Design method of high-temperature alloy solid blade wax mold anti-deformation tool

Abstract

The invention relates to a high-temperature alloy solid blade wax mold reversible deformation tool design method, belongs to the technical field of precision casting, and solves the problems that the correction precision is limited during reversible deformation of an existing blade wax mold; and a specific, simple and standardized blade wax mold reversible deformation method does not exist. The invention provides a specific, simple and standardized blade wax mold reversible deformation method, which comprises the following steps: firstly, analyzing according to a cross section to obtain a blade body size deformation rule, then designing a blade wax mold reversible deformation tool according to the deformation rule, and finally, carrying out reversible deformation on the blade wax mold by virtue of the tool. According to the method, the deformation difference between the air inlet and exhaust edges of the blade wax mold and the middle of the blade body is considered, cracks on the air inlet and exhaust edges of the blade wax mold are avoided, the correction precision is improved, and the purpose of effective deformation is achieved.

Description

Technical Field

[0001] The invention relates to the technical field of precision casting, and in particular to a design method for a wax mold reverse deformation tooling of a high-temperature alloy solid blade. Background Art

[0002] Turbine blade preparation is currently a key technical bottleneck in the manufacture of large military and civilian engines and ground-based gas turbine blades. The dimensional deformation of blades is a key technical difficulty in the preparation of large-sized, narrow and long blades. The conventional approach to solving the dimensional deformation of blades is to use mechanical methods to correct the cast blanks, or to correct the wax mold after the blade wax mold is pressed. Mechanical methods require high control of the degree of correction and are prone to cause irreversible damage to the blades. Correcting the wax mold overcomes some of the defects of mechanical correction, but there are still some shortcomings.

[0003] When correcting the wax model, a specific tool is required to achieve the purpose of correction by pressing the wax model with the tool. However, most of the tooling in the prior art allows the entire cross-section of the wax model to move in a certain direction together, without considering the difference between the deformation of the blade inlet and exhaust edges and the deformation of the blade body in the middle, which may cause cracks to appear on the blade wax model inlet and exhaust edges, or greatly reduce the anti-deformation amount that should be set to prevent cracks, thereby failing to play an effective anti-deformation role, or even if no cracks appear, the blade body surface size produced by the anti-deformation tool is unqualified. Summary of the invention

[0004] In view of the above analysis, an embodiment of the present invention aims to provide a method for designing a high-temperature alloy solid blade wax mold anti-deformation tooling, which can solve at least one of the following technical problems: (1) The correction accuracy of the existing blade wax mold is limited during anti-deformation; (2) There is no specific, simple, and standardized method for anti-deformation of blade wax molds; (3) When mechanical means are used to correct the blade casting blank, the casting blank is easily scrapped; (4) The existing blade wax mold anti-deformation method is not flexible enough.

[0005] On the one hand, an embodiment of the present invention provides a method for designing a wax mold anti-deformation tooling for a high-temperature alloy solid blade, comprising the following steps:

[0006] S1. Manufacture a batch of blades according to the target blade size requirements;

[0007] S2, randomly select m blades, select n sections from the blade body of each blade, detect the blade size by three-coordinate or blue light scanning method, and obtain the normal deviation value of each point on the n sections of the blade from the theoretical blade profile;

[0008] S3. According to the three-coordinate and blue light size detection results of the m blades, find the maximum deformation points of the blade base and blade back of each of the n sections, namely, point P and point Q;

[0009] S4, adding the deformation amounts s and t of the points P and Q of each of the n sections of the m blades and taking the average value, and also adding the deformation amounts of the inlet and outlet edges of the n sections of the blade and taking the average value, to obtain the deformation of the n sections of the blade;

[0010] S5. According to the result of S4, several sections are selected from n sections to design the blade anti-deformation model;

[0011] S6. Use the blade anti-deformation model designed in S5 to design the inner cavity of the blade part of the wax mold anti-deformation tooling, and finally obtain the blade wax mold anti-deformation tooling.

