Processing method of gas film hole with inner hole shunt cone and processing die of gas film hole

Abstract

The application provides a processing method and a processing die of a gas film hole with an inner split flow cone, relates to the field of gas turbine turbine blade gas film cooling hole processing technology, and is characterized in that: two first cylindrical hole segments and second cylindrical hole segments with different diameters are formed on a blade base by means of electric spark processing or laser drilling, a processing die matched with a designed gas film hole structure is arranged in the first cylindrical hole segment, the position of the processing die and the blade base is adjusted according to scale marks on the surface of the processing die, the gap between the processing die and the second cylindrical hole segment is filled by means of thermal spraying, the processing die is finally dissolved by means of chemical processing, and a gas film hole structure with an inner split flow cone meeting design requirements is obtained. The method is simple in steps and easy to implement, can process new gas film holes with an inner split flow cone structure on a gas turbine turbine blade base, can also modify original cylindrical gas film holes, and improves the gas film cooling efficiency of an existing gas turbine turbine blade.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine turbine blade film cooling hole processing technology, and particularly relates to a processing method of a film hole with an inner flow splitting cone and a film hole processing die. BACKGROUND

[0002] With the development of gas turbines towards higher work power and thermal efficiency, the inlet temperature of the gas turbine is gradually increased, which undoubtedly poses greater challenges to the turbine blade cooling technology. As one of the most important cooling methods for gas turbine turbine blades, the film cooling technology has a wide application in the design of high-temperature gas turbine blades. The principle is that the high-pressure air between the compressor stages is transported to the internal cooling channel of the turbine blade through the cold air transportation channel inside the gas turbine rotor, and the cooling air exchanges heat with the blade through the internal flow channel of the turbine blade, and then flows out through the film holes on the surface of the blade. The jet cooling air adheres to the surface of the turbine blade to form a protection, avoiding direct contact of the blade with the high-temperature main stream gas to cause high-temperature ablation. With the in-depth study of the film cooling technology, the film hole structure has gradually developed from the initial cylindrical film hole to the fan-shaped hole, the conical hole, the combined film hole and other special-shaped hole structures. Compared with the cylindrical film hole, the above special-shaped holes have further improved the film cooling effect and are expected to be applied to the film cooling design of high-temperature components of the gas turbine.

[0003] Due to the consideration of the processing method, the existing gas turbine blade film cooling structure mostly adopts the cylindrical film hole, which can be processed by laser drilling or electric spark processing. However, for other special-shaped cooling hole structures with higher film cooling efficiency, it is difficult to complete the processing by using the ordinary film hole processing method. SUMMARY

[0004] The present application aims to at least solve one of the technical problems in the related art to some extent.

[0005] To this end, the first object of the present application is to provide a processing method of a film hole with an inner flow splitting cone, comprising:

[0006] S1, determining a target film hole diameter corresponding to a designed film hole structure, and processing an initial cylindrical hole section on the surface of the turbine blade substrate by electric spark processing or laser drilling to obtain the initial cylindrical hole section, wherein the initial diameter of the initial cylindrical hole section is equal to the target film hole diameter;

[0007] S2, dividing the initial cylindrical hole section into a first cylindrical hole section and a second cylindrical hole section, and expanding the diameter of the second cylindrical hole section to obtain the second cylindrical hole section after the diameter expansion, wherein the first diameter corresponding to the first cylindrical hole section is equal to the initial diameter, and the second diameter corresponding to the second cylindrical hole section after the diameter expansion is greater than the first diameter;

[0008] S3, place the gas film hole processing die with the hole inner splitter cone into the first cylindrical hole section, wherein the outer surface of the gas film hole processing die carries scale marks;

[0009] S4, determine the specific position of the gas film hole processing die according to the scale marks, and fix the position of the gas film hole processing die by using an external clamp;

[0010] S5, fill the coating in the gap between the gas film hole processing die and the second cylindrical hole section with an enlarged diameter on the blade base, so that the coating fills the gap between the gas film hole processing die and the second cylindrical hole section with an enlarged diameter;

[0011] S6, dissolve the gas film hole processing die by chemical processing to obtain the final gas film hole structure with the hole inner splitter cone;

[0012] S7, repeat the above steps S1-S6 to process the gas film hole structure with the hole inner splitter cone at other positions of the turbine blade base.

