A construction method and cooling structure of a double-wave-shaped groove air film hole cooling structure

Abstract

The present invention belongs to the technical field of heat transfer and cooling of hot-end components of gas turbines, and particularly relates to a construction method and cooling structure for a double-wavy groove film hole cooling structure. The structure comprises: a solid wall, the top surface of the solid wall being provided with a thermal barrier coating, the thermal barrier coating being provided with a double-wavy groove, the double-wavy groove being composed of a plurality of interconnected groove units, each of which being composed of a groove upstream wall surface, a groove bottom surface, and a double-wavy groove downstream wall surface, the groove bottom surface being parallel to the top surface of the solid wall, and the groove depth of the groove unit being no greater than the thickness of the thermal barrier coating; a plurality of film holes being provided at equal intervals on the solid wall, the outlets of the film holes being provided on the groove bottom surfaces of the corresponding groove units.

Description

Technical Field

[0001] The present invention belongs to the technical field of heat transfer and cooling of hot end components of a gas turbine, and in particular relates to a construction method and a cooling structure of a double-wave-shaped groove air film hole cooling structure. Background Art

[0002] Gas turbine engines, a thermal power device based on the Brayton cycle, are widely used in modern military and industrial applications due to their powerful output and high thermal efficiency. Gas turbine engines operate in an extremely harsh and demanding environment characterized by high temperature, high pressure, and high speed. The high temperature environment is particularly evident in the turbine, one of its three core components. Experience shows that, assuming the engine size remains constant, a 56K increase in turbine inlet temperature can increase gas turbine thrust by 8-13% and improve cycle efficiency by 2-4%. The turbine inlet temperature of today's advanced aircraft engines exceeds 2000K, but the temperature resistance limit of turbine blade materials is far lower than the turbine inlet temperature, necessitating the use of efficient cooling technology to ensure proper operation.

[0003] Film cooling, one of the most widely used and efficient cooling technologies, initially employed cylindrical holes. In-depth research by domestic and international scholars has revealed that within the flow field structure formed by a cold air jet from a cylindrical hole, counter-rotating kidney-shaped vortex pairs possess the highest strength relative to other vortex systems. Kidney vortices draw the mainstream air beneath the cold air, enhancing mixing and lifting the cold air off the wall, significantly detrimental to film cooling. Based on this, researchers have designed outlet-expanding, shaped holes, exemplified by dustpan holes. These holes increase the film hole outlet area and width by expanding in the flow or span direction, thereby reducing the cold air jet momentum, increasing the film's spanwise coverage, and increasing the spacing between the kidney-shaped vortex pairs to reduce induced lift and induce the formation of anti-kidney vortices. However, classic outlet-expanding, shaped holes experience severe flow separation within the hole at large expansion angles, limiting the increase in outlet width and, consequently, the film's coverage width, limiting their effectiveness in improving cooling efficiency.

[0004] In order to improve the coverage effect and cooling efficiency of film cooling, researchers have made a lot of improvements to the discrete film hole structure, among which the groove film hole is one of the more promising improvement directions. By opening discrete or continuous grooves at the outlet of the film hole, the cold air jet is induced to continue to extend in the span direction, thereby improving the coverage effect of the cold air. For example, the "heart-shaped" pit film hole disclosed in Chinese patent application CN201510810965.1 and the slotted structure designed based on the velocity distribution of the film hole outlet disclosed in Chinese patent application CN201611254468.9 are both discrete groove film hole structures. The groove film hole structure disclosed in Chinese CN201520294987.2 (prior art A) and the dumbbell-shaped groove film hole disclosed in Chinese patent application CN202110769505.4 (prior art B) are both continuous groove film hole structures. The groove film hole structures proposed in the above technical solutions can both expand the film jet in the span direction and improve the efficiency of film cooling. However, under a large blowing ratio, the normal momentum of the cold air jet at the outlet of the film hole is large, and the cold air can easily pass over the groove, making the guiding function of the groove ineffective. At the same time, the cold air has a poor wall attachment effect. The cooling efficiency of the groove film hole under a large blowing ratio is seriously deteriorated. Summary of the Invention