[0012] Furthermore, in S1, the target blade is a solid and slender blade made of a high-temperature alloy, and the blade body length is ≥100 mm.

[0013] Furthermore, in S2, the m≥10.

[0014] Further, in S2, when selecting the cross section, it is selected according to the blade design drawing, and the n is consistent with the number of cross sections in the blade drawing.

[0015] Furthermore, in S4, the average deformation of point P on the nth section of the blade is s n =(s 1 +s 2 +s 3 +……+s m ) / m, the average deformation at point Q is t n =(t 1 +t 2 +t 3 +……+t m ) / m.

[0016] Furthermore, in S5, when selecting a section, first select a section (4) in the middle of the blade with the largest deformation, then select a section (2) with a smaller deformation near the tenon and a section (5) with a smaller deformation near the blade crown, and finally select a transition section between the three selected sections based on the length of the blade.

[0017] Furthermore, when the blade length is 100-300 mm, 1-2 transition sections can be selected, and when the blade length is greater than 300 mm, 2-3 transition sections can be selected.

[0018] Furthermore, in S5, when designing the blade anti-deformation model, several selected sections are offset based on the blade wax mold blade theoretical three-dimensional model.

[0019] Furthermore, in S5, a blade anti-deformation model is designed, including the following steps:

[0020] S101, according to S4, the deformation conditions of n sections of the blade are obtained, including the maximum deformation point P of the blade base, the maximum deformation point Q of the blade back, and the average deformation of the inlet side and the exhaust side;

[0021] S102, based on the original theoretical blade cross-section line, using 3D drawing software (UG) to obtain the inverse deformation cross-section line of the cross-section by increasing or decreasing a linear function;

[0022] S103. After the anti-deformation section lines of several sections are completed, the three-dimensional shape of the blade body of the anti-deformation tooling is completed through the curve command of the UG software.

[0023] On the other hand, an embodiment of the present invention provides a high-temperature alloy solid blade wax mold reverse deformation tooling, the inner cavity of the tooling is manufactured by the blade wax mold reverse deformation tooling design method described above.

[0024] Compared with the prior art, the present invention can achieve at least one of the following beneficial effects:

[0025] 1) The present invention fully considers the maximum deformation of the blade, measures the maximum deformation of the blade by three-coordinate or blue light scanning method (both methods are based on actual measurement data, rather than relying solely on experience or simplified assumptions, and are therefore more accurate), and designs a tool that can specifically correct the difference between the deformation of the inlet and exhaust edges of the blade wax mold and the deformation in the middle of the blade body. The tool can finely control the deformation of different cross-sections of the blade wax mold, thereby more accurately compensating for the deformation that may occur in the turbine blade during the casting process. It avoids the problem that the traditional wax mold correction tool moves the entire cross-section of the wax mold in a certain direction during correction, and does not take into account the difference between the deformation of the inlet and exhaust edges of the blade wax mold and the deformation in the middle of the blade body, resulting in reduced aerodynamic performance, reduced dimensional accuracy, and increased scrap rate of the final prepared blade. The present invention improves the correction accuracy of the anti-deformation tool when correcting the blade wax mold.

[0026] 2) A specific, simple, and standardized method for anti-deformation of blade wax molds is proposed. This method simply prioritizes the maximum deformation and then designs the deformation of the intake and exhaust edges. In this way, the blade wax mold anti-deformation tooling can be designed in a relatively short time. With the help of this tooling, the purpose of anti-deformation of the blade wax mold can be achieved. The method is simple and efficient. If the blade design needs to be adjusted, the maximum deformation area can be quickly located and targeted modifications can be made. This method provides convenience for the application of some advanced technologies in actual production.

[0027] 3) It avoids the problem of easy scrapping of the blade casting blank when mechanical means are used to correct the blade casting blank. It avoids the large-scale correction of the blade casting after deformation and the resulting size scrapping, improves the blade size qualification rate, reduces the blade correction ratio, improves the blade production efficiency, and reduces the blade production cost.

