A multi-functional tooling for wire cutting of gas turbine blades and its manufacturing method

Abstract

The present invention discloses a multifunctional tool for gas turbine blade wire cutting and a manufacturing method thereof. The multifunctional tool comprises a base. Different base units are adapted and assembled according to the shape and size of parts to obtain three kinds of molds. Mold I is suitable for fixing and cutting blade petiole tenons and circular parts. Mold II is suitable for blade blade profile parts, blade top areas and parts with steps. Mold III is suitable for blade wing areas or parts with arc areas. In the present invention, for the mold, the investment casting process is used, and the inner cavity contour of each mold can be cast more accurately to better meet the cutting accuracy of the blade. Then, it is cut into four modules by a wire cutting machine, which can be expanded according to the size of the blade to better meet the multifunctionality of the tool; for regular parts, wire cutting is used; for holes and other parts, machine tool processing and punching are used to avoid scratching and squeezing the workpiece and improve precision.

Description

Technical Field

[0001] The present invention belongs to the technical field of gas turbines, and particularly relates to a multi-functional tooling for wire cutting of gas turbine blades and a manufacturing method thereof. Background Art

[0002] Gas turbine blades are important components of gas turbines. Generally, they work under high temperature, high pressure, and corrosive media. Their shapes are complex and the processing requirements are strict, which directly affect the operating efficiency and reliability of gas turbines. The blade structure mainly includes regions such as the blade root, airfoil, and blade tip. The structure of each region is relatively complex. In order to study the internal structure of each region of the blade, it is very necessary to cut the blade. Currently, the most used equipment is the wire electrical discharge machine. However, due to the extremely irregular shape of the blade and the relatively regular fixtures used in the wire cutting equipment, dimensional deviations may occur when cutting irregular blades, which may lead to deviations in subsequent blade analysis.

[0003] Currently, most of the tooling structures for wire cutting are relatively regular, and their manufacturing processes are also relatively simple. The current manufacturing methods mainly involve first using a fitter to establish a reference plane, mark and demarcate the plate, and then perform lathe processing, such as drilling, followed by milling machine processing, such as milling slots, and finally using a fitter to deburr. The disadvantages of the above methods are as follows: The tooling processed by this process has relatively regular shapes. When fixedly cutting irregular parts, it can only be clamped by relying on pads, which will result in dimensional errors, causing misalignment of the analysis surface and resulting in relatively large errors. Another manufacturing method is to use a numerically controlled machine tool for processing. Although the processing route can be edited according to the shape of the mold to process irregular molds, it is only limited to relatively simple molds. For molds with relatively complex structures, due to the limitations of the machine tool's own structure and processing tools, the processing accuracy of extremely complex parts is relatively low, affecting subsequent analysis. In addition, its processing price is often relatively high, the equipment investment is large, and the technical requirements for operators and maintenance personnel are also relatively high. Moreover, when processing parts with complex shapes, the workload of manual programming is large. Summary of the Invention

[0004] In order to solve the technical problems in the prior art, the purpose of the present invention is to provide a multi-functional tooling for wire cutting of gas turbine blades and a manufacturing method thereof.

[0005] In order to achieve the above purpose and reach the above technical effects, the technical solution adopted by the present invention is as follows:

[0006] A multi-functional tooling for wire cutting of gas turbine blades, comprising a base. The base includes base unit I, base unit II, base unit III and base unit IV. Base unit I and base unit II are spliced to form mold I. Base unit I, base unit II, base unit III and base unit IV are spliced to form mold II. Base unit III and base unit IV are spliced to form mold III. A platform plate is arranged on the base. A number of parallel guide rods are arranged on the platform plate, and the distance between the guide rods is adjustable. A locking structure is arranged on the guide rods.

[0007] Furthermore, a number of screws are arranged vertically and horizontally on the base. Base unit I and base unit II are spliced to form mold I through the screws. Base unit I, base unit II, base unit III and base unit IV are spliced to form mold II through the screws. Base unit III and base unit IV are spliced to form mold III through the screws.

