The leftmost line of the rectangle in Figure 2 It is represented as a line along the blade height direction, which can also be understood as that after determining the target structural parameters of the cold air injection structure, the cold air injection structure can be obtained by slotting along the slotting line based on the target structural parameters.
[0045] Figure 3 This is a schematic diagram of a cold air injection structure shown in this application. Figure 3 As shown, the cold air injection structure includes a first wall surface 2, a second wall surface 3, a cold air injection slot 4 and a third wall surface 5, wherein the cold air injection slot is used for injecting cold air.
[0046] Among them, the first wall surface 2 and the suction surface 1 intersect to form an intersection line, that is, the intersection line is Figure 3 The slotted line 9 of the cold air injection structure.
[0047] The second wall surface 3 intersects with the first wall surface 2 to form an intersection line.
[0048] The cold air injection slot 4 intersects with the second wall surface 3 to form an intersection line.
[0049] The third wall surface 5 intersects with the cold air injection slot 4 to form an intersection line, and the third wall surface 5 intersects with the suction surface 1 to form an intersection line.
[0050] The third wall surface 5 adopts a B-spline curve to ensure that the blade profile at the cold air injection structure position is smooth.
[0051] The first wall surface 2 can be either a plane or a curved surface, depending on the design or use requirements.
[0052] The second wall surface 3 can be either a plane or a curved surface, depending on the design or use requirements.
[0053] The cold air injection slot 4 can be either a flat surface or a curved surface, depending on the design or use requirements.
[0054] in, Figure 3 In addition to the cold air injection structure, the figure also shows other wall surfaces 10 formed on the turbine blade by the cold air injection structure after a groove is dug out at a certain position on the turbine blade to form the cold air injection structure.
[0055] Figure 4 This is a schematic diagram of a radial section of a cold air injection structure on a turbine blade shown in this application. Figure 4 The cooling air injection structure is partially enlarged and shown in Figure 4 .
[0056] like Figure 4 As shown, the pressure surface of the turbine blade is represented by label 6, the leading edge of the turbine blade is represented by label 7, the trailing edge of the turbine blade is represented by label 8, the suction surface of the turbine blade is represented by label 1, and the cold air injection structure is designed on the suction surface 1 of the turbine blade.
[0057] like Figure 4 As shown, wherein: the first wall 2 is Figure 4In addition to the reference numeral 2, line AB can also be used to assist understanding. Line AB represents the first wall 2 on the cross-sectional diagram. As described above, since the first wall 2 can be either a plane or a curved surface, line AB can be either a straight line or a curve.
[0058] like Figure 4 As shown, wherein: the second wall 3 is Figure 4 In addition to the reference numeral 3, line BC can also be used to assist understanding. Line BC is a curve representing the second wall 3 on the cross-sectional diagram. As described above, since the second wall 3 can be either a plane or a curved surface, line BC can be either a straight line or a curve.
[0059] like Figure 4 As shown, wherein: the cold air injection slot 4 is Figure 4 In addition to the symbol 4, the CD line can also be used to assist understanding. The CD line is a curve representing the cold air injection slot 4 on the cross-sectional diagram. As mentioned above, since the cold air injection slot 4 can be either a flat surface or a curved surface, the CD line can be either a straight line or a curved line.
[0060] like Figure 4 As shown, wherein: the third wall 5 is Figure 4 In addition to the symbol 5, the DE line can also be used to assist understanding. The DE line represents the third wall 5 on the cross-sectional diagram. Point E can be understood as the intersection of the third wall 5 and the suction surface 1 on this cross-sectional diagram. As mentioned above, the DE line is a B-spline curve.
[0061] in, Figure 4 The dotted line portion is the original curve of the suction surface 1 at the cold air injection structure before grooving. After grooving the cold air injection structure at this position on the turbine blade, the original dotted line portion on the cross-sectional diagram has been dug out and no longer exists, so it is represented by a dotted line.
[0062] The cold air injection slot 4 is used to inject cold air, such as Figure 4 As shown, the cold air ejected through the cold air ejection slots 4 can pass through more areas of the suction surface of the turbine blade, thereby improving the cooling effect of the turbine blade.
