Heat treatment method for aviation Ti6242 material compressor precision forging blade and deformation controllable tool

Abstract

The invention relates to the technical field of heat treatment of Ti6242 material aviation precision forging blades. The invention discloses a heat treatment method for an aviation Ti6242 material compressor precision forging blade and a deformation controllable tool. The heat treatment method comprises the following steps: cleaning; solid solution heat treatment; carrying out vibration finishing; thickness grouping and chemical milling; bending and twisting correction; aging heat treatment; and finally inspecting and turning into machining. A heat treatment deformation controllable tool for an aviation Ti6242 material compressor precision forging blade comprises a base, a material frame and material discs, the material frame is fixed to the base, four layers of material disc fixing frames are arranged on the material frame, a gap is reserved between every two adjacent material disc fixing frames, material disc fixing positions are arranged on the material disc fixing frames, and the material disc fixing positions are fixed to the material frame. The material disc is fixed to the material disc fixing position in a matched mode, a positioning hole is formed in the material disc, and a positioning groove is formed in the positioning hole. The positioning holes are formed in the charging tray, so that the gravity centers of the blades are vertically hung on the positioning holes downwards, the heat treatment size deformation of Ti6242 materials in the solid solution process is better reduced, and the percent of pass of forgings is greatly improved.

Description

Technical Field

[0001] This invention relates to the field of heat treatment technology for precision forged aerospace blades made of Ti6242 material, and particularly to a heat treatment method and deformation controllable tooling for precision forged aerospace compressor blades made of Ti6242 material. Background Technology

[0002] Compressor blades, as one of the key components of aero-engines, are characterized by their complex structure, high precision, complex machining processes, and large quantity. Generally, the machining workload of compressor blades accounts for 30% to 40% of the total machining workload of the entire engine. Because compressor blades must possess excellent metallurgical properties, precise dimensions, and excellent surface integrity, the precision forging manufacturing technology for compressor blades is extremely complex in the manufacturing industry. Titanium alloys are mainly used in aero-engines to manufacture parts such as fans, compressor discs, blades, and casings, as well as various types of fasteners. Their usage exceeds 70% in the aerospace industry. Replacing structural steel with titanium alloys can reduce the weight of parts by approximately 30%. Precision forged compressor blades generally have complex structures, high dimensional accuracy, and thin blade profiles of only about 1-3 mm. However, existing Ti6242 materials can be heated to 970℃ to 980℃ during solution heat treatment, making them extremely prone to deformation during heat treatment. This makes it difficult to guarantee the high dimensional accuracy of precision forged blades, resulting in poor reliability, low yield rates, and reduced production efficiency. Summary of the Invention

[0003] The purpose of this invention is to provide a heat treatment method and deformation controllable tooling for precision forging of compressor blades made of Ti6242 material, so as to solve the technical problem of easy dimensional deformation of Ti6242 material compressor blades during forging heat treatment mentioned in the background art.

[0004] The above-mentioned technical objective of this invention is achieved through the following technical solution: a heat treatment method and deformation controllable tooling for precision forged compressor blades made of aerospace Ti6242 material, comprising the following steps:

[0005] Step 1: Cleaning: Before heat treatment, an etching process is carried out to clean the dirt on the surface of the parts and ensure that the parts are clean and free of contamination. The etching process contains 6 cleaning tanks, which are divided into alkaline washing, pure water washing, pure water washing, etching washing, pure water washing, and hot pure water washing. The 6 tanks are operated in sequence to complete the cleaning process.

[0006] The corrosion cleaning tank contains a mixture of hydrofluoric acid and nitric acid in an 8:1 ratio; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 30-60 seconds. The alkaline cleaning tank contains a mixture of 20-25% concentration Turco 5948DPM cleaning agent and pure water; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 3-5 minutes. The pure water cleaning tank contains pure water; the cleaning time is 2-3 minutes, and the temperature is 15-35 degrees Celsius. The hot pure water cleaning tank contains pure water; the cleaning temperature is 70-80 degrees Celsius, and the cleaning time is 2-3 minutes.

[0007] Step 2: Solution heat treatment: Place the above forgings into a vacuum heat treatment furnace and heat them to the phase transformation point T. β -20℃±10℃, the T β The temperature indicates the phase transition point; after heat preservation, it is purged with argon gas and cooled to below 60℃, then air-cooled to 0-25℃;

[0008] Step 3: Vibratory finishing: Place the parts into a vibratory finishing machine for finishing. After finishing, wash the parts with water to remove any remaining finishing liquid from the surface of the parts.

[0009] Step 4: Thickness grouping and chemical milling: Use an inductance meter to detect the thickness of the profile. For blades with excessive thickness, the excess profile thickness needs to be removed until the process requirements are met.

[0010] Step 5: Bending and Torsion Correction: Inspect the flange, torsion angle and bending dimensions of the final forging. For dimensions that are out of tolerance, use pliers to hold the blade and correct the values ​​of its flange, torsion angle and bending to make its flange, torsion angle and bending dimensions meet the process requirements.

[0011] Step 6: Aging heat treatment: Place the above forgings into a vacuum heat treatment furnace, heat to 595±10℃, hold at the temperature, then cool to below 60℃ with argon gas, and air cool to room temperature: 0-25℃ after removing from the furnace.

[0012] Step 7: Final inspection and transfer to machining: Inspect the blades and transfer the qualified blades to machining, such as milling the exhaust edge, cutting the blade tip and milling the blade root, to obtain the final finished blade.

[0013] Furthermore, the heat preservation time in step 2 is 50 minutes; the heat preservation time in step 6 is 480 minutes.