[0008] Furthermore, guide rods are symmetrically arranged on two opposite sides of the platform plate. The number of the guide rods is two. A number of positioning holes for adjusting the position of the guide rods are arranged at intervals on the other two opposite sides of the platform plate. The guide rods are fixed by inserting positioning pins into the positioning holes. A gasket is added below the positioning pins.

[0009] Furthermore, the locking structure includes sliders and locking clamp blocks. Sliders are respectively arranged at two opposite ends of each guide rod. The sliders can slide along the guide rods according to the size and shape of the parts. Locking clamp blocks are arranged on each slider. The upper and lower ends of the locking clamp blocks are respectively connected to the sliders and the base.

[0010] Furthermore, the locking clamp block is in a U-shaped structure. Locking bolts are respectively installed at the upper and lower ends of the locking clamp block. The lower end of the locking clamp block extends into a slider inner groove arranged on the base. The locking bolts vertically pass through the locking clamp block and are fixed on the sliders.

[0011] Furthermore, a locking gasket is arranged between the locking bolts and the locking clamp blocks.

[0012] The present invention also discloses a manufacturing method of the multi-functional tooling for wire cutting of gas turbine blades, including the following steps:

[0013] 1) Manufacture the base, mold I, mold II, mold III;

[0014] 2) Make screw holes on the base;

[0015] 3) Manufacture screws and tightening bolts, with the material being stainless steel, and insert them into the screw holes;

[0016] 4) Make a platform plate on the base;

[0017] 5) Make positioning holes on the platform plate;

[0018] 6) Make the guide rod, then drill holes in the guide rod and place the positioning pins;

[0019] 7) Make a slider embedding groove on the side of the base;

[0020] 8) Make the slider, cut it by wire cutting machine, and install it inside the guide rod;

[0021] 9) Make the locking clamp block, cut it by wire cutting machine, and leave bolt holes at the upper and lower parts of the locking clamp block for fixing the slider;

[0022] 10) Make the anti-sliding block for placing at the bottom of the base.

[0023] Furthermore, in step 1), the steps of making the base, mold I, mold II, and mold III include:

[0024] First, according to the shape of the gas turbine blade, including the blade root, blade profile, and blade tip parts, use the investment casting process to prepare the ceramic core molds of mold I, mold II, and mold III;

[0025] Subsequently, carry out wax pattern manufacturing, mold shell preparation, pouring of alloy liquid, and then carry out shell removal and core removal to obtain the blank parts of mold I, mold II, and mold III;

[0026] Subsequently, carry out the heat treatment process of the blank parts by using a heat treatment furnace;

[0027] Subsequently, use a wire electrical discharge machining machine to cut off the redundant parts and cut the lower support part of the base into the required shape, polish and buff it with sandpaper, and then use a wire electrical discharge machining machine to cut the complete casting into four modules, thus completing the production of the base and mold I, mold II, and mold III.

[0028] Furthermore, in steps 2) and 5), respectively, through the machine tool processing technology, use special drills according to the diameter of the holes to drill holes and make screw holes and positioning holes.

[0029] Furthermore, in step 4), the platform plate is cut by a wire cutting machine; in step 6), the guide rod is cut by a wire cutting machine; in step 8), the slider is cut by a wire cutting machine; in step 9), the locking clamp block is cut by a wire cutting machine; in step 10), the anti-sliding block is precisely cut by wire cutting.

[0030] Compared with the prior art, the beneficial effects of the present invention are:

[0031] 1) The present invention discloses a multi-functional tooling for wire cutting of gas turbine blades. The base units I, II, III, and IV can be adaptively assembled according to the shape and size of the parts to obtain the required molds. Different base units are connected together by screws and can form different molds. This tooling can actually nest three types of molds, namely mold I, mold II, and mold III, reflecting the multi-functionality of the tooling and significantly improving its practicality. Mold I is mainly applicable to the fixation and cutting of the blade petiole tenon and circular parts. Mold II is mainly applicable to the blade profile part, the blade tip area, and parts with a stepped shape. Mold III is mainly applicable to the blade airfoil area or parts with an arc area. Using the tooling of the present invention can cut parts of various shapes and sizes, including but not limited to regular-shaped parts and irregular-shaped parts, with good stability and little damage to the parts, increasing the application scenarios of the tooling and having a broader application prospect.