[0005] The purpose of the present invention is to provide a construction method and cooling structure of a double-wave-shaped groove air film hole cooling structure to solve the above-mentioned problems.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] A method for constructing a double-wave-shaped groove air film hole cooling structure, comprising:

[0008] The air film hole outlet corresponds to a double-wave curve, which is obtained by the following steps:

[0009] Find the midpoint A of the downstream edge of the film hole outlet profile, and establish a plane coordinate system xOy with point O as the origin, with the x-axis set along the direction of the cold air jet and the y-axis set perpendicular to the direction of the cold air jet.

[0010] Marking the spline fitting control points in the xOy coordinate system, and setting the control point positions according to the functional relationship between the air film hole parameter settings and the control points;

[0011] Connecting the control points and drawing a spline curve to obtain a double-wave-shaped groove downstream profile line, wherein the groove downstream profile line has two wave crests and one wave trough;

[0012] A groove is formed between the downstream profile line of the groove and the upstream straight line of the groove to form a groove unit, wherein the upstream straight line of the groove is located upstream of the outlet profile line of the air film hole;

[0013] A plurality of groove units are interconnected to form a double-wave groove.

[0014] Preferably, a plane coordinate system xOy is established with point O as the origin, the midpoint A of the downstream edge of the film hole outlet profile is found, point O is marked downstream of point A in the direction of the cold air jet, and a plane coordinate system xOy is established with point O as the origin and P / 2, with the x-axis direction along the flow direction and the y-axis direction along the span direction;

[0015] Wherein, P is the distance between adjacent air film holes.

[0016] Preferably, the positions of the control points are obtained by marking points B(x1, y1), C(x2, y2), D(x3, y3), E(x4, y4), and F(x5, P / 2) and marking points B'(x1', -y1), C'(x2', -y2), D'(x3', -y3), E'(x4', -y4), and F'(x5', -P / 2) in the xOy coordinate system respectively;

[0017] Among them, 0 <y1<y2<y3<y4<P / 2,x3≥x4≥x5,x3≥x2≥x1≥0,x3’≥x4’≥x5’,x3’≥x2’≥x1’≥0。

[0018] Preferably, when connecting the control points and drawing a spline curve, a double-wavy groove downstream profile line is obtained: the points F'(x5',-P / 2), E'(x4',-y4), D'(x3',-y3), C'(x2',-y2), B'(x1',-y1), the origin O, B(x1,y1), C(x2,y2), D(x3,y3), E(x4,y4), and F(x5,P / 2) are connected in sequence and drawn into a spline curve to obtain a double-wavy groove downstream profile line.

[0019] Preferably, when the air film hole is not provided with a spanwise inclination angle, a double corrugated groove is provided symmetrically along the x-axis, x1 = x1', x2 = x2', x3 = x3', x4 = x4', x5 = x5';

[0020] When the air film hole is set with a spanwise inclination angle, the double corrugated groove is asymmetric along the x-axis, x1≠x1', x2≠x2', x3≠x3', x4≠x4', and x5≠x5'.

[0021] A double-wavy groove film hole cooling structure, comprising: a solid wall, a thermal barrier coating provided on the top surface of the solid wall, the double-wavy groove being formed on the thermal barrier coating, the double-wavy groove being composed of a plurality of interconnected groove units, the groove unit being composed of a groove upstream wall surface, a groove bottom surface, and a double-wavy groove downstream wall surface, the groove bottom surface being parallel to the top surface of the solid wall, and the groove depth of the groove unit being no greater than the thickness of the thermal barrier coating;

[0022] The air film holes are arranged at equal intervals on the solid wall, and the outlets of the air film holes are arranged on the bottom surface of the groove in the corresponding groove unit.