[0028] 4) The method of the present invention is highly flexible and can be customized for specific deformation situations, especially when rapid response is required or when dealing with turbine blades with complex shapes and working under extreme working conditions, and can better adapt to different working conditions and requirements.

[0029] 5) It can improve the performance of the blade. This method can improve the aerodynamic performance of the blade, reduce airflow separation, and improve the efficiency of the engine by optimizing the deformation of the inlet and exhaust edges; improve the reliability of the blade by effectively controlling the deformation of key areas; reduce flow losses and improve aerodynamic performance through smooth transitions between the layers of the blade section or between the inlet and exhaust edges, while reducing stress concentration and improving the structural strength of the blade.

[0030] In the present invention, the above-mentioned technical solutions can also be combined with each other to achieve more preferred combination solutions. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can become obvious from the description, or can be understood by practicing the present invention. The purpose and other advantages of the present invention can be achieved and obtained through the contents particularly pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] The drawings are only for the purpose of illustrating particular embodiments and are not to be considered limiting of the present invention. Like reference symbols denote like components throughout the drawings.

[0032] Figure 1 is the blue light detection result of n sections of a leaf;

[0033] Figure 2 is the three-coordinate detection result of a blade section;

[0034] Figure 3 It is a schematic diagram of the positions of point P, point Q and inlet and exhaust edges in a blade cross section;

[0035] Figure 4 Several cross-sectional schematic diagrams selected for designing the blade anti-deformation model;

[0036] Figure 5 It is a schematic diagram of the anti-deformation cross-section line when designing the anti-deformation model of the blade;

[0037] Figure 6 To obtain the schematic diagram of the three-dimensional model of the blade part of the anti-deformation tooling according to the curve group command;

[0038] Figure 7 It is a schematic diagram of the cover opening structure of the blade wax mold anti-deformation tooling of the present invention;

[0039] Figure 8 It is a schematic diagram of the cover structure of the blade wax mold anti-deformation tooling of the present invention.

[0040] Reference numerals:

[0041] 1-tenon; 2-section with smaller deformation near the tenon; 3-transition section with middle deformation; 4-section with maximum deformation in the middle of the blade body; 5-section with smaller deformation near the crown; 6-crown; 7-blade inlet edge; 8-point P with maximum deformation of the blade basin; 9-point Q with maximum deformation of the blade back; 10-reverse deformation from point P to the exhaust edge of the blade; 11-reverse deformation section curve; 12-theoretical section curve; 13-blade exhaust edge; 14-upper cover; 15-lower cover; 16-rotating shaft; 17-locking device; 18-wax mold of the blade to be corrected; 19-rotating shaft seat; 20-rotating shaft fixing seat; 21-upper mold drawer. DETAILED DESCRIPTION

[0042] The preferred embodiments of the present invention are described in detail below in conjunction with the accompanying drawings, wherein the accompanying drawings constitute a part of this application and are used together with the embodiments of the present invention to illustrate the principles of the present invention, but are not used to limit the scope of the present invention.

[0043] The preparation process of turbine blades is complicated, and the final castings are usually obtained through processes such as mold making, shell making, pouring, and post-processing. In the wax mold preparation process, shell preparation process, casting pouring and solidification process, and cutting runners of the blades, there are shrinkage and deformation to varying degrees. In order to ensure that the final casting size meets the design requirements, the wax mold needs to be corrected after the blade wax mold is pressed, that is, the anti-deformation offset. In the subsequent casting process, the anti-deformation offset of the blade wax mold is corrected to the theoretical blade shape, and finally a blade with qualified size is obtained.