[0013] According to one embodiment of the present application, if the laser drilling method is used to process the initial cylindrical hole section on the surface of the turbine blade base, a protective material is filled in the turbine blade cavity before drilling to avoid damaging the blade cavity wall when the laser penetrates the blade base.

[0014] According to one embodiment of the present application, when the diameter of the second cylindrical hole section is expanded to obtain the second cylindrical hole section with an enlarged diameter, an electric spark processing method is used.

[0015] According to one embodiment of the present application, the length of the second cylindrical hole section with an enlarged diameter along the hole center axis is greater than the axial distance of the splitter cone trailing edge from the blade base surface in the designed gas film hole structure.

[0016] According to one embodiment of the present application, determining the specific position of the gas film hole processing die according to the scale marks includes: ensuring that the scale of the alignment point between the gas film hole processing die and the outer surface of the blade base is equal to the distance of the splitter cone trailing edge from the gas film hole outlet along the hole center axis in the designed gas film hole structure, so as to determine the specific position of the gas film hole processing die.

[0017] According to one embodiment of the present application, when the coating is filled in the gap between the gas film hole processing die and the second cylindrical hole section with an enlarged diameter on the blade base, a thermal spraying method is used.

[0018] According to one embodiment of the present application, when the film hole structure with the hole internal flow cone at other positions of the turbine blade base is processed, the position of the film hole processing die is adjusted based on the scale mark carried on the outer surface of the film hole processing die and the film hole structure designed at other positions, so that the film hole structure with the hole internal flow cone at other positions of the turbine blade base is processed.

[0019] A second object of the present application is to provide a film hole processing die, comprising: a processing die cylindrical section and a flow cone structure in the cylindrical section; wherein the flow cone structure is located on the leeward side of the processing die cylindrical section and close to the film hole outlet position; the starting point of the flow cone structure close to the inner cavity wall surface of the blade base is taken as the leading edge of the flow cone structure, and the ending point of the flow cone structure away from the inner cavity wall surface of the blade base is taken as the trailing edge of the flow cone structure; after the film hole with the hole internal flow cone is processed based on the processing method of the film hole with the hole internal flow cone as described above, in the cooling process, the cooling air will flow into the film hole inlet first, pass through the leading edge of the flow cone structure, flow through the flow cone structure, exit the flow cone through the trailing edge of the flow cone structure, and then flow out through the film hole outlet.

[0020] According to one embodiment of the present application, the film hole processing die is made of ceramic material and has a certain thickness, and the first diameter corresponding to the first cylindrical hole section processed on the surface of the turbine blade base is equal to the target film hole diameter corresponding to the film hole processing die.

[0021] According to one embodiment of the present application, the outer surface of the film hole processing die is provided with a scale mark along the hole axis, wherein the scale mark line is on the middle section of the flow cone structure, and the mark scale represents the axial distance of a certain place on the surface of the film hole processing die from the trailing edge of the flow cone structure.

[0022] The present application at least achieves the following beneficial effects: 1. The processing method of the film hole with the hole internal flow cone provided by the present application has simple processing steps and is easy to implement. Two cylindrical hole sections with different diameters are opened on the blade base by means of electric spark processing or laser drilling, a processing die matched with the designed film hole structure is placed in the cylindrical hole section of the blade base, the gap between the cylindrical hole section and the processing die is filled by means of thermal spraying, and finally the processing die is dissolved by means of chemical processing, so that the final required film hole structure with the hole internal flow cone is obtained.

[0023] 2. The processing method of the film hole with the hole internal flow cone provided by the present application can modify the original cylindrical film hole, obtain the film hole structure with the hole internal flow cone on the basis of the existing cylindrical film hole, and realize the repair and improvement of the cylindrical film hole on the original blade base.

[0024] 3. The method for processing the gas film hole with the inner flow dividing cone of the application, when laser drilling, the protective material is filled in the blade inner cavity to prevent the blade inner wall from being damaged when processing the cylindrical hole section, and to affect the working state of the subsequent blade.

[0025] 4. The method for processing the gas film hole with the inner flow dividing cone of the application, when processing the cylindrical hole section, the diameter of the first cylindrical hole section is ensured to be equal to the outer surface diameter of the gas film hole processing die, so as to avoid the spraying material from penetrating into the blade inner cavity when filling the gap between the processing die and the second cylindrical hole section by using the thermal spraying method, and affecting the structure of the blade inner cavity.