[0023] Preferably, the air film hole is arranged at an angle, and the angle between the axis of the air film hole and the direction of the cold air jet satisfies 30°≦the angle with the direction of the cold air jet≦90°;

[0024] Assuming that a plane perpendicular to the cold air jet direction is a spreading surface, the angle between the axis of the air film hole and the spreading surface satisfies 30°≦the angle of the spreading surface≦150°;

[0025] The aperture D of the air film hole satisfies 0.4 mm≦D≦1.0 mm.

[0026] Preferably, the air film hole includes a cylindrical section and an expansion section, the expansion section is provided at a portion of the air film hole close to the outlet, and the ratio of the expansion section length Le to the total length L of the air film hole satisfies 0≦Le / L≦1.

[0027] Preferably, the ratio of the spacing P between adjacent air film holes to the pore diameter D of the cylindrical segment satisfies P / D≧3.

[0028] Preferably, the angle γ between the upstream wall surface of the double-wave groove and the bottom surface of the groove satisfies 30°≦γ≦90°;

[0029] The angle δ between the downstream wall surface of the double-wavy groove and the bottom surface of the groove satisfies 30°≦δ≦90°.

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

[0031] The dual-wave-grooved film hole cooling structure provided by this invention further enhances the cooling effect of the already effective special-shaped holes. After exiting the film hole, the cold air impacts the downstream wall of the dual-wave-shaped groove and expands fully, increasing the spanwise coverage of the cold air. At high blowing ratios, the two groove peaks on the downstream wall of the dual-wave groove induce the formation of anti-kidney vortices, enhancing the cold air's wall adhesion and promoting its spanwise expansion, significantly improving cooling efficiency.

[0032] The double-wavy groove air film hole cooling structure provided by the present invention is based on the grooves opened in the thermal barrier coating. The double-wavy groove structure can be formed by peeling off the coating or blocking before spraying, and has certain processing feasibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. Those skilled in the art can also derive other drawings based on these drawings without inventive work.

[0034] Figure 1 This is a three-dimensional structural diagram of the double-wavy groove air film hole of the present invention.

[0035] Figure 2 It is a top view of the double-wave-shaped groove air film hole of the present invention.

[0036] Figure 3 It is a cross-sectional view of the double-wave-shaped groove air film hole of the present invention.

[0037] Figure 4 This is a unit structure diagram of the double-wavy groove air film hole of the present invention.

[0038] Figure 5 This is a schematic diagram of the profile of the double-wavy groove air film hole of the present invention.

[0039] Figure 6 It is the average cooling efficiency of the surface within the downstream 40D range of the double-wave groove air film hole of the present invention, the sinusoidal groove air film hole disclosed in prior art A, and the dumbbell-shaped groove air film hole disclosed in prior art B under different blowing ratios.

[0040] Figure 7 This is a comparison curve of the spanwise average air film cooling efficiency of the double-wavy groove air film hole of the present invention, the sinusoidal groove air film hole disclosed in prior art A, and the dumbbell-shaped groove air film hole disclosed in prior art B within a downstream flow distance of 40D of the air film hole at a blowing ratio of 1.5.

[0041] Figure 8 The flow direction vortex cloud diagram and velocity vector diagram of the double-wave groove air film hole of the present invention at a cross section 10D downstream of the air film hole.

[0042] Figure 9 This is the flow vortex cloud diagram and velocity vector diagram of the sinusoidal groove air film hole disclosed in prior art A at a cross section 10D downstream of the air film hole.

[0043] Figure 10This is the flow vortex cloud diagram and velocity vector diagram of the dumbbell-shaped groove air film hole disclosed in prior art B at a cross section 10D downstream of the air film hole.

[0044] Figure 11 This is a cooling effect cloud diagram of the double-wave groove air film hole of the present invention within a flow distance of 40D downstream of the air film hole.