[0044] On the one hand, an embodiment of the present invention provides a method for designing a wax mold anti-deformation tooling for a high-temperature alloy solid blade, comprising the following steps:

[0045] S1. Manufacture a batch of blades according to target blade size requirements;

[0046] S2, randomly select m blades, select n sections from the blade body of each blade, detect the blade size by three-coordinate or blue light scanning method, and obtain the normal deviation value of each point on the n sections of the blade from the theoretical blade profile;

[0047] S3. According to the three-coordinate and blue light size detection results of the m blades, find the maximum deformation points of the blade base and blade back of each of the n sections, namely, point P and point Q;

[0048] S4, adding the deformation amounts s and t of the points P and Q of each of the n sections of the m blades and taking the average value, and also adding the deformation amounts of the inlet and outlet edges of the n sections of the blade and taking the average value, to obtain the deformation of the n sections of the blade;

[0049] S5. According to the result of S4, several sections are selected from n sections to design the blade anti-deformation model;

[0050] S6. Use the blade anti-deformation model designed in S5 to design the inner cavity of the blade part of the wax mold anti-deformation tooling, and finally obtain the blade wax mold anti-deformation tooling.

[0051] The present invention uses some advanced technologies and methods, such as three-coordinate or blue light scanning, to obtain the deformation results of the blade body, and designs the wax mold anti-deformation tooling accordingly. With the help of the tooling, the blade wax mold is corrected, and then after subsequent processing, a qualified blade is finally obtained. However, in practical applications, how to specify the design details of the tooling and how to simplify and standardize the tooling design method will be the focus of the present invention.

[0052] Specifically, the present invention takes into account the difference between the deformation of the inlet and exhaust edges of the blade wax mold and the deformation in the middle of the blade body. When designing the anti-deformation model of the blade body, the points P and Q with the maximum deformation in the middle of the blade body and the deformation laws of the inlet and exhaust edges are analyzed. The blade wax mold anti-deformation tooling is designed according to the deformation law, and a series of problems such as cracks in the blade wax mold, failure to effectively anti-deform, or unqualified final blade size are successfully avoided due to the traditional method of blade wax mold anti-deformation tooling not taking into account the difference between the deformation of the inlet and exhaust edges of the blade wax mold and the deformation in the middle of the blade body.

[0053] Furthermore, in S1, the target blade is a solid and slender blade made of high temperature alloy, and the blade length is ≥ 100 mm. Figure 4 , the left side is the tenon 1, the right side is the blade crown 6, the middle part is the blade body, and the blade body part is a solid and slender shape. When manufacturing blades according to the target blade size requirements, the manufactured blades will have a certain degree of deformation due to factors such as thermal stress and shrinkage during the casting process.

[0054] Furthermore, in S2, m≥10. In order to ensure the statistical reliability and representativeness of the test results, a plurality of leaves are generally selected for testing. Selecting m≥10 leaves for testing can ensure the reliability of the results.

[0055] Further, in S2, the section is selected according to the blade design drawing, and n is consistent with the number of sections in the blade drawing. The design drawing of each blade defines the cross-sectional shape and size of the blade in detail, and these sections represent the structural characteristics of the blade at different spanwise positions. By testing each section, it is possible to ensure the performance and consistency of the blade over the entire length.

[0056] Specifically, in S2, when the leaf size is detected by the blue light scanning method, the detection result is as follows: Figure 1 As shown in the figure, different colors are used to indicate the degree of deviation, and the size and position of the deviation can be intuitively displayed by the depth of the color.

[0057] Specifically, in S2, when the blade size is detected using the three-coordinate method, the detection result is as follows: Figure 2 As shown, the figure provides detailed measurement results of the blade cross-sectional dimensions, which can be used to evaluate the deviation of the blade deformation, etc.

[0058] Specifically, in S3, since the thicker the wax mold, the greater the shrinkage deformation during the preparation process, the positions of point P and point Q are generally as follows: Figure 3 As shown in the figure, it is close to the maximum thickness of the blade and the tangent point of the blade. The positions of point P and point Q of the same section of different blades are basically the same.

[0059] Furthermore, in S4, the average deformation of point P on the nth section of the blade is s n =(s 1 +s 2 +s 3 +……+s m ) / m, the average deformation at point Q is t n =(t 1 +t 2 +t 3 +……+t m ) / m. Where m refers to the number of randomly selected leaves in S2.