[0026] 5. The gas film hole die provided by the application is matched with the designed gas film hole structure with the inner flow dividing cone, and the gas film hole processing method and the gas film hole die can realize the processing of the new type of gas film hole with the inner flow dividing cone, and improve the gas film cooling efficiency of the turbine blade.

[0027] 6. The gas film hole die provided by the application is provided with scale marks along the hole central axis direction, the positioning of the gas film hole processing die in the cylindrical hole section of the blade base body is realized by adjusting the scale mark value of the blade base body surface flush with the gas film hole die, so as to process all the gas film holes with the inner flow dividing cone on the blade base body, and obtain the gas film hole structure with the inner flow dividing cone consistent with the design. BRIEF DESCRIPTION OF DRAWINGS

[0028] The above and / or additional aspects and advantages of the application will become apparent and more readily appreciated from the following description, taken in conjunction with the following drawings, in which:

[0029] Figure 1 is a schematic view of an exemplary embodiment of a method for processing a gas film hole with an inner flow dividing cone shown by the application.

[0030] Figure 2 is a sectional view of a first cylindrical hole section and a second cylindrical hole section with an expanded diameter opened on a turbine blade base body shown by the application.

[0031] Figure 3 is a schematic view of a gas film hole processing die with an inner flow dividing cone placed in the first cylindrical hole section shown by the application.

[0032] Figure 4 is a schematic view of a finally obtained gas film hole structure with an inner flow dividing cone shown by the application.

[0033] Figure 5 is a schematic view of the overall structure of a gas film hole processing die shown by the application.

[0034] Figure 6is a top view of a gas film hole machining die with an inner split cone shown in the present application.

[0035] BRIEF DESCRIPTION OF DRAWINGS

[0036] 1, blade base; 2, first cylindrical hole section; 3, second cylindrical hole section with enlarged diameter; 4, gas film hole machining die; 5, gap between second cylindrical hole section and machining die; 6, front edge of split cone; 7, trailing edge of split cone; 8, scale mark on machining die; 9, alignment point of machining die and blade base. DETAILED DESCRIPTION

[0037] The embodiments of the present application are described in detail below with reference to the accompanying drawings, examples of which are shown in the drawings, wherein the same or similar notations represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application.

[0038] Figure 1 is a schematic diagram of an exemplary embodiment of a gas film hole machining method with an inner split cone shown in the present application, as Figure 1 shown, the gas film hole machining method with an inner split cone includes the following steps:

[0039] S101, determine the target gas film hole diameter corresponding to the designed gas film hole structure, and process an initial cylindrical hole section on the surface of the turbine blade base by electric spark machining or laser drilling, wherein the initial diameter of the initial cylindrical hole section is equal to the target gas film hole diameter.

[0040] wherein the angle between the initial cylindrical hole section and the surface of the blade base satisfies the inclination angle of the designed gas film hole structure.

[0041] wherein if laser drilling is used to process the initial cylindrical hole section on the surface of the turbine blade base 1, protective material needs to be filled in the turbine blade cavity before drilling, and the purpose of filling protective material is to provide a barrier during laser drilling, so that the laser can only penetrate the protective material, but not directly contact the blade cavity wall.

[0042] wherein paraffin and pine tar and other materials are often used as protective materials because they have high thermal resistance and heat resistance, and can effectively absorb and diffuse laser energy, thereby protecting the blade cavity wall from damage.

[0043] S102, divide the initial cylindrical hole section into a first cylindrical hole section and a second cylindrical hole section, and expand the diameter of the second cylindrical hole section to obtain a second cylindrical hole section after diameter expansion, wherein the first diameter corresponding to the first cylindrical hole section is equal to the initial diameter, and the second diameter corresponding to the second cylindrical hole section after diameter expansion is greater than the first diameter.

[0044] Figure 2 is a cross-sectional view of the first cylindrical hole section and the second cylindrical hole section after diameter expansion shown in the present application, as shown in the figure, the diameter range that needs to be expanded is marked on the initial cylindrical hole section 2, and the second cylindrical hole section generated after the initial cylindrical hole section is divided can be further expanded in diameter by adjusting the electric spark machining parameters to obtain the second cylindrical hole section 3 after diameter expansion. Figure 2

[0045] Wherein the second diameter corresponding to the second cylindrical hole section after diameter expansion 3 is greater than the first diameter corresponding to the first cylindrical hole section 2, and the center axis of the second cylindrical hole section after diameter expansion 3 and the first cylindrical hole section 2 coincide.

