A high-temperature alloy solid blade wax mold reverse deformation tooling design method

Abstract

The present application relates to a kind of high-temperature alloy solid blade wax mould reverse deformation tooling design method, belong to precision casting technical field, solve the existing blade wax mould reverse deformation when limited correction accuracy;There is no a set of specific, simple, standard blade wax mould reverse deformation method, etc. The present application provides a kind of specific, simple, standard blade wax mould reverse deformation method, first according to section analysis to obtain blade blade size deformation law, then according to the deformation law to design blade wax mould reverse deformation tooling, finally blade wax mould is deformed with the tooling. This method considers the difference between blade wax mould inlet and exhaust edge and middle deformation of blade body, avoids crack in blade wax mould inlet and exhaust edge, improves correction accuracy, achieves the purpose of effective deformation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of precision casting, and particularly relates to a high-temperature alloy solid blade wax mold reverse deformation tooling design method. BACKGROUND

[0002] Turbine blade preparation is a key technical bottleneck in the manufacture of large military and civil engine blades and ground combustion engine blades. The size deformation of the blade is a key technical difficulty in the preparation process of large-size, narrow and long type blades. The conventional method for solving the size deformation of the blade is to use a mechanical method to correct the shape of the cast blank, or to correct the shape of the wax mold after the wax mold is pressed. The mechanical correction method has high control requirements and is easy to cause irreversible damage to the blade. The correction of the wax mold overcomes some defects of the mechanical correction method, but still has some deficiencies.

[0003] When the wax mold is corrected, a specific tooling is needed to press the wax mold to achieve the purpose of correction. However, the tooling in the prior art mostly moves the entire cross section of the wax mold in a certain direction, without considering the difference between the deformation of the blade inlet and exhaust edges and the deformation of the middle part of the blade, which may cause cracks in the blade wax mold inlet and exhaust edges, or the reverse deformation amount set to prevent cracks is greatly reduced, thereby failing to effectively play a reverse deformation role, or even if no cracks occur, the blade blade surface size produced by using the reverse deformation tooling is not qualified. SUMMARY

[0004] In view of the above analysis, the embodiments of the present application aim to provide a high-temperature alloy solid blade wax mold reverse deformation tooling design method, which can at least solve one of the following technical problems: (1) the correction accuracy is limited when the existing blade wax mold is reversed; (2) there is no specific, simple and standardized blade wax mold reverse deformation method; (3) the cast blank is prone to scrap when the mechanical method is used to correct the blade cast blank; (4) the existing blade wax mold reverse deformation method is not flexible enough.

[0005] In one aspect, the embodiments of the present application provide a high-temperature alloy solid blade wax mold reverse deformation tooling design method, which comprises the following steps:

[0006] S1, a batch of blades are manufactured according to the target blade size requirements;

[0007] S2, m blades are randomly selected, n sections are selected from each blade, and the blade size is detected by a three-coordinate or blue light scanning method to obtain the normal deviation value of each point on the n sections of the blade from the theoretical blade type;

[0008] S3, according to the three-coordinate and blue light size detection results of the m blades, the P point and the Q point, which are the maximum deformation points of the blade basin and the blade back of each section, are found.

[0009] S4, adding and averaging the deformation amounts s and t of the P point and the Q point of each section of the m pieces of blades, and adding and averaging the deformation amounts of the inlet and the exhaust edge of the n sections of the blades to obtain the deformation of the n sections of the blades;

[0010] S5, selecting several sections from the n sections according to the result of S4 to design a blade reverse deformation model;

[0011] S6, using the blade reverse deformation model designed in S5 to design the inner cavity of the blade part of the wax mold reverse deformation tooling, and finally obtaining the blade wax mold reverse deformation tooling.

[0012] Further, in S1, the target blade is a high-temperature alloy solid slender blade, and the length of the blade body is greater than or equal to 100 mm.

[0013] Further, in S2, m is greater than or equal to 10.

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

[0015] Further, in S4, the average deformation amount of the P point on the nth section of the blade is s n =(s1+s2+s3+…+s m ) / m, and the average deformation amount of the Q point is t n =(t1+t2+t3+…+t m ) / m.