[0045] Figure 12 This is a cooling effect cloud diagram of the sinusoidal groove air film hole disclosed in prior art A within a flow range of 40D downstream of the air film hole.

[0046] Figure 13 This is a cooling effect cloud diagram of the dumbbell-shaped groove air film hole disclosed in prior art B within a flow range of 40D downstream of the air film hole.

[0047] Among them, 1. solid wall; 2. thermal barrier coating; 3. air film hole; 4. double wavy groove; 5. upstream wall of groove; 6. bottom surface of groove; 7. downstream wall of double wavy groove; 8. groove unit; 9. outlet; 10. downstream profile of groove; 11. baseline; 12. upstream straight line of groove. DETAILED DESCRIPTION

[0048] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0049] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0050] Reference Figures 1 to 13 The present invention discloses a method for constructing a double-wave-shaped groove air film hole cooling structure, comprising:

[0051] The outlet of the air film hole 3 corresponds to a double-wave curve, which is obtained by the following steps:

[0052] Find the midpoint A of the downstream edge of the outlet profile of the air film hole 3, and establish a plane coordinate system xOy with point O as the origin, with the x-axis set along the direction of the cold air jet and the y-axis set perpendicular to the direction of the cold air jet.

[0053] Mark the spline fitting control points in the xOy coordinate system, and set the control point positions according to the functional relationship between the parameter settings of the air film hole 3 and the control points;

[0054] The control points are connected and drawn into a spline curve to obtain a double-wave-shaped groove downstream profile line 10 having two wave crests and one wave trough;

[0055] A groove is formed between the groove downstream profile line 10 and the groove upstream straight line 12 to form a groove unit 8, and the groove upstream straight line 12 is located upstream of the outlet profile line of the air film hole 3;

[0056] The plurality of groove units 8 are interconnected to form a double-wave-shaped groove 4 .

[0057] To further optimize the solution, establish a plane coordinate system xOy with point O as the origin, find the midpoint A of the downstream edge of the outlet profile of the air film hole 3, mark point O downstream of the jet direction of point A, and establish a plane coordinate system xOy with point O as the origin and P / 2, with the x-axis along the flow direction and the y-axis along the span direction;

[0058] Wherein, P is the distance between adjacent air film holes 3.

[0059] To further optimize the scheme, the control point positions are obtained by marking the points B(x1,y1), C(x2,y2), D(x3,y3), E(x4,y4), and F(x5,P / 2) in the xOy coordinate system, and marking the points B'(x1',-y1), C'(x2',-y2), D'(x3',-y3), E'(x4',-y4), and F'(x5',-P / 2);

[0060] Among them, 0 <y1<y2<y3<y4<P / 2,x3≥x4≥x5,x3≥x2≥x1≥0,x3’≥x4’≥x5’,x3’≥x2’≥x1’≥0。

[0061] Further optimization scheme, when connecting control points, drawing a spline curve, obtains the double-wavy groove downstream profile line 10: connect points F'(x5',-P / 2), E'(x4',-y4), D'(x3',-y3), C'(x2',-y2), B'(x1',-y1), origin O, B(x1,y1), C(x2,y2), D(x3,y3), E(x4,y4), F(x5,P / 2) in sequence, draw a spline curve, and obtain the double-wavy groove downstream profile line 10.

[0062] Further optimization scheme, when the air film hole 3 is not set with a spanwise inclination angle, a double corrugated groove is set symmetrically along the x-axis, x1 = x1', x2 = x2', x3 = x3', x4 = x4', x5 = x5';

[0063] The spanwise inclination angle is the angle between the axis of the air film hole 3 and the spanning surface.

[0064] When the air film hole (3) is set with a spanwise inclination angle, the double corrugated groove is asymmetric along the x-axis, x1≠x1', x2≠x2', x3≠x3', x4≠x4', and x5≠x5'.