[0060] Specifically, in S4, generally speaking, the deformation of the inlet and outlet edges of a single section of the blade is 20% to 50% of the deformation of the blade basin and blade back where the maximum deformation is at point P and point Q. The specific deformation will vary slightly depending on the blade profile structure and the position of the section on the blade.

[0061] Furthermore, in S5, when selecting a cross section, you can refer to Figure 4 First, select a section 4 with the largest deformation in the middle of the blade body, then select section 2 with smaller deformation near the tenon and section 5 with smaller deformation near the crown, and finally select a transition section between the three selected sections according to the length of the blade body.

[0062] Specifically, when the blade length is 100-300 mm, 1-2 transition sections can be selected; when the blade length is greater than 300 mm, 2-3 transition sections can be selected.

[0063] In one embodiment, since the blade is 350 mm long, two transition sections are selected, plus the section with the maximum deformation in the middle of the blade body and the section with smaller deformation near the blade crown and the tenon, a total of five sections are selected.

[0064] Furthermore, in S5, when designing the blade anti-deformation model, several selected sections are offset based on the blade wax mold blade theoretical three-dimensional model (directly obtained from the mold inner cavity model of the blade wax mold outer shape mold), and the specific design method is as follows:

[0065] S101, according to the deformation conditions of n sections of the blade determined in S4: the deformation of the blade base at point P with the maximum deformation, the deformation of the blade back at point Q with the maximum deformation, the deformation of the air inlet side, and the deformation of the exhaust side;

[0066] S102, based on the original theoretical cross-sectional line, using 3D drawing software (UG) to obtain the inversely deformed cross-sectional line of the cross-sectional area by increasing or decreasing a linear function;

[0067] S103. After the anti-deformation section lines of several sections are completed, the three-dimensional shape of the blade body of the anti-deformation tooling is completed through the curve command of the UG software. The model schematic diagram is as follows Figure 6 shown.

[0068] S104. Finally, the complete blade anti-deformation model is obtained by summing the three-dimensional shape of the blade body after anti-deformation with the tenon and the theoretical three-dimensional shape of the blade crown.

[0069] Specifically, in S102, if Figure 5 As shown, the blade anti-deformation section line 11 is offset from the blade theoretical section line 12 to the negative normal direction of the blade deformation, and the anti-deformation amount 10 from point P to the blade exhaust edge in the figure decreases as a function of the distance from point P 8 where the blade basin deformation is the largest. It is known that the offsets of point P and the exhaust edge are F(P) and F(row). As the distance x of the curve from point P increases, the offset y gradually decreases, y=a+b(x), and x is 0 at point P. It is obtained that the a value in the linear function is F(P). Then, the offset of the exhaust edge is F(row), and the distance of the exhaust edge from point P is also determined, so the b value in the function can be obtained. By analogy, the anti-deformation section lines of the selected sections are finally obtained.

[0070] Furthermore, in S6, since the blade anti-deformation model is already the result of the blade offset, when designing the inner cavity of the tooling blade part, it is only necessary to design the inner cavity part according to the blade anti-deformation model obtained in S5, that is, to design it to be the same as the model obtained in S5.

[0071] Furthermore, after S6, the wax mold anti-deformation tooling is required to perform anti-deformation pressing on the blade wax mold, and then perform subsequent processes to finally obtain the target blade. The specific steps are as follows:

[0072] (1) Using a wax mold shape mold to press out a complete wax mold of the blade to be corrected;

[0073] (2) After taking out the wax model of the blade to be corrected, immediately put it into the opened wax model anti-deformation tooling, specifically put the back of the blade into the inner cavity of the lower cover plate of the tooling; after putting it in, close the upper cover plate, such as Figure 8 As shown, at this time, the upper cover plate and the lower cover plate are combined together to form an inner cavity to clamp the wax model. The blade body part of the wax model of the blade to be corrected will be subjected to the pressure of the inner cavity of the tooling, and will be pressed and deformed in the inner cavity. The pressing time is 1 to 10 minutes, and the specific time can be adjusted according to the blade structure and the degree of deformation of the blade; the blade crown and the tenon part are processed according to the original wax model theoretical model, which is only fitted but not subjected to pressure.