[0032] 2) The present invention discloses a manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades. The molds are mainly made by investment casting process. By cutting different parts of the actual blade and manufacturing ceramic cores according to the models of different parts of the actual blade, it is beneficial to more precisely cast the inner cavity contour of each mold, making it better meet the cutting accuracy of the blade. Then, it is cut into four modules by a wire cutting machine and can be expanded according to the size of the blade to better meet the multi-functionality of the tooling. For other regular components (such as guide rods, sliders, etc.), wire cutting is used. For parts such as holes, machining and drilling on a machine tool are used to avoid scratching and squeezing the workpiece and better achieve its precision. Brief Description of the Drawings

[0033] Figure 1 is a three-dimensional structural schematic diagram of the present invention;

[0034] Figures 2-3 respectively are three-dimensional structural schematic diagrams of a multi-functional tooling for wire cutting of gas turbine blades of the present invention when no screws are installed;

[0035] Figure 4 is a bottom three-dimensional structural schematic diagram of a multi-functional tooling for wire cutting of gas turbine blades of the present invention when no screws are installed. Detailed Embodiments

[0036] The present invention is elaborated in detail below so that the advantages and features of the present invention can be more easily understood by those skilled in the art, thereby making a clearer and more definite definition of the protection scope of the present invention.

[0037] A brief overview of one or more aspects is given below to provide a basic understanding of these aspects. This overview is not an exhaustive survey of all conceived aspects and is neither intended to identify the key or decisive elements of all aspects nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that follows.

[0038] As Figures 1-4 shown, a multi-functional tooling for wire cutting of gas turbine blades includes:

[0039] A base 1, located at the bottom of the tooling, can be fixed to the wire cutting guide rod and serves to support the mold.

[0040] A number of screws 2 are arranged on the base 1. According to the characteristics of the part, after the tooling is determined, it is fastened by tightening bolts 21 to prevent the base 1 from swinging.

[0041] A platform plate 3 is arranged on the base 1 and is used to place two parallel guide rods 4. The guide rods 4 can expand, contract and move according to the size and shape of the part. Positioning holes 5 are arranged on the platform plate 3 at intervals. The positioning holes 5 are used to adjust the position of the guide rods 4, and the distance between the positioning holes 5 can be adjusted according to the size and shape of the part. After the position of the guide rods 4 is determined, the guide rods 4 are fixed by inserting positioning pins 51 into the positioning holes 5. In order to prevent the guide rods 4 from slipping due to the loosening of the positioning pins 51, gaskets are added to the positioning pins 51.

[0042] Sliders 6 are arranged on the guide rods 4. Sliders 6 are respectively arranged at opposite ends of each guide rod 4. The sliders 6 can slide along the guide rods 4 according to the size and shape of the part. When the part is embedded in the mold, the sliders 6 will hold against the mold, playing a role in fixing the part. Plastic gaskets are installed on both sides of the sliders 6 to prevent damage to the part.

[0043] Locking clamp blocks 7 are arranged on the sliders 6. The locking clamp blocks 7 are in a U-shaped structure. Locking bolts 71 and locking gaskets 72 are respectively installed at the upper and lower ends of the locking clamp blocks 7. The lower part of the locking clamp blocks 7 extends into the slider embedded grooves 11 arranged on the base 1. After the part is clamped by the two side sliders 6, the locking bolts 71 pass vertically through the locking clamp blocks 7 and are fixed on the sliders 6, and the locking clamp blocks 7 will lock the sliders 6. The locking gaskets 72 are placed between the locking bolts 71 and the locking clamp blocks 7.