[0046] Wherein the length of the second cylindrical hole section after diameter expansion 3 along the hole center axis direction is greater than the axial distance from the splitter cone tail edge 7 in the designed film hole structure to the surface of the blade base 1.

[0047] S103, place the film hole machining mold with hole inner splitter cone in the first cylindrical hole section, wherein the outer surface of the film hole machining mold carries scale marks.

[0048] Figure 3 is a schematic diagram of placing the film hole machining mold with hole inner splitter cone in the first cylindrical hole section shown in the present application, as shown in the figure, in the present application, when machining the film hole with hole inner splitter cone, the film hole machining mold with hole inner splitter cone needs to be placed in the first cylindrical hole section, which can make the machining process of the film hole more accurate and reliable. Figure 3

[0049] S104, determine the specific position of the film hole machining mold according to the scale marks, and fix the position of the film hole machining mold with external clamps.

[0050] After placing the film hole machining mold 4 into the first cylindrical hole section machined on the turbine blade base 1, adjust the position of the film hole machining mold 4 so that the scale mark 8 on the film hole machining mold 4 is in the plane of the long axis of the outlet of the second cylindrical hole section after diameter expansion 3, and ensure that the scale of the alignment point 9 between the film hole machining mold and the outer surface of the blade base 1 is equal to the distance between the splitter cone tail edge 7 in the designed film hole structure and the film hole outlet along the hole center axis direction, so as to determine the specific position of the film hole machining mold 4.​​

[0051] S105, filling the gap between the gas film hole processing die and the second cylindrical hole section with diameter expansion on the blade base body with coating, so that the gap between the gas film hole processing die and the second cylindrical hole section with diameter expansion is filled with coating.

[0052] Thermal spraying is a commonly used surface repair and coating technology, which can use high-temperature spraying to spray material particles onto the surface to be repaired or coated. In this application, the gap 5 between the gas film hole processing die 4 and the second cylindrical hole section 3 with diameter expansion on the blade base body 1 is filled by thermal spraying. During the thermal spraying process, the material is melted or partially melted at high temperature and sprayed to the position of the hole section gap 5. After thermal spraying, the gap 5 between the gas film hole processing die 4 and the cylindrical hole section of the blade base body is eliminated, and the gas film hole processing die 4 and the blade base body 1 are bonded as a whole.

[0053] S106, dissolving the gas film hole processing die by chemical processing to obtain the final gas film hole structure with hole inner splitter cone.

[0054] Figure 4 is a schematic diagram of a final gas film hole structure with hole inner splitter cone shown in this application, as Figure 4 shown, the gas film hole processing die 4 bonded with the blade base body 1 is dissolved by a specific chemical solution to obtain a gas film hole structure with hole inner splitter cone matching the designed gas film hole structure.

[0055] S107, repeating the above steps S101-S106 to process the gas film hole structure with hole inner splitter cone at other positions of the turbine blade base body.

[0056] When processing the gas film hole structure with hole inner splitter cone at other positions of the turbine blade base body, the length of the designed gas film hole result will change, and the position of the splitter cone structure in the gas film hole will also change. The position of the gas film hole processing die 4 in the base body cylindrical hole section needs to be adjusted according to the position of the designed gas film hole inner splitter cone. Specifically, based on the scale marks carried on the outer surface of the gas film hole processing die, combined with the designed gas film hole structure at other positions, the position of the gas film hole processing die is adjusted to satisfy the scale size 8 that the processing die is flush with the outer surface of the blade base body and the distance between the splitter cone trailing edge 7 in the designed gas film hole structure and the gas film hole outlet along the hole axis is equal, so that the final gas film hole structure matches the designed gas film hole with hole inner splitter cone.

[0057] Figure 5 is a schematic diagram of the overall structure of a gas film hole processing die shown in this application, as Figure 5 shown, the gas film hole processing die 4 includes a processing die cylindrical section and a splitter cone structure inside the cylindrical section.

[0058] The flow splitting cone structure is located on the leeward side of the machining die cylindrical section and close to the gas film hole outlet position.

[0059] The starting point of the flow splitting cone structure close to the blade base inner cavity wall surface is taken as the flow splitting cone structure leading edge 6, and the ending point of the flow splitting cone structure away from the blade base inner cavity wall surface is taken as the flow splitting cone structure trailing edge 7.