[0016] Further, in S5, when selecting the sections, a section with the maximum deformation amount in the middle of the blade body (4) is first selected, then a section (2) close to the tenon with a smaller deformation amount and a section (5) close to the blade crown with a smaller deformation amount are selected, and finally, transition sections are selected between the three selected sections according to the length of the blade body.

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

[0018] Further, in S5, when designing the blade reverse deformation model, the selected sections are offset based on the theoretical three-dimensional model of the blade wax mold blade body.

[0019] Further, in S5, the blade reverse deformation model is designed, including the following steps:

[0020] S101, according to the deformation of the n sections of the blade obtained in S4, including the P point with the maximum deformation amount of the blade basin, the Q point with the maximum deformation amount of the blade back, the average deformation amount of the inlet edge, and the average deformation amount of the exhaust edge;

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

[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, wherein 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 blade finally prepared. 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 de-deforming blade wax molds was proposed. This method simply prioritizes the areas with the greatest deformation and then designs the deformation at the inlet and exhaust edges. This allows for the design of a blade wax mold de-deformation tool in a relatively short period of time. This tool can be used to achieve the desired de-deformation of the blade wax mold. The method is simple and highly efficient. If adjustments to the blade design are required, the area of ​​greatest deformation can be quickly located and targeted modifications can be made. This method facilitates the application of advanced technologies in actual production.

[0027] 3) It avoids the problem of scrapping the blade casting blank when using mechanical means to correct the blade casting blank. It avoids the large-scale correction after deformation of the blade casting 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 application has high flexibility. It can be customized for specific deformation conditions, especially when quick response is required or when dealing with complex shapes and working under extreme working conditions, it can better adapt to different working conditions and requirements.

[0029] 5) The performance of the blade can be improved. The method optimizes the deformation of the inlet and outlet edges, improves the aerodynamic performance of the blade, reduces airflow separation, and improves the efficiency of the engine; by effectively controlling the deformation of the key area, the reliability of the blade is improved; by smooth transition between each layer of the blade section or between the inlet and outlet edges, reducing flow loss and improving aerodynamic performance, while reducing stress concentration and improving the structural strength of the blade.

[0030] In the present application, the above technical solutions can be combined with each other to realize more preferred combination schemes. Other features and advantages of the present application will be described in the subsequent specification, and some advantages will become apparent from the specification, or will be understood by implementing the present application. The purpose and other advantages of the present application can be achieved and obtained by the contents specifically pointed out in the specification and the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0031] The accompanying drawings are included to provide a further understanding of the embodiments, and are incorporated in and constitute a part of this specification, illustrate embodiments of the application, and together with the description serve to explain the principles of the application. In the drawings:

[0032] Figure 1 The blue light detection results of n sections of a certain blade;

[0033] Figure 2 The three-coordinate detection results of a section of a certain blade;

[0034] Figure 3 The position diagram of P point, Q point and inlet and outlet edges in a section of a certain blade;

[0035] Figure 4 The schematic diagram of several sections selected when designing the reverse deformation model of the blade body;

[0036] Figure 5 The schematic diagram of the reverse deformation section line when designing the reverse deformation model of the blade body;

[0037] Figure 6 The schematic diagram of the three-dimensional model of the blade body part of the reverse deformation tool obtained according to the curve group command;

[0038] Figure 7 The schematic diagram of the opening structure of the reverse deformation tool of the blade wax mold of the present application;

[0039] Figure 8 The schematic diagram of the closing structure of the reverse deformation tool of the blade wax mold of the present application.