[0074] (3) The deformed blade wax mold is pressed to produce the target blade according to the normal precision casting process. During the casting process, the reverse deformation bias of the blade wax mold is corrected to the theoretical blade shape or close to the theoretical blade shape after the casting process, and the blade body size meets the requirements of the design drawing or exceeds the tolerance and has a qualified size with a small correction ratio.

[0075] On the other hand, an embodiment of the present invention provides a high-temperature alloy solid blade wax mold reverse deformation tooling, the inner cavity of the tooling is manufactured by the blade wax mold reverse deformation tooling design method described above.

[0076] In one embodiment, a high-temperature alloy solid blade wax mold anti-deformation tooling, the cover opening structure is as follows Figure 7 As shown, the cover structure is as follows Figure 8 As shown, the high-temperature alloy solid blade wax mold reverse deformation tooling includes an upper cover plate 14, a lower cover plate 15, a rotating shaft 16, a rotating shaft seat 19, a rotating shaft fixing seat 20, an upper mold draw block 21 and a locking device 17; the upper cover plate 14 is provided with a blade basin part of the reverse deformation tooling inner cavity, and the lower cover plate 15 is provided with a blade back part of the reverse deformation tooling inner cavity; the upper cover plate 14 and the lower cover plate 15 will form an integral tooling inner cavity after being combined, and the tooling inner cavity is made by the reverse deformation method of the present invention; the upper cover plate is connected to the rotating shaft seat through a rotating shaft, and the other end of the rotating shaft is fixed to the upper cover plate through a rotating shaft fixing seat. The upper mold draw block is connected to the lower cover plate through a guide column and a guide sleeve to realize the core pulling action.

[0077] The above tooling structure is a hinge structure. In addition to the hinge structure, it can also be a structure with upper and lower molds.

[0078] The present invention provides a specific, simple and standardized method for reverse deformation of blade wax molds. The method fully considers the difference between the deformation of the inlet and outlet edges of the blade wax mold and the deformation of the middle of the blade body, can avoid cracks in the blade wax mold, directly obtain a blade with a significantly reduced deformation or even no deformation, improves the correction accuracy, and increases the blade size qualification rate. The method makes the correction process more standardized, reduces the influence of human factors, and improves production efficiency and casting quality.

[0079] The present invention is further described below with reference to the specification using examples, but the examples are only used for the present invention and are not intended to limit the present invention.

[0080] Example 1

[0081] A method for designing a wax mold anti-deformation tooling for a high-temperature alloy solid blade, and using the tooling to prepare a blade with a qualified size, wherein the blade body is 250 mm long, and the specific steps are as follows:

[0082] Step 1: Manufacture a batch of blades according to the target blade size requirements; analyze the deformation law of the blade body size according to the cross section, randomly select 15 blades, measure 9 cross sections of each blade, use blue light scanning or three-coordinate detection of the size of each blade cross section (S1, S2...S9), calculate the deviation value of the blade body size relative to the theoretical blade size through the detection results of 15 blades, the maximum deviation of the blade basin deformation at point P of the S5 section is 0.6mm, the maximum deviation of the blade back deformation at point Q is also 0.6mm, and the deviations of the inlet and exhaust edges are approximately 0.2 and 0.3. The deviation of the S1 section close to the crown is basically 0, the deviation of the S9 section close to the edge plate is basically 0, the maximum deviation of the S3 section between the S1 and S5 sections, and the S7 section between the S5 and S9 sections, the blade basin and back are basically 0.4mm, and the deviations of the inlet and exhaust edges are both 0.15mm;