[0044] A number of anti-slip blocks 12 are arranged at the bottom of the base 1 to prevent the mold from sliding.

[0045] The base 1 includes several base units, denoted as: base unit Ⅰ 1-1, base unit Ⅱ 1-2, base unit Ⅲ 1-3, and base unit Ⅳ 1-4. The different base units are connected together by a screw 2 and can form different molds. The screw 2 is fastened to the base 1 through a tightening bolt 21. Specifically, the tooling can freely select a suitable mold according to the shape and size of the part. Among them, mold Ⅰ 8 is a fillet type mold, composed of base unit Ⅰ 1-1 and base unit Ⅱ 1-2. Base unit Ⅰ 1-1 and base unit Ⅱ 1-2 are connected together by a screw 2, and are mainly applicable to the fixation and cutting of the blade petiole tenon and circular parts; mold Ⅱ 9 is similar to a stepped shape, composed of base unit Ⅰ 1-1, base unit Ⅱ 1-2, base unit Ⅲ 1-3, and base unit Ⅳ 1-4. Base unit Ⅰ 1-1, base unit Ⅱ 1-2, base unit Ⅲ 1-3, and base unit Ⅳ 1-4 are connected together by a screw 2, and are mainly applicable to the fixation and cutting of the blade profile part, the blade tip area, and parts with a stepped shape; mold Ⅲ 10 is an arc shape, composed of base unit Ⅲ 1-3 and base unit Ⅳ 1-4. Base unit Ⅲ 1-3 and base unit Ⅳ 1-4 are connected together by a screw 2, and are mainly applicable to the fixation and cutting of the blade airfoil area or parts with an arc area.

[0046] A manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades includes the following steps:

[0047] 1) Manufacture the base, mold Ⅰ, mold Ⅱ, and mold Ⅲ

[0048] First, according to the shape of the gas turbine blade, including parts such as the blade root, airfoil, and blade tip, use the investment casting process to prepare the ceramic core molds of mold Ⅰ8, mold Ⅱ9, and mold Ⅲ10. The present invention preferably uses a silicon-based ceramic core, and its manufacturing steps include the preparation of quartz glass powder, the preparation of the mixture, the preparation of the ceramic slurry, core pressing and shaping, core sintering, core inspection and correction, and core strengthening, etc.; among them, the preparation steps of quartz glass powder include: first, crush the block and strip quartz glass, then clean it with hydrochloric acid solution, and then clean it with clean water, and then perform ball milling, that is, ball mill and mix the glass powder and glass balls, then dry it, and finally sieve it with a 220-270 mesh sieve; the preparation steps of the mixture include: when the quartz glass powder is prepared, prepare the mixture, and during the preparation of the mixture, a mineralizer (composed of alumina, silica, and calcium oxide) needs to be added to promote the sintering of the core, reduce the sintering temperature of the core, and shorten the sintering time; the preparation steps of the ceramic slurry include: first add a plasticizer (a mixture of polyethylene and wax), then add the mixture and stir, and add an activator (such as oleic acid) to the mixture to significantly increase the fluidity of the slurry; the core pressing and shaping steps include: the core pressing has a ceramic slurry temperature of 100°C, a mold preheating temperature of 35°C, a pressing pressure of 0.5 MPa, and a holding pressure time of 0.3 min. The pressed core is subjected to processes such as shaping and inspection; the steps of core sintering and inspection include: the first stage is the dewaxing stage (heating to 450°C and holding for 2 h), the second stage is the roasting stage (heating to 800°C and holding for 2 h), and then inspection is carried out; core strengthening: the strengthening of the core is mainly divided into high-temperature strengthening and low-temperature strengthening. High-temperature strengthening is to immerse the core in ethyl silicate solution and silica sol solution, dry it naturally for 44 h, and harden it with ammonia for 30 min to improve the high-temperature strength and thermal deformation resistance of the core, while low-temperature strengthening is to immerse the core in thermosetting phenolic resin and urea, and then dry it in the air, mainly to improve the room-temperature strength and plasticity of the core and prevent the core from being damaged during trimming and handling;