[0040] Reference signs:

[0041] 1 - tenon; 2 - section close to tenon with small deformation; 3 - transition section with moderate deformation; 4 - section in middle of blade with maximum deformation; 5 - section close to blade crown with small deformation; 6 - blade crown; 7 - blade inlet edge; 8 - P point of maximum deformation in blade basin; 9 - Q point of maximum deformation in blade back; 10 - counter-deformation from P point to blade outlet edge; 11 - counter-deformation section curve; 12 - theoretical section curve; 13 - blade outlet edge; 14 - upper cover plate; 15 - lower cover plate; 16 - rotating shaft; 17 - locking device; 18 - blade wax mold to be straightened; 19 - rotating shaft seat; 20 - rotating shaft fixing seat; 21 - upper mold extraction block. DETAILED DESCRIPTION

[0042] The preferred embodiments of the present application will be described in detail below with reference to the drawings, which form a part of this application, and together with the embodiments of the present application serve to explain the principles of the present application, but not to limit the scope of the present application.

[0043] The turbine blade preparation process is complex, and the final casting can be obtained only through processes such as mold making, shell making, pouring, and post-processing. However, there are different degrees of shrinkage and deformation in the processes of preparing the wax mold, preparing the shell, pouring and solidifying the casting, and cutting the runner. In order to obtain a final casting with a size meeting the design requirements, the wax mold needs to be straightened, i.e., counter-deformed, after being pressed, and in the subsequent casting process, the counter-deformation of the blade wax mold is corrected to the theoretical blade shape, and finally a qualified blade with a correct size is obtained.

[0044] In one aspect, the embodiment of the present application provides a high-temperature alloy solid blade wax mold counter-deformation tool design method, including the following steps:

[0045] S1, manufacturing a batch of blades according to the target blade size requirements;

[0046] S2, randomly selecting m pieces of blades, selecting n sections in the blade part of each blade, and detecting the blade size by using a three-coordinate or blue light scanning method to obtain the normal deviation value of each point on the n sections of the blade from the theoretical blade shape;

[0047] S3, finding the P point and the Q point of each section of the n sections, which are the points with maximum deformation in the blade basin and the blade back, according to the three-coordinate and blue light size detection results of the m pieces of blades;

[0048] S4, adding and averaging the deformation s and t of the P point and the Q point of each section of the n sections of the m pieces of blades, and adding and averaging the deformation of the inlet and outlet edges of the n sections of the blades to obtain the deformation of the n sections of the blades;

[0049] S5, selecting several sections from the n sections to design a blade body counter-deformation model according to the result of S4.

[0050] S6, using the blade body reverse deformation model designed in S5, designing the inner cavity of the wax mold reverse deformation tooling blade body part, and finally obtaining the blade wax mold reverse deformation tooling.

[0051] The present application obtains the blade body deformation result by adopting some advanced technologies and methods, such as three coordinates or blue light scanning, and designs the wax mold reverse deformation tooling according to the result, and the tooling is used for orthopedic treatment of the blade wax mold, and after subsequent processing, a qualified blade is finally obtained. However, in practical application, how to specifically design the details of the tooling and how to simplify and standardize the tooling design method will be the focus of the present application.

[0052] Specifically, the present application considers the difference between the deformation of the inlet and outlet edges of the blade wax mold and the deformation of the middle part of the blade body, analyzes the maximum points P and Q of the deformation of the middle part of the blade body and the deformation law of the inlet and outlet edges when designing the blade body reverse deformation model, and designs the blade wax mold reverse deformation tooling according to the deformation law, thereby successfully avoiding a series of problems such as cracks in the blade wax mold, ineffective reverse deformation of the blade wax mold, and unqualified final blade size caused by the traditional method without considering the difference between the deformation of the inlet and outlet edges of the blade wax mold and the deformation of the middle part of the blade body.

[0053] Further, in S1, the target blade is a high-temperature alloy solid slender blade, and the length of the blade body is greater than or equal to 100 mm. The specific structure can refer to Figure 4 , the left side is a tenon 1, the right side is a blade crown 6, and the middle part is a blade body. When the blade is manufactured according to the size requirements of the target blade, the manufactured blade will be deformed to a certain extent due to thermal stress and shrinkage during the casting process.

[0054] Further, in S2, m is greater than or equal to 10. In order to ensure the statistical reliability and representativeness of the test results, a plurality of blades are generally selected for testing, and m is greater than or equal to 10. The selection of the blades can ensure the reliability of the results.