[0063] Figure 5 This is a schematic diagram used to introduce the target structure parameters shown in this application, such as Figure 5 As shown, the target structure parameters include the following 4 parameters:
[0064] The first parameter: the width of the cold air injection slot, that is, Figure 4 H in SLOT length.
[0065] The second parameter: the thickness between the second wall and the suction surface, that is, Figure 4 H in LIP Since a wall is formed between the second wall surface 3 and the suction surface 1, the thickness of this wall can be constant or non-constant, that is, the thickness between the second wall surface and the suction surface can be constant or gradually changing, which means that H LIP The value can be one or more.
[0066] The third parameter: the width of the second wall, that is Figure 4 L in LIP length.
[0067] The fourth parameter is the axial length of the slot line corresponding to the cold air injection structure along the axial direction, that is, Figure 4 S in M length.
[0068] Among them, the above introduces the axial length of the slotted line corresponding to the cold air injection structure on the suction surface along the axial direction, and then, taking each point on the slotted line as the starting point, a straight line is drawn toward the suction surface along the axial direction based on the axial length; based on the intersection of the straight line and the suction surface, the intersection line between the third wall surface and the suction surface can be constructed, and then based on the wall surface in the shape of a B-spline curve, the intersection line is connected with another intersection line (the other intersection line here refers to the intersection line formed by the intersection of the third wall surface and the cold air injection slot) to obtain the third wall surface.
[0069] Figure 6 This is a schematic diagram of another cold air injection mechanism designed on a turbine blade as shown in this application. Figure 6 As shown, the slot lines of the cold air injection mechanism can also be designed to be inclined based on the blade height direction.
[0070] The cold air injection structure designed in the present application can effectively perform local cooling, avoid damage to turbine blades due to overheating in a high-temperature environment, extend the service life of the blades, and meet the needs of blade surface cooling; at the same time, the cold air injection structure designed in the present application adopts tangential injection of cooling air, which can effectively suppress the boundary layer thickening and fluid separation caused by the inward shock wave of the trailing edge, reduce aerodynamic losses, and improve the overall efficiency of the turbine; meet the needs of blade cooling without introducing too much additional active jets, avoiding unnecessary airflow losses and energy consumption.
[0071] The following is an example. For example, it is assumed that the slot position determined above is S c It can also be understood as S c represents the dimensionless position of the slot line of the cold air injection structure on the suction surface of the turbine blade. Assuming that the determined S c=52%S ss (S ss Indicates the total arc length of the original suction surface. For turbine blades, S is generally ss are all fixed known values), the final target design parameters can be: S M =10%S ss 、H SLOT =H LIP =0.5mm, L LIP =1mm, target cooling air blowing ratio is 0.8.
[0072] Assuming that the target cooling air blowing ratio is between 0.75 and 1.0 and the cascade energy loss meets the preset conditions, a value within the range can be selected as the final target cooling air blowing ratio.
[0073] Furthermore, after obtaining the target design parameters, simulation verification can be performed. Figure 7 This is a verification diagram shown in this application, such as Figure 7 As shown, Figure 7 The horizontal axis represents the cooling air blowing ratio; the vertical axis represents the blade energy loss coefficient, and MP represents the different dimensionless positions of the starting point of the cooling air injection structure on the suction surface of the turbine blade (MP0.520 means that the broken line represents S c =52%S ss The corresponding broken lines at different cooling air blowing ratios are as follows: Figure 7 It can be seen that the cold air injection structure designed according to the above slot positions and the above target design parameters can achieve an excellent effect of reducing energy loss.
[0074] Figure 8 This is a schematic diagram of a design device for a cold air injection structure shown in this application. Figure 8 As shown, the design device 800 of the cold air injection structure includes a first determination module 801, a second determination module 802, a parameter acquisition module 803, and a parameter optimization module 804, wherein:
[0075] The first determination module 801 is configured to determine distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of a turbine blade on the suction surface of the turbine blade.
[0076] The second determining module 802 is configured to determine slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters.
[0077] The parameter acquisition module 803 is used to acquire the initial design parameters of the cold air injection structure and to establish a blade energy loss simulation model of the gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio.
[0078] The parameter optimization module 804 is used to optimize and simulate the initial design parameters based on the blade energy loss simulation model and the slotting parameters to obtain target design parameters when the blade energy loss meets preset conditions. The target design parameters include target structural parameters and a target cooling air blowing ratio.