[0049] Subsequently, wax pattern manufacturing is carried out, and its steps mainly include: wax pattern pressing (the die-casting temperature of the liquid pattern material is 60°C, the pouring pressure is 0.4 MPa, the holding pressure time is 40 s, and the parting agent uses potassium soap solution plus silicone oil), wax pattern inspection and repair (wherein, the pits are repaired with a special wax material of paraffin-alcohol (or acetone) plus dichloroethane ethylene), wax pattern modularity (should include the combination of the gating system, runners, and ceramic core), and mold cleaning (the module should be cleaned in a washing machine and dried naturally in the air);

[0050] Wax pattern pressing, including the following steps: Select rosin-wax-based material as the main raw material for the wax pattern, and then use a mold to press at a die-casting temperature of 60°C, a pouring pressure of 0.4 MPa, and a holding pressure time of 40 s. The parting agent is potassium soap solution plus silicone oil, which is atomized and sprayed on the mold surface;

[0051] Wax pattern inspection and repair: When the pressed wax pattern has defects or pits, use a special wax material of paraffin-alcohol (or acetone) plus dichloroethane ethylene for repair;

[0052] Number of wax pattern modules: Combine the prepared gating system, runners, and ceramic core molds;

[0053] Wax pattern cleaning: Place the wax pattern in a cleaning machine and wash the module with water, and then air-dry it naturally;

[0054] Mold shell preparation: The material is fused alumina. The main steps include rain-type sandblasting, drying and hardening, investment melting, mold shell roasting, and cleaning. The cleaning agent is ethyl silicate hydrolysis solution; The specific steps are: brush the investment with coating, sprinkle sand, and then dry it, repeating many times. The mold shell is mainly composed of multiple layers of refractory materials and binders. Among them, the refractory material is mainly fused alumina, and the bonding layer is mainly ethyl silicate and silica sol. In order to ensure the surface quality of the mold shell, the rain-type sandblasting method is adopted, and then drying and hardening are carried out at a temperature of 20°C, a relative humidity of 50%, and a flow rate of 250 m / min; Then place the mold shell in hot water for dewaxing; Roast the mold shell at 900°C; Finally, clean the mold shell with ethyl silicate hydrolysis solution;

[0055] Subsequently, pour the alloy liquid, and then carry out shell removal and core removal to obtain the blank parts of mold Ⅰ8, mold Ⅱ9, and mold Ⅲ10. Among them, the pouring step includes: Heat the alloy to 1500°C and melt it in a vacuum melting furnace, and then pour the alloy liquid into the mold shell to complete pouring. When the casting cools, use mechanical shell removal to remove the mold shell, and place the casting in an alkaline solution to complete core removal;

[0056] Subsequently, carry out the heat treatment process of the blank parts by using a heat treatment furnace. The main parameters are: quenching at 9800°C and tempering at 150°C, so as to improve the comprehensive properties such as hardness, strength, and corrosion resistance;

[0057] Subsequently, use a wire electrical discharge machining cutter to cut off the excess parts and cut the lower support part of the base 1 into the shape as Figures 1-4 shown. Polish and buff it with different grades of sandpaper. After polishing the base 1 smoothly, use a wire electrical discharge machining cutter to cut the complete casting into four modules, that is, complete the production of the base and mold Ⅰ8, mold Ⅱ9, and mold Ⅲ10.

[0058] 2) Making screw holes

[0059] On the base 1, through the machining process, use a special drill according to the diameter of the hole to drill holes, and precision machining can be achieved.

[0060] 3) Manufacture the screw rod 2 and the fastening bolt 21, with the material being stainless steel, and insert them into the screw rod holes.

[0061] 4) Manufacture the platform plate 3

[0062] Manufacture the platform plate 3 above the base 1. The flat plate at this place is cut by a wire cutting machine. The platform plate 3 is smaller than the plane of the base 1.