[0060] After the gas film hole with hole inner flow splitting cone is machined based on the gas film hole machining die, in the cooling process, the cooling air will flow into the gas film hole inlet, first pass through the flow splitting cone structure leading edge 6, flow through the flow splitting cone structure, and then exit the flow splitting cone through the flow splitting cone structure trailing edge 7 and flow out through the gas film hole outlet.

[0061] The gas film hole machining die 4 is made of ceramic material, which can withstand high temperature of the sprayed material during thermal spraying filling in the machining process, and is easy to be dissolved by chemical solution to form the final gas film hole structure in the later chemical machining.

[0062] Figure 6 is a top view of a gas film hole machining die with hole inner flow splitting cone shown in the application, as Figure 6 The gas film hole machining die 4 has a certain thickness H, the first cylindrical hole section 2 on the surface of the turbine blade base 1 corresponds to the first diameter equal to the target gas film hole diameter D of the gas film hole machining die, so that when the gas film hole machining die 4 is dissolved by the chemical solution, the final gas film hole structure with hole inner flow splitting cone can be formed.

[0063] The gas film hole machining die 4 is made of ceramic material, which can withstand high temperature of the sprayed material during thermal spraying filling in the machining process, and is easy to be dissolved by chemical solution to form the final gas film hole structure in the later chemical machining.

[0064] The application at least realizes the following beneficial effects: 1. The application provides a machining method of gas film hole with hole inner flow splitting cone, which has simple machining steps and is easy to implement. Two cylindrical hole sections with different diameters are opened on the blade base by electric spark machining or laser drilling, a machining die matched with the designed gas film hole structure is placed in the cylindrical hole section of the blade base, the gap between the cylindrical hole section and the machining die is filled by thermal spraying, and finally the machining die is dissolved by chemical machining to obtain the final required gas film hole structure with hole inner flow splitting cone.

[0065] 2. The processing method of the gas film hole with the inner flow dividing cone provided in the application can modify the original cylindrical gas film hole, obtain the gas film hole structure with the inner flow dividing cone on the basis of the existing cylindrical gas film hole, and realize the repair and improvement of the cylindrical gas film hole on the original blade base.

[0066] 3. In the processing method of the gas film hole with the inner flow dividing cone provided in the application, the blade inner cavity is filled with a protective material when laser drilling is performed, so as to prevent the blade inner wall from being damaged when the cylindrical hole section is processed, and affect the working state of the subsequent blade.

[0067] 4. In the processing method of the gas film hole with the inner flow dividing cone provided in the application, the diameter of the first cylindrical hole section processed is ensured to be equal to the outer surface diameter of the gas film hole processing die when the cylindrical hole section is processed, so as to avoid the spraying material from penetrating into the blade inner cavity when the gap between the processing die and the second cylindrical hole section is filled by using the thermal spraying method, and affecting the structure of the blade inner cavity.

[0068] 5. The gas film hole die provided in the application is matched with the designed gas film hole structure with the inner flow dividing cone, and the above-mentioned gas film hole processing method and the gas film hole die can realize the processing of the new type of gas film hole with the inner flow dividing cone, and improve the gas film cooling efficiency of the turbine blade.

[0069] 6. The gas film hole die provided in the application is provided with a scale mark along the hole central axis direction, the positioning of the gas film hole processing die in the cylindrical hole section of the blade base is realized by adjusting the scale mark value of the blade base surface flush with the gas film hole die, so as to process all the gas film holes with the inner flow dividing cone on the blade base, and obtain the gas film hole structure with the inner flow dividing cone consistent with the design.

[0070] In the description of the present application, it should be understood that the orientations or positional relationships indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like are based on the orientations or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as limiting the present application.

[0071] In addition, the terms "first", "second", etc. are used only to describe the purpose and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined with "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise specifically limited.