[0065] A double-wavy groove film hole cooling structure, comprising: a solid wall 1, a thermal barrier coating 2 provided on the top surface of the solid wall 1, a double-wavy groove 4 formed on the thermal barrier coating 2, the double-wavy groove 4 consisting of a plurality of interconnected groove units 8, the groove unit 8 consisting of a groove upstream wall surface 5, a groove bottom surface 6, and a double-wavy groove downstream wall surface 7, the groove bottom surface 6 being parallel to the top surface of the solid wall 1, and the groove depth of the groove unit 8 being no greater than the thickness of the thermal barrier coating 2;

[0066] The air film holes 3 are opened at equal intervals on the solid wall 1 , and the outlets 9 of the air film holes 3 are opened on the groove bottom surface 6 of the corresponding groove unit 8 .

[0067] Further optimization scheme, the air film hole 3 is set obliquely, and the angle between the axis of the air film hole 3 and the direction of the cold air jet meets the angle of 30°≦with the direction of the cold air jet≦90°;

[0068] Assume that the plane perpendicular to the cold air jet direction is the expansion plane, and the angle between the axis of the air film hole 3 and the expansion plane satisfies 30°≤the angle of the expansion plane≤150°;

[0069] The aperture D of the air film hole 3 satisfies 0.4 mm≦D≦1.0 mm.

[0070] According to a further optimization scheme, the air film hole 3 includes a cylindrical section and an expansion section. The expansion section is provided at the portion of the air film hole 3 close to the outlet 9. The ratio of the expansion section length Le to the total length L of the air film hole 3 satisfies 0≦Le / L≦1.

[0071] According to a further optimization scheme, the ratio of the spacing P between adjacent air film holes 3 to the aperture D of the cylindrical segment satisfies P / D≧3.

[0072] Further optimizing the solution, the angle γ between the upstream wall surface 5 of the double-wave groove 4 and the bottom surface 6 of the groove satisfies 30°≦γ≦90°;

[0073] The angle δ between the downstream wall surface 7 of the double-wavy groove and the groove bottom surface 6 of the double-wavy groove 4 satisfies 30°≦δ≦90°.

[0074] Among them, the air film hole 3 in this embodiment can be selected from typical outlet expansion holes such as cylindrical holes, dustpan holes, and other hole types as well as convergent slit holes, cat ear holes, and other hole types.

[0075] The dual-wave-grooved film hole cooling structure provided by the present invention can further enhance the cooling effect of special-shaped holes such as dustpan holes or cat-ear holes, which already have good cooling effects. After flowing out of the film hole 3, the cold air impacts the downstream wall surface 7 of the dual-wave-shaped double-wave groove and fully expands, increasing the spanwise coverage of the cold air. At high blowing ratios, the two groove peaks on the downstream wall 7 of the dual-wave groove induce the formation of anti-kidney vortices, enhancing the wall adhesion effect of the cold air, promoting the spanwise expansion of the cold air, and significantly improving cooling efficiency.

[0076] The double-wavy groove air film hole cooling structure provided by the present invention is based on the grooves opened in the thermal barrier coating. The double-wavy groove structure can be formed by peeling off the coating or blocking before spraying, and has certain processing feasibility.

[0077] Find the midpoint A of the downstream edge of the outlet profile of the air film hole 3, mark the point 0.1D downstream from point A in the direction of the cold air jet as point O, and establish a coordinate system;

[0078] With point O as the origin, establish the plane coordinate system xOy;

[0079] Mark the points B (0.31D, 0.3D), C (1.22D, 0.9D), D (2.47D, 1.5D), E (2.29D, 2.0D), and F (1.92D, 2.5D) in the xOy coordinate system, and distribute them along the span direction, i.e., y1 <y2<y3<y4<P / 2;

[0080] Similarly, mark points B'(0.31D,-0.3D), C'(1.22D,-0.9D), D'(2.47D,-1.5D), E'(2.29D,-2.0D), and F'(1.92D,-2.5D);

[0081] A spline curve is drawn with points F, E, D, C, B, B', C', D', E', and F' as control points to obtain a double wavy profile 10;

[0082] The groove upstream straight line 12 and the groove downstream profile line 10 are connected by a straight line 11, and the groove unit 8 is obtained by stretching along the outer normal direction D / 2 of the wall surface, that is, the groove depth H is D / 2.