[0055] Further, in S2, the cross section is selected according to the blade design drawing, and n is consistent with the number of cross sections of the blade drawing. The cross section shape and size of each blade are defined in detail on the design drawing of each blade, and these cross sections represent the structural characteristics of the blade at different spanwise positions. By testing at each cross section, the performance and consistency of the blade in the entire length can be ensured.

[0056] Specifically, in S2, when the blade size is detected by the blue light scanning method, the detection result is as shown in Figure 1 , in which different colors are used to represent 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 detecting the size of the blade by the three-coordinate method, the detection result is as shown in Figure 2 The figure provides detailed measurement results of the cross-sectional size of the blade, which can be used to evaluate the deviation of the deformation of the blade.

[0058] Specifically, in S3, the thicker the wax model, the greater the shrinkage deformation generated during preparation. Generally, the positions of P and Q points are as shown in Figure 3 The P and Q points of different blades at the same cross section are basically consistent.

[0059] Further, in S4, the average deformation of the P point on the nth cross section of the blade is s n =(s1+s2+s3+…+s m ) / m, and the average deformation of the Q point is t n =(t1+t2+t3+…+t m ) / m. Where m refers to the number of randomly selected blades in S2.

[0060] Specifically, in S4, generally, the deformation of the inlet and exhaust edges on a single cross section of the blade body is 20% to 50% of the deformation of the P and Q points where the maximum deformation of the blade basin and the blade back is located. The specific deformation may vary slightly depending on the blade surface structure and the position of the cross section in the blade body.

[0061] Further, in S5, when selecting the cross section, refer to Figure 4 , first select a cross section 4 with the maximum deformation in the middle of the blade body, then select a cross section 2 close to the tenon with smaller deformation and a cross section 5 close to the blade crown with smaller deformation, and finally select a transition cross section between the three selected cross sections according to the length of the blade body.

[0062] Specifically, when the length of the blade body is 100-300 mm, 1-2 transition cross sections can be selected, and when the length of the blade body is > 300 mm, 2-3 transition cross sections can be selected.

[0063] In an embodiment, since the length of the blade is 350 mm, 2 transition cross sections are selected, plus the cross section with the maximum deformation in the middle of the blade body and the cross sections close to the blade crown and the tenon with smaller deformation, a total of 5 cross sections are selected.

[0064] Further, in S5, when designing the blade reverse deformation model, the selected cross sections are offset based on the theoretical three-dimensional model of the blade body of the wax model (directly obtained from the mold cavity model of the mold for making the wax model of the blade). The specific design method is as follows:

[0065] S101, according to the deformation of the n cross sections of the blade determined in S4: the P point with the maximum deformation of the blade basin, the Q point with the maximum deformation of the blade back, the deformation of the inlet and exhaust edges;

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

[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 UG software. The model 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 theoretical three-dimensional numerical models of the tenon and the blade crown.

[0069] Specifically, in S102, if Figure 5 As shown, the blade's reverse deformation section line 11 is offset from the blade's theoretical section line 12 in the negative normal direction of the blade's deformation. Furthermore, the reverse deformation 10 from point P to the blade's exhaust edge decreases as a function of distance from point P 8, where the blade basin deformation is maximum. Given that the offsets between point P and the exhaust edge are F(P) and F(row), as the distance x from point P increases, the offset y gradually decreases, y = a + b(x). At point P, x is 0, and the linear function a = F(P). Furthermore, since the exhaust edge offset is F(row), and the distance from the exhaust edge to point P is also determined, the b value in the function can be obtained. By analogy, the reverse deformation section lines of the selected sections are ultimately obtained.

[0070] Furthermore, in S6, since the blade airfoil inverse deformation model is already the result of the blade offset, when designing the inner cavity of the tooling blade airfoil part, it is only necessary to design the inner cavity part according to the blade airfoil inverse 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, as shown in the figure. Figure 8 As shown, at this time, the upper cover plate and the lower cover plate are merged together to form an inner cavity to clamp the wax model. The blade body part of the wax model 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 blade deformation; the blade crown and tenon parts are processed according to the original wax model theoretical model, which is only fitted and not subject to pressure.