[0079] Among them, the present application also proposes a cold air injection structure, which is designed and generated using the design method of the above-mentioned cold air injection structure.
[0080] Among them, the present application also proposes a turbine blade, which can be provided with one or more cold air injection structures designed and generated using the above-mentioned cold air injection structure design method along the blade height direction of the turbine blade.
[0081] In order to implement the above embodiment, the present application also provides an electronic device 900, such as Figure 9 As shown, the electronic device 900 includes: a processor 901 and a memory 902 communicatively connected to the processor, the memory 902 stores instructions that can be executed by at least one processor, and the instructions are executed by at least one processor 901 to implement the design method of the cold air injection structure as shown in the above embodiment.
[0082] In order to implement the above embodiment, the embodiment of the present application also proposes a non-transitory computer-readable storage medium storing computer instructions, wherein the computer instructions are used to enable the computer to implement the design method of the cold air injection structure shown in the above embodiment.
[0083] In order to implement the above embodiments, the embodiments of the present application further provide a computer program product, including a computer program, which, when executed by a processor, implements the design method of the cold air injection structure shown in the above embodiments.
[0084] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.
[0085] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. Throughout the description of this application, "plurality" means two or more, unless otherwise specifically defined.
[0086] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.
[0087] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.
Claims
1. A design method for a cold air injection structure, characterized in that: include: determining distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of the turbine blade on the suction surface of the turbine blade; determining slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters; Acquiring initial design parameters of the cold air injection structure, and establishing a blade cascade energy loss simulation model for a gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio; The initial design parameters are optimized and simulated based on the cascade energy loss simulation model in combination with the slotting parameters to obtain target design parameters when the cascade energy loss meets preset conditions. The target design parameters include target structural parameters and a target cooling air blowing ratio.
2. The method according to claim 1, characterized in that The cold air injection structure includes a first wall surface, a second wall surface, a cold air injection slot, and a third wall surface, wherein the cold air injection slot is used for injecting cold air.
3. The method according to claim 2, characterized in that in: The first wall surface intersects with the suction surface to form an intersection line; The second wall surface intersects with the first wall surface to form an intersection line; The cold air injection slot intersects with the second wall surface to form an intersection line; The third wall surface intersects with the cold air injection slot to form an intersection line, and the third wall surface intersects with the suction surface to form an intersection line.
4. The method according to claim 3, characterized in that The third wall surface adopts a B-spline curve.
5. The method according to claim 4, characterized in that The slotting parameters include a slotting position where a slotting line is located and a slotting length corresponding to the slotting line.
6. The method according to claim 5, characterized in that The target structure parameters include: the width of the cold air injection slot; the thickness between the second wall surface and the suction surface; the width of the second wall; The axial length of the slot line corresponding to the cold air injection structure along the axial direction.
7. The method according to claim 6, characterized in that The method for determining the intersection line formed by the intersection of the third wall surface and the suction surface includes: Taking each point on the slotted line as a starting point, draw a straight line along the axis direction based on the axis length toward the suction surface; An intersection line between the third wall surface and the suction surface is constructed based on an intersection point between the straight line and the suction surface.
8. A design device for a cold air injection structure, characterized in that: include: A first determining module is used to determine distribution parameters of the trailing edge inward extension shock waves corresponding to adjacent blades of the turbine blade on the suction surface of the turbine blade; a second determining module, configured to determine slotting parameters of the cold air injection structure on the suction surface based on the distribution parameters; a parameter acquisition module, configured to acquire initial design parameters of the cold air injection structure and establish a cascade energy loss simulation model for a gas turbine, wherein the initial design parameters include initial structural parameters and an initial cold air blowing ratio; A parameter optimization module is used to optimize and simulate the initial design parameters based on the blade energy loss simulation model and the slotting parameters to obtain target design parameters when the blade energy loss meets preset conditions, wherein the target design parameters include target structural parameters and a target cold air blowing ratio.
9. A cold air injection structure, characterized in that: The cold air injection structure is designed and generated by the design method according to any one of claims 1 to 7.
10. A turbine blade, characterized in that: The turbine blade is provided with a cold air injection structure designed and generated by the design method according to any one of claims 1 to 7.