[0083] Taking fan-shaped holes as an example, the angle between the axis of the film hole 3 and the span is 16°, the hole diameter D is 10 mm, the hole axis length L is 2.3D, the ratio of the fan-shaped hole expansion section length to the total length Le / L is 0.48, the lateral spacing P between adjacent holes is 5D, and the flow direction inclination angle α of the fan-shaped hole is 45 degrees, with no span-wise inclination angle. Cooling gas flows through the film hole 3 of the present invention and is ejected, forming an air film covering the flat plate surface. It then mixes with the high-temperature mainstream and is ultimately dissipated.

[0084] Wherein, D is the aperture of the cylindrical section of the air film hole 3, P is the spacing between adjacent air film holes 3, Le is the length of the expansion section, L is the total length of the air film hole 3, and α is the angle between the axis of the air film hole 3 and the direction of the cold air jet.

[0085] In order to verify the validity of this patent, numerical simulations were carried out on the wall cooling efficiency within the downstream 40D range of three types of flat-plate film cooling using the same fan-shaped holes and the same groove depth, namely the sinusoidal groove film hole disclosed in prior art A, the dumbbell-shaped groove film hole disclosed in prior art B, and the double-wavy groove film hole in this embodiment.

[0086] The working conditions used in the numerical simulation are: mainstream aperture Reynolds number Re D =10000, mainstream turbulence Tu=1%, cold air to mainstream density ratio DR=1.5, blowing ratio M is taken as 0.5, 1.0, 1.5 and 2.0 respectively.

[0087] The calculation process uses UG modeling, FluentMeshing to generate unstructured meshes, and CFX solver to solve. The calculated film cooling efficiency and flow field characteristics are as follows: Figures 6 to 13 shown.

[0088] Figure 6 The average cooling efficiency of the surface within the downstream 40D range of the double-wave groove air film hole in this embodiment is compared with that of the sinusoidal groove air film hole disclosed in prior art A and the dumbbell-shaped groove air film hole disclosed in prior art B under different blowing ratios.

[0089] The horizontal axis represents the blowing ratio, and the vertical axis represents the surface average film cooling efficiency.

[0090] It can be seen that when the blowing ratio M≤1.0, the cooling efficiency of the double-wave-shaped groove air film holes in this embodiment is equivalent to that of the sinusoidal groove air film holes, and higher than that of the dumbbell-shaped groove air film holes.

[0091] When the blowing ratio M>1.0, the double-wave-shaped groove film holes of this embodiment have a higher surface average film cooling efficiency than the other two types of groove film holes.

[0092] When the blowing ratio M=2.0, the cooling efficiency of the double-wave-shaped groove air film holes of this embodiment is much higher than that of the other two types of groove air film holes, which fully demonstrates the effectiveness and superiority of this patent.

[0093] Figure 7 The spanwise average air film cooling efficiency distribution of the double-wavy groove air film hole in this embodiment is compared with the sinusoidal groove air film hole disclosed in prior art A and the dumbbell-shaped groove air film hole disclosed in prior art B within a flow distance of 40D downstream of the air film hole when the blowing ratio M=2.0.

[0094] The abscissa represents the distance in the streamwise direction, and the ordinate represents the spanwise average film cooling efficiency.

[0095] It can be seen that compared with the other two types of groove air film holes, the double-wavy groove air film holes of this embodiment have a significant improvement in the span-wise average cooling efficiency when the blowing ratio M=2.0: at any flow position, the span-wise average cooling efficiency of the double-wavy groove air film holes of this embodiment is always greater than that of the other two types of groove air film holes.