[0063] 5) Manufacture the positioning holes

[0064] On the platform plate 3, through the machining process, use a special drill according to the diameter of the hole to drill holes. The distance between the holes is 2 cm. A total of two rows of holes are set, with 6 holes in each row. A scale is set beside the positioning hole 5 to better locate the distance.

[0065] 6) Manufacture the guide rod

[0066] It is made by cutting with a wire cutting machine. Subsequently, on the guide rod 4, through the machining process, use a special drill according to the diameter of the hole to drill holes, and place the positioning pin 51.

[0067] 7) Manufacture the slider embedded grooves

[0068] On the side of the base 1, make four cuboid-shaped grooves as the slider embedded grooves 11. These grooves are machined using a precision machine tool, and the blades used must be hard and cannot produce debris.

[0069] 8) Manufacture the sliders 6, which are cut by a wire cutting machine, a total of four, and install them in the guide rod 4.

[0070] 9) Manufacture the locking clamp blocks 7, which are cut by a wire cutting machine. Make four locking clamp blocks 7 according to the sizes of the slider embedded grooves 11 and the sliders 6. Bolt holes are left at the upper and lower parts of the locking clamp blocks 7 to fix the sliders 6.

[0071] 10) Manufacture the anti-slip blocks 12

[0072] Manufacture on the bottom surface of the base 1 and perform precision cutting by wire cutting.

[0073] In the present invention, the mold is mainly manufactured using the investment casting process. By cutting different parts of the actual blade and manufacturing ceramic cores according to the models of different parts of the actual blade, it is beneficial to more precisely cast the cavity contour of each mold, enabling it to better meet the cutting accuracy of the blade. Then, it is cut into four modules by a wire cutting machine and can be expanded according to the size of the blade to better meet the versatility of the tooling. For the manufacturing of other regular components (such as the guide rod 4, slider 6, etc.), wire cutting is used. For parts such as holes, machining and drilling processes are used on a machine tool, with high precision.

[0074] Because the accuracy required for blade analysis is relatively high, especially for the control of the blade position, it is even more stringent. If the accuracy of the used mold is low, resulting in the deviation of the blade cutting position, it will cause errors in subsequent analysis and measurement, leading to serious consequences. Therefore, the mold preparation, tooling drilling, and processing of each component in the present invention all use precise processing techniques. In particular, the mold preparation uses the precision casting method, which can reflect the precision of the mold and provide precise guarantee for subsequent blade cutting and blade analysis. Since it meets the cutting of each part of the blade, its versatility is demonstrated.

[0075] For parts or structures not specifically described in the present invention, existing technologies or existing products can be adopted and will not be elaborated here.

[0076] The above are only the embodiments of the present invention and do not limit the patent scope of the present invention. Any equivalent structural or equivalent process transformation made using the content of the specification of the present invention, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present invention.