[0074] (3) The blade wax pattern after deformation is pressed according to the normal precision casting process to produce the target blade, and the reverse deformation bias of the blade wax pattern is corrected to the theoretical blade type or close to the theoretical blade type after the casting process, so that the blade size meets the design requirements or the size of the qualified blade with a small orthopedic proportion is obtained.

[0075] In another aspect, the embodiment of the present application provides a high-temperature alloy solid blade wax pattern reverse deformation tool, and the inner cavity of the tool is obtained by the blade wax pattern reverse deformation tool design method described above.

[0076] In one embodiment, a high-temperature alloy solid blade wax pattern reverse deformation tool has an open cover structure as shown in Figure 7 and a cover closing structure as shown in Figure 8 The high-temperature alloy solid blade wax pattern reverse deformation tool comprises 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 pulling block 21 and a locking device 17; the upper cover plate 14 is provided with a blade basin part of the reverse deformation tool inner cavity, and the lower cover plate 15 is provided with a blade back part of the reverse deformation tool inner cavity; the upper cover plate 14 and the lower cover plate 15 form an integral tool inner cavity after being combined, and the tool inner cavity is obtained by the reverse deformation method of the present application; the upper cover plate is connected to the rotating shaft seat through the rotating shaft, and the other end of the rotating shaft is fixed on the upper cover plate through the rotating shaft fixing seat. The upper mold pulling block is connected to the lower cover plate through guide columns and guide sleeves to realize the core pulling action.

[0077] The tool structure described above is a hinge structure, and in addition to the hinge structure, it can also be an upper and lower mold opening structure, etc.

[0078] The present application provides a specific, simple and standardized blade wax pattern reverse deformation method, which fully considers the difference between the deformation of the blade wax pattern at the exhaust edge and the deformation of the blade body in the middle, can avoid cracks in the blade wax pattern, directly obtains a size qualified blade with greatly reduced deformation or even no deformation, improves the correction accuracy, and improves the blade size qualified rate. The method makes the orthopedic process more standardized, reduces the influence of human factors, and improves the production efficiency and casting quality.

[0079] The present application will be further described in conjunction with the embodiments of the specification, but the embodiments are only used for the present application and not limit the present application.

[0080] Embodiment 1

[0081] A high-temperature alloy solid blade wax pattern reverse deformation tool design method, and a size qualified blade prepared by the tool, the blade 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 blade size deformation law according to the cross section, randomly select 15 blades, measure 9 cross sections of each blade, use blue light scanning or three coordinate detection to measure the size of each cross section (S1, S2…S9) of the blade, calculate the deviation value of the blade size relative to the theoretical size of the blade from the detection results of 15 blades, the maximum P point deviation of the blade basin of the S5 cross section is 0.6mm, the maximum Q point deviation of the blade back is also 0.6mm, the inlet and outlet edge deviations are about 0.2 and 0.3. The deviation of S1 cross section close to the blade crown is basically 0, the deviation of S9 cross section close to the rim plate is basically 0, the maximum deviation of the blade basin and the blade back of S3 cross section between S1 and S5 cross sections, and S7 cross section between S5 and S9 cross sections is basically 0.4mm, and the inlet and outlet edge deviations are 0.15mm;

[0083] Step 2: Bias in the opposite direction according to the deformation of Q point, P point and inlet and outlet edge of S1, S3, S5, S7 and S9 cross sections in the theoretical mold cavity of the blade wax mold;

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

[0085] Step 4: Put the blade wax mold just taken out of the blade outer mold into the reverse deformation tooling and press for 2 minutes, then take it out to obtain the pressed and deformed blade wax mold;

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

[0087] The final result is that the blade orthopedic ratio is reduced from 85% to 10%.