[0096] Figures 8 to 10 The flow vortex cloud diagram and velocity vector diagram of the double wavy groove air film hole in this embodiment, the sinusoidal groove air film hole disclosed in prior art A, and the dumbbell-shaped groove air film hole disclosed in prior art B at a cross section 10D downstream of the air film hole when the blowing ratio M=2.0 are respectively shown.

[0097] It can be seen that the double-wavy groove air film holes in this embodiment form an anti-kidney vortex pair near the wall. Under the action of the anti-kidney vortex pair, the cold air is pressed on the wall and extends to both sides along the span direction, which enhances the wall-adhering effect of the cold air and increases the span-wise coverage range of the cold air.

[0098] Figures 11 to 13 The figures show the cooling effect cloud diagrams of the double-wavy groove air film hole in this embodiment, the sinusoidal groove air film hole disclosed in prior art A, and the dumbbell-shaped groove air film hole disclosed in prior art B within a flow distance of 40D downstream of the air film hole when the blowing ratio M=2.0.

[0099] It can be seen that the double-wave-shaped grooved film holes of this embodiment have a stronger span-wise induction effect on the cooling air, and the cooling air covers a wider and more uniform range on the downstream wall surface. At the same time, the cooling air adheres to the wall better, thus significantly improving its cooling efficiency compared to the other two grooved film holes. This fully demonstrates the effectiveness and superiority of this patent.

[0100] In the description of the present invention, it should be understood that the terms "longitudinal", "transverse", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing the present invention, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0101] The embodiments described above are merely descriptions of preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Without departing from the spirit of the present invention, various modifications and improvements made to the technical solutions of the present invention by persons skilled in the art should fall within the scope of protection defined by the claims of the present invention.

Claims

1. A method for constructing a double-wave-shaped groove film hole cooling structure, characterized in that: include: The outlet of the air film hole (3) corresponds to a double-wave curve, which is obtained by the following steps: Find the midpoint A of the downstream side of the outlet profile of the air film hole (3), and establish a plane coordinate system xOy with point O as the origin at a distance S1 downstream of the cold air jet direction at point A. The x-axis is set along the cold air jet direction, and the y-axis is set perpendicular to the cold air jet direction. Set the groove upstream straight line (12) at a distance S2 from the midpoint of the upstream side of the outlet profile of the air film hole (3); Marking the spline fitting control points in the xOy coordinate system, and setting the control point positions according to the functional relationship between the parameter settings of the air film hole (3) and the control points; Connecting the control points and drawing a spline curve to obtain a double-wave-shaped groove downstream profile line (10), wherein the groove downstream profile line (10) has two wave crests and one wave trough; A groove is formed between a groove downstream profile line (10) and a groove upstream straight line (12) to form a groove unit (8), wherein the groove upstream straight line (12) is located upstream of the outlet profile line of the air film hole (3); A plurality of groove units (8) are interconnected to form a double-wave-shaped groove (4); The double-wavy groove (4) comprises a double-wavy groove downstream wall surface (7), and two groove wave crests are provided on the double-wavy groove downstream wall surface (7).

2. The method for constructing a double-wave-shaped groove film hole cooling structure according to claim 1, characterized in that: With point O as the origin, establish the plane coordinate system xOy, find the midpoint A of the downstream side of the outlet profile of the air film hole (3), mark point O downstream of the cold air jet direction at point A, and establish the plane coordinate system xOy with point O as the origin and P / 2, with the x-axis direction along the flow direction and the y-axis direction along the span direction; Wherein, P is the distance between adjacent air film holes (3).