[0083] Step 2: On the inner cavity of the theoretical mold of the blade wax model, the deformation of the Q point, the P point and the inlet and exhaust edges in each of the five sections S1, S3, S5, S7 and S9 is offset in the opposite direction;

[0084] Step 3: Obtain the anti-deformation section lines of sections S1, S3, S5, S7, and S9 according to the increasing or decreasing function, obtain the blade anti-deformation model according to the curve command group, and finally sum it with the theoretical wax model of the blade crown and tenon to obtain the final blade wax model anti-deformation model. Process the blade wax model anti-deformation tooling according to the blade wax model anti-deformation model;

[0085] Step 4: Place the blade wax model just taken out of the blade shape mold into the anti-deformation tooling for pressing, place it for 2 minutes and then take it out to obtain the blade wax model after pressing and deformation;

[0086] Step 5: Use the pressed and deformed blade wax mold to produce blades of qualified size. According to the blade process flow, the reverse deformation bias of the blade wax mold is corrected to the theoretical blade shape or close to the theoretical blade shape during the casting process. After subsequent processing, a blade of qualified size with greatly reduced or no deformation is obtained.

[0087] The final result was a reduction in blade correction from 85% to 10%.

[0088] Example 2

[0089] A method for designing a wax mold anti-deformation tooling for a high-temperature alloy solid blade, and using the tooling to prepare a blade with a qualified size, wherein the blade body is 350 mm long, and the specific steps are as follows:

[0090] Step 1: Manufacture a batch of blades according to the target blade size requirements; analyze the deformation law of blade body size according to the section, randomly select 15 blades, measure 11 sections of each blade, use blue light scanning or three-coordinate detection of the size of each section (S1, S2...S11) of the blade, calculate the deviation value of the blade body size relative to the theoretical size of the blade through the detection results of 15 blades, the maximum deviation of the blade basin deformation of the S6 section is 0.8mm, the maximum deviation of the blade back deformation is also 0.8mm, and the deviation of the inlet and exhaust edges is about 0.4. The deviation of the S2 section close to the crown is basically 0, the deviation of the S10 section close to the edge plate is basically 0, the maximum deviation of the blade basin and blade back of the S4 section between the S2 and S6 sections is basically 0.6mm, and the deviation of the inlet and exhaust edges is 0.3mm. The maximum deviation of the blade basin and blade back of the S3 section between the S2 and S4 sections is basically 0.4mm, and the deviation of the inlet and exhaust edges is 0.15mm. The maximum deviation of the blade basin and blade back of the S8 section between the S6 and S10 sections is basically 0.4mm, and the deviation of the inlet and exhaust edges is 0.15mm;

[0091] Step 2: On the inner cavity of the theoretical mold of the blade wax model, the deformation of the Q point, the P point and the inlet and exhaust edges in each of the six sections S2, S3, S4, S6, S8 and S10 is offset in the opposite direction;

[0092] Step 3: Obtain the anti-deformation section lines of the S2, S3, S4, S6, S8, and S10 sections according to the increasing or decreasing function, obtain the blade anti-deformation model according to the curve command group, and finally sum it with the theoretical wax model of the blade crown and tenon to obtain the final blade wax model anti-deformation model. Process the blade wax model anti-deformation tooling according to the blade wax model anti-deformation model;

[0093] Step 4: Place the blade wax model just taken out of the blade shape mold into the anti-deformation tooling for pressing, place it for 5 minutes and then take it out to obtain the blade wax model after pressing and deformation;

[0094] Step 5: Use the pressed and deformed blade wax mold to produce blades of qualified size. According to the blade process flow, the reverse deformation bias of the blade wax mold is corrected to the theoretical blade shape or close to the theoretical blade shape during the casting process. After subsequent processing, a blade of qualified size with greatly reduced or no deformation is obtained.

[0095] The final result was a reduction in blade correction from 90% to 15%.

[0096] Comparative Example 1

[0097] The blade wax model of Example 1 is dimensionally corrected using a common wax model correction tool, and the inner cavity of the tool has not undergone the anti-deformation bias of the present invention.