[0088] Example 2

[0089] A high-temperature alloy solid blade wax mold reverse deformation tooling design method, and a size qualified blade prepared by using the tooling, the blade body is 350mm long, the specific steps are:

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

[0091] Step 2: Bias the deformation of Q point, P point and inlet and outlet edges of each cross section of S2, S3, S4, S6, S8 and S10 in the reverse direction on the theoretical mold cavity of the blade wax mold;

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

[0093] Step 4: Put the blade wax mold just taken out of the blade outer shape mold into the reverse deformation tooling and press it, take it out after 5 minutes to obtain the pressed and deformed blade wax mold;

[0094] Step 5: Use the production size qualified blade of the pressed and deformed blade wax mold. Produce according to the blade process flow, the reverse deformation bias of the blade wax mold is corrected to the theoretical blade type or close to the theoretical blade type during casting, and after subsequent processing, the size qualified blade with greatly reduced or even no deformation is obtained.

[0095] The final result is that the blade orthopedic ratio is reduced from 90% to 15%.

[0096] Comparative Example 1

[0097] The blade wax mold of Example 1 is subjected to size correction by using a common wax mold correction tooling, and the inner cavity of the tooling is not subjected to the reverse deformation bias of the present application.

[0098] The final result is that because the wax mold is pressed and deformed, the tool reduces the deformation of the wax mold during the pressing stage, but does not play a role in the reverse deformation during the subsequent shell pouring process, resulting in that the blade wax mold does not reach the qualified standard after the subsequent process.

[0099] Comparative Example 2

[0100] The blade wax mold of Example 1 is subjected to reverse deformation by using a tool which is further improved compared with the tool of Comparative Example 1, and the tool can adjust and control the position and height of each profile of the blade wax mold and adjust and control the torsion angle of the blade wax mold.

[0101] The final result is that because the tool does not consider the difference between the deformation of the inlet and exhaust edges of the blade wax mold and the deformation of the middle of the blade body, cracks appear in the inlet and exhaust edges of the blade wax mold.

[0102] The above description is only the preferred specific implementation of the present application, but the protection scope of the present application is not limited to this. Any change or replacement within the technical range disclosed by the present application can be easily thought by those skilled in the art, and should be covered within the protection scope of the present application.

Claims

1. A method for designing a reverse deformation tooling for a high-temperature alloy solid blade wax mold, characterized in that: The following steps are involved: S1. Manufacture a batch of blades according to target blade size requirements; S2. Randomly select m blades, select n sections from the blade body of each blade, measure the blade dimensions using three-dimensional coordinates or blue light scanning, and obtain the normal deviation value of each point on the n sections from the theoretical blade profile; S3. Based on the three-dimensional or blue light dimensional detection results of the m blades, find the points P and Q where the blade base and blade back have the maximum deformation in each of the n sections; S4. Add the deformations s and t of points P and Q of each of the n sections of the m blades and take the average value. Also add the deformations of the inlet and exhaust edges of the n sections of the blade and take the average value to obtain the deformation of the n sections of the blade. S5. According to the results 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 anti-deformation tooling, and finally obtain the blade wax mold anti-deformation tooling; Among them, in S5, when selecting the cross section, first select a cross section (4) in the middle of the blade body with the maximum deformation, then select a cross section (2) near the tenon with a substantially zero deformation, and a cross section (5) near the blade crown with a substantially zero deformation, and finally select a transition cross section between the three selected cross sections according to the blade body length; In S5, the process of designing the blade airfoil anti-deformation model is to offset several selected cross sections based on the blade wax mold blade airfoil theoretical three-dimensional model, which specifically includes the following steps: S101, according to S4, the deformation of n sections of the blade is obtained, including the deformation of the blade base at point P, the deformation of the blade back at point Q, and the average deformation of the intake side and the exhaust side; S102. Based on the original theoretical blade cross-section line, obtain the inverse deformation cross-section line of the cross-section by increasing or decreasing a linear function through UG software; S103. After the anti-deformation section lines of several sections are completed, the three-dimensional model of the blade body of the anti-deformation tooling is completed through the curve command of the UG software.

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 a 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, characterized in that: In S2, when selecting a section, the section is selected according to the blade design drawing, and the 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 of 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, characterized in that: When the blade length is 100-300 mm, 1-2 transition sections are selected; when the blade length is greater than 300 mm, 2-3 transition sections are selected.

7. 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 1-6.

Images