3. The method for constructing a double-wave-shaped groove film hole cooling structure according to claim 2, characterized in that: The control point positions are obtained by marking points B(x1, y1), C(x2, y2), D(x3, y3), E(x4, y4), and F(x5, P / 2) in the xOy coordinate system, and marking points B'(x1', -y1), C'(x2', -y2), D'(x3', -y3), E'(x4', -y4), and F'(x5', -P / 2); Among them, 0 <y1<y2<y3<y4<P / 2,x3≥x4≥x5,x3≥x2≥x1≥0,x3’≥x4’≥x5’,x3’≥x2’≥x1’≥0。 4. The method for constructing a double-wave-shaped groove film hole cooling structure according to claim 3, characterized in that: When connecting the control points and drawing a spline curve, a double-wavy groove downstream profile line (10) is obtained: points F'(x5',-P / 2), E'(x4',-y4), D'(x3',-y3), C'(x2',-y2), B'(x1',-y1), origin O, B(x1,y1), C(x2,y2), D(x3,y3), E(x4,y4), F(x5,P / 2) are connected in sequence and drawn into a spline curve to obtain a double-wavy groove downstream profile line (10).

5. The method for constructing a double-wave-shaped groove film hole cooling structure according to claim 3, characterized in that: When the air film hole (3) is not provided with a spanwise inclination angle, a double corrugated groove is provided symmetrically along the x-axis, x1=x1', x2=x2', x3=x3', x4=x4', x5=x5'; When the air film hole (3) is set with a spanwise inclination angle, the double corrugated groove is asymmetric along the x-axis, x1≠x1', x2≠x2', x3≠x3', x4≠x4', and x5≠x5'.

6. A double-wave groove air film hole cooling structure, characterized in that: include: A solid wall (1), wherein a thermal barrier coating (2) is provided on the top surface of the solid wall (1), and the thermal barrier coating (2) is provided with the double-wavy groove (4), wherein the double-wavy groove (4) is a double-wavy groove (4) constructed by the construction method of the double-wavy groove film hole cooling structure according to any one of claims 1 to 5, and the double-wavy groove (4) is composed of a plurality of interconnected groove units (8), and the groove unit (8) is composed of a groove upstream wall (5), a groove bottom surface (6), and a double-wavy groove downstream wall (7), and two groove peaks are provided on the double-wavy groove downstream wall (7), the groove bottom surface (6) is parallel to the top surface of the solid wall (1), and the groove depth of the groove unit (8) is not greater than the thickness of the thermal barrier coating (2); Air film holes (3) are opened at equal intervals on the solid wall (1), and outlets (9) of the air film holes (3) are opened on the groove bottom surface (6) in the corresponding groove unit (8).

7. The double-wave-shaped groove film hole cooling structure according to claim 6, characterized in that: The air film hole (3) is arranged obliquely, and the angle between the axis of the air film hole (3) and the direction of the cold air jet satisfies 30°≦the angle with the direction of the cold air jet≦90°; Assuming that a plane perpendicular to the cold air jet direction is an expansion plane, the angle between the axis of the air film hole (3) and the expansion plane satisfies 30°≦the angle of the expansion plane≦150°; The aperture D of the air film hole (3) satisfies 0.4 mm≦D≦1.0 mm.

8. The double-wave-shaped groove film hole cooling structure according to claim 6, characterized in that: The air film hole (3) comprises a cylindrical section and an expansion section, the expansion section is provided at a portion of the air film hole (3) close to the outlet (9), and the ratio of the expansion section length Le to the total length L of the air film hole (3) satisfies 0≦Le / L≦1.

9. The double-wave-shaped groove film hole cooling structure according to claim 8, characterized in that: The ratio of the spacing P between adjacent air film holes (3) to the aperture D of the cylindrical segment satisfies P / D≧3.

10. The double-wave-shaped groove film hole cooling structure according to claim 9, characterized in that: The angle γ between the upstream wall surface (5) of the double-wave-shaped groove (4) and the bottom surface (6) of the groove satisfies 30°≦γ≦90°; The angle δ between the downstream wall surface (7) of the double-wavy groove (4) and the groove bottom surface (6) satisfies 30°≦δ≦90°.

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