Claims

1. Method for manufacturing a multi-functional tooling for wire cutting of gas turbine blades, Characterized in that, The multi-functional tooling for wire cutting of gas turbine blades includes a base, and the base includes base unit Ⅰ, base unit Ⅱ, base unit Ⅲ and base unit Ⅳ. Base unit Ⅰ and base unit Ⅱ are spliced to form mold Ⅰ. Base unit Ⅰ, base unit Ⅱ, base unit Ⅲ and base unit Ⅳ are spliced to form mold Ⅱ. Base unit Ⅲ and base unit Ⅳ are spliced to form mold Ⅲ. A platform plate is arranged on the base. A number of parallel guide rods are arranged on the platform plate, and the distance between the guide rods is adjustable. A locking structure is arranged on the guide rods; The manufacturing method includes the following steps: 1) Manufacture the base, mold Ⅰ, mold Ⅱ, and mold Ⅲ; 2) Make screw holes on the base; 3) Manufacture screws and fastening bolts, made of stainless steel, and insert them into the screw holes; 4) Make a platform plate on the base; 5) Make positioning holes on the platform plate; 6) Manufacture guide rods, then drill holes on the guide rods and place positioning pins; 7) Make a slider embedded groove on the side of the base; 8) Manufacture sliders, cut them by wire cutting machine, and install them inside the guide rods; 9) Manufacture locking clamp blocks, cut them by wire cutting machine, and bolt holes are left on the upper and lower parts of the locking clamp blocks for fixing the sliders; 10) Manufacture anti-sliding blocks for placing at the bottom of the base; In step 1), the steps of manufacturing the base, mold Ⅰ, mold Ⅱ, and mold Ⅲ include: First, according to the shape of the gas turbine blade, including the blade root, blade profile, and blade tip parts, use the investment casting process to prepare the ceramic core molds of mold Ⅰ, mold Ⅱ, and mold Ⅲ; Subsequently, carry out wax pattern manufacturing, mold shell preparation, pouring of alloy liquid, and then carry out shell removal and core removal to obtain the blank parts of mold Ⅰ, mold Ⅱ, and mold Ⅲ; Subsequently, carry out the heat treatment process of the blank parts by using a heat treatment furnace; Subsequently, use a wire electrical discharge machining machine to cut off the redundant parts and cut the lower support part of the base into the required shape, polish and buff with sandpaper, and then use a wire electrical discharge machining machine to cut the complete casting into four modules, that is, the manufacture of the base and mold Ⅰ, mold Ⅱ, and mold Ⅲ is completed.

2. The method for manufacturing a multi-functional tooling for wire cutting of gas turbine blades according to claim 1, Characterized in that, A number of screws are arranged vertically and horizontally on the base. Base unit Ⅰ and base unit Ⅱ are spliced to form mold Ⅰ through screws. Base unit Ⅰ, base unit Ⅱ, base unit Ⅲ and base unit Ⅳ are spliced to form mold Ⅱ through screws. Base unit Ⅲ and base unit Ⅳ are spliced to form mold Ⅲ through screws.

3. The method for manufacturing a multi-functional tooling for wire cutting of gas turbine blades according to claim 1, Characterized in that, Guide rods are symmetrically arranged on the opposite sides of the platform plate. The number of the guide rods is two. A number of positioning holes for adjusting the position of the guide rods are arranged at intervals on the remaining opposite sides of the platform plate. The guide rods are fixed by inserting positioning pins into the positioning holes, and gaskets are added below the positioning pins.

4. The method for manufacturing a multi-functional tooling for wire cutting of gas turbine blades according to claim 1, It is characterized in that the locking structure includes sliders and locking clamping blocks. Sliders are respectively arranged at opposite ends of each guide rod. The sliders can slide along the guide rods according to the size and shape of the parts. Locking clamping blocks are arranged on each slider. The upper and lower ends of the locking clamping blocks are respectively connected to the sliders and the base.

5. The manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades according to claim 4, It is characterized in that the locking clamping block is in a U-shaped structure. Locking bolts are respectively installed at the upper and lower ends of the locking clamping block. The lower end of the locking clamping block extends into the slider embedded groove arranged on the base. The locking bolts vertically pass through the locking clamping block and are fixed on the sliders.

6. The manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades according to claim 5, It is characterized in that a locking gasket is arranged between the locking bolts and the locking clamping blocks.

7. The manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades according to claim 1, It is characterized in that in step 2) and step 5), screw holes and positioning holes are made respectively through machine tool processing technology and using special drills according to the diameter of the holes.

8. The manufacturing method of a multi-functional tooling for wire cutting of gas turbine blades according to claim 1, It is characterized in that in step 4), the platform plate is cut by a wire cutting machine; in step 6), the guide rods are cut by a wire cutting machine; in step 8), the sliders are cut by a wire cutting machine; in step 9), the locking clamping blocks are cut by a wire cutting machine; in step 10), the anti-sliding blocks are precisely cut by wire cutting.

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