[0072] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", or "some examples" and the like means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms is not necessarily directed to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. Furthermore, the person skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0073] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary and cannot be construed as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. A method of machining a gas film hole with a hole-internal flow dividing cone, characterized in that, The method comprises the following steps: S1, determining a target gas film hole diameter corresponding to a designed gas film hole structure, and processing an initial cylindrical hole section on a turbine blade substrate surface by means of electric spark machining or laser drilling to obtain the initial cylindrical hole section, wherein an initial diameter of the initial cylindrical hole section is equal to the target gas film hole diameter; S2, dividing the initial cylindrical hole section into a first cylindrical hole section and a second cylindrical hole section, and expanding the diameter of the second cylindrical hole section to obtain a second cylindrical hole section after diameter expansion, wherein a first diameter corresponding to the first cylindrical hole section is equal to the initial diameter, a second diameter corresponding to the second cylindrical hole section after diameter expansion is greater than the first diameter, the center axis of the second cylindrical hole section after diameter expansion and the first cylindrical hole section coincide, and the length of the second cylindrical hole section after diameter expansion along the hole center axis direction is greater than the axial distance of the trailing edge of the splitter cone from the blade substrate surface in the designed gas film hole structure; S3, placing a gas film hole processing die with an inner splitter cone into the first cylindrical hole section, wherein the outer surface of the gas film hole processing die carries scale marks; wherein the first diameter is equal to the target gas film hole diameter corresponding to the gas film hole processing die; S4, determining the specific position of the gas film hole processing die according to the scale marks, and fixing the position of the gas film hole processing die by using an external clamp; S5, filling a coating in the gap between the gas film hole processing die and the second cylindrical hole section after diameter expansion on the blade substrate, so that the coating fills the gap between the gas film hole processing die and the second cylindrical hole section after diameter expansion; S6, dissolving the gas film hole processing die by means of chemical processing to obtain a final gas film hole structure with an inner splitter cone; S7, repeating the above steps S1-S6 to process the gas film hole structure with an inner splitter cone at other positions of the turbine blade substrate; The determination of the specific position of the gas film hole processing die according to the scale marks comprises: Ensuring that the scale of the alignment point between the gas film hole processing die and the outer surface of the blade substrate is equal to the distance of the trailing edge of the splitter cone from the gas film hole outlet along the hole center axis in the designed gas film hole structure, so as to determine the specific position of the gas film hole processing die.

2. The method of claim 1, wherein, If the laser drilling method is used to process the initial cylindrical hole section on the turbine blade substrate surface, a protective material is filled in the turbine blade cavity before drilling to avoid damage to the blade cavity wall when the laser penetrates the blade substrate.

3. The method according to claim 1 or 2, characterized in that, In the step of expanding the diameter of the second cylindrical hole section to obtain the second cylindrical hole section after diameter expansion, an electric spark machining method is used.

4. The method of claim 3, wherein, In the step of filling the coating in the gap between the gas film hole processing die and the second cylindrical hole section after diameter expansion on the blade substrate, a thermal spraying method is used.

5. The method of claim 4, wherein, In the step of processing the gas film hole structure with an inner splitter cone at other positions of the turbine blade substrate, the position of the gas film hole processing die is adjusted based on the scale marks carried on the outer surface of the gas film hole processing die and combined with the designed gas film hole structure at other positions, so as to process the gas film hole structure with an inner splitter cone at other positions of the turbine blade substrate.

6. A gas film orifice machining die characterized by, The method comprises the following steps: The processing die cylindrical section and the flow separation cone structure in the cylindrical section; The flow separation cone structure is located on the leeward side of the processing die cylindrical section and close to the gas film hole outlet position; The starting point of the flow separation cone structure close to the blade base inner cavity wall surface is regarded as the leading edge of the flow separation cone structure, and the ending point of the flow separation cone structure away from the blade base inner cavity wall surface is regarded as the trailing edge of the flow separation cone structure; After the processing of the gas film hole with the flow separation cone structure based on the gas film hole processing die according to any one of claims 1-5, in the cooling process, the cooling air will flow into the gas film hole from the gas film hole inlet, first pass through the leading edge of the flow separation cone structure, then pass through the flow separation cone structure, exit the flow separation cone through the trailing edge of the flow separation cone structure and flow out through the gas film hole outlet.

7. The gas film orifice machining die of claim 6, wherein, The gas film hole processing die is made of ceramic material, and has a certain thickness, and the first cylindrical hole section processed on the surface of the turbine blade base corresponds to a first diameter equal to the target gas film hole diameter corresponding to the gas film hole processing die.

8. The gas film orifice machining die of claim 6 or 7, wherein, The outer surface of the gas film hole processing die is provided with a scale mark along the hole axis, wherein the scale mark line is on the middle surface of the flow separation cone structure, and the mark scale represents the axial distance of a certain place on the surface of the gas film hole processing die from the trailing edge of the flow separation cone structure.

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