[0098] The final result is: because the wax mold will shrink and deform after being pressed out, the tooling reduces the deformation of the wax mold during the pressing stage, but it cannot play an anti-deformation role in the subsequent shell making and pouring processes, resulting in the blade wax mold undergoing subsequent processes and the final blade body surface dimensions not meeting the qualified standards.

[0099] Comparative Example 2

[0100] The blade wax model of Example 1 is reversely deformed using a certain tooling, which is further improved compared to Comparative Example 1 and can adjust the position height of each molding surface of the blade wax model and adjust the torsion angle of the blade wax model.

[0101] The final result is: because the tooling did not take into account the difference between the deformation of the inlet and exhaust edges of the blade wax model and the deformation in the middle of the blade body, cracks appeared on the inlet and exhaust edges of the blade wax model.

[0102] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A method for designing a wax mold anti-deformation tooling for a high-temperature alloy solid blade, characterized in that: The following steps are involved: S1. Manufacture a batch of blades according to the target blade size requirements; S2, randomly select m blades, select n sections from the blade body of each blade, detect the blade size by three-coordinate or blue light scanning method, and obtain the normal deviation value of each point on the n sections of the blade from the theoretical blade profile; S3. According to the three-coordinate and blue light size detection results of the m blades, find the maximum deformation points of the blade base and blade back of each of the n sections, namely, point P and point Q; S4, adding the deformation amounts s and t of the points P and Q of each of the n sections of the m blades and taking the average value, and also adding the deformation amounts of the inlet and outlet edges of the n sections of the blade and taking the average value, to obtain the deformation of the n sections of the blade; S5. According to the result of S4, several sections are selected from n sections to design the blade anti-deformation model; S6. Use the blade anti-deformation model of S5 to design the inner cavity of the blade part of the anti-deformation tooling, and finally obtain the blade wax mold anti-deformation tooling.

2. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S1, the target blade is a solid and slender blade made of high-temperature alloy, and the blade length is ≥100 mm.

3. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S2, m≥10.

4. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S2, the section is selected according to the blade design drawing, and n is consistent with the number of sections in the blade drawing.

5. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S4, the average deformation of point P on the nth section of the blade is s n =(s1+s2+s3+……+s m ) / m, the average deformation at point Q is t n =(t1+t2+t3+……+t m ) / m.

6. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S5, when selecting a section, first select a section (4) in the middle of the blade body with the largest deformation, then select a section (2) with a smaller deformation near the tenon and a section (5) with a smaller deformation near the blade crown, and finally select a transition section between the three selected sections based on the length of the blade body.

7. The blade wax mold anti-deformation tooling design method according to claim 6 is characterized in that: When the blade length is 100-300 mm, 1-2 transition sections can be selected; when the blade length is greater than 300 mm, 2-3 transition sections can be selected.

8. The blade wax mold anti-deformation tooling design method according to claim 1 is characterized in that: In S5, when designing the blade anti-deformation model, several selected sections are offset based on the blade wax mold blade theoretical three-dimensional model.

9. The blade wax mold anti-deformation tooling design method according to claim 8, characterized in that: In S5, the blade anti-deformation model is designed, including the following steps: S101, according to S4, the deformation conditions of n sections of the blade are obtained, including the maximum deformation point P of the blade base, the maximum deformation point Q of the blade back, and the average deformation of the inlet side and the exhaust side; S102, based on the original theoretical blade cross-section line, using 3D drawing software (UG) to obtain the inverse deformation cross-section line of the cross-section by increasing or decreasing a linear function; S103. After the anti-deformation section lines of several sections are completed, the three-dimensional shape of the blade body of the anti-deformation tooling is completed through the curve command of the UG software.

10. A high-temperature alloy solid blade wax mold anti-deformation tooling, characterized in that: The inner cavity of the tooling is made by the blade wax mold reverse deformation tooling design method described in any one of claims 1-9.

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