[0014] Furthermore, in step 3, the polishing time is 2 hours, the frequency is set to 40-50Hz, and the polishing abrasive medium is selected as ceramic medium.

[0015] Furthermore, in step 4, the excess surface thickness of the blades with excessive thickness is removed by chemical milling. The process requirement is that the blade thickness is within the tolerance range of -0.05mm to +0.15mm; excessive thickness indicates that the dimension does not meet the process requirements.

[0016] Furthermore, in step 5, the flange, torsion angle and bending dimensions of the final forging are inspected using an inductance meter and a bending and torsion testing fixture.

[0017] Furthermore, in step 7, a 10x magnifying glass is used to perform a 100% inspection of the forging to check for visual defects such as cracks, folds, scratches, dents, pits, and pockmarks on the surface of the forging, and to check whether the dimensions of the forging edge plate, bending, twisting, contour, thickness, etc. meet the process requirements.

[0018] A controllable tooling fixture for heat treatment deformation of precision forged compressor blades made of aerospace Ti6242 material, used to perform a heat treatment method for precision forged compressor blades made of aerospace Ti6242 material, includes: a base, a material rack, and a material tray. The material rack is fixed on the base, and a material tray fixing frame is provided on the material rack. The material tray fixing frame has four layers, with a gap reserved between adjacent material tray fixing frames. A material tray fixing position is provided on the material tray fixing frame, and the material tray is correspondingly fixed on the material tray fixing position. A positioning hole is provided on the material tray, and a positioning groove is provided on the positioning hole.

[0019] Furthermore, at least one positioning hole is provided, and the positioning holes are evenly distributed on the material tray.

[0020] Furthermore, each of the positioning holes is provided with at least one positioning groove, and each positioning groove is provided with a tenon fixing position.

[0021] Furthermore, the base 1 and the material rack 2 are made of a high-temperature alloy material containing molybdenum, and the material tray 3 is made of mullite.

[0022] In summary, the present invention has the following beneficial effects: The present invention provides a heat treatment method and deformation controllable tooling for precision forged compressor blades made of Ti6242 material for aerospace applications. Through steps such as cleaning, solution heat treatment, vibration finishing, thickness grouping and chemical milling, bending and torsion correction, aging heat treatment, final inspection and transfer to machining, the blade components meet the process requirements, effectively improving the reliability of the blades, and improving product quality and production efficiency.

[0023] Meanwhile, by setting positioning holes on the material tray and hanging the blade vertically downwards on the positioning holes, this application improves stability, reduces the dimensional deformation of Ti6242 material during heat treatment in the solution treatment process, and greatly improves the forging qualification rate. Attached Figure Description

[0024] Figure 1 This is a process flow diagram of the present invention;

[0025] Figure 2 This is a schematic diagram of the structure of the present invention;

[0026] Figure 3 This is a schematic diagram of the base structure in this invention;

[0027] Figure 4 This is a schematic diagram of the material rack structure in this invention;

[0028] Figure 5 This is a schematic diagram of the material tray structure in this invention;

[0029] Figure 6 This is a report drawing of the forged blade dimensions according to an embodiment of the present invention;

[0030] Figure 7 This is a low-magnification longitudinal microstructure diagram of the forged blade in an embodiment of the present invention;

[0031] Figure 8 This is a high-magnification microstructure image of the forged blade in an embodiment of the present invention;

[0032] Figure 9 This is a graph showing the test results of the room temperature tensile properties of the forgings in an embodiment of the present invention;

[0033] Figure 10 This is a graph showing the hydrogen content detection data of forgings in an embodiment of the present invention;

[0034] Figure 11 This is a graph showing the detection data of the bending deformation of the forging after heat treatment in an embodiment of the present invention.

[0035] Figure 12 This is a graph showing the detection data of the blade twist deformation after heat treatment in an embodiment of the present invention.

[0036] Reference numerals: 1-base, 2-material rack, 21-material tray fixing frame, 22-material tray fixing position, 3-material tray, 31-positioning hole, 32-positioning groove, 33-tenon fixing position. Detailed Implementation

[0037] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0038] Example 1: Refer to the appendix of the instruction manual. Figure 1A heat treatment method and deformation controllable tooling for precision-forged compressor blades made of Ti6242 aerospace material, comprising the following steps:

[0039] Step 1: Cleaning: Before heat treatment, an etching process is performed to clean the surface of the parts, ensuring that the blade surface is free of oil, moisture, dust, etc., and guaranteeing that the parts are clean and uncontaminated. The etching process includes at least 6 cleaning tanks, divided into alkaline washing, pure water washing, pure water washing, etching washing, pure water washing, and hot pure water washing. The 6 tanks are operated in sequence to complete the cleaning process. The liquid composition in the etching washing tank is an 8:1 mixture of hydrofluoric acid and nitric acid; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 30-60 seconds. The liquid composition in the alkaline washing tank is a mixture of 20-25% concentration Turco 5948DPM cleaning agent and pure water; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 3-5 minutes. The liquid composition in the pure water washing tank is pure water; the cleaning time is 2-3 minutes, and the temperature is 15-35 degrees Celsius. The temperature of the hot pure water washing is 70-80 degrees Celsius, and the cleaning time is 2-3 minutes. The cleaning process can be repeated or cyclical depending on the usage requirements, until the blades are visually cleaned with hot pure water. Only after the blades are thoroughly cleaned should they be placed into the vacuum furnace.

[0040] Step 2: Solution heat treatment: Hang the blades vertically on the material tray, and place the tenons in the positioning slots of the material tray; after the blades are placed, place one thermocouple on the blade in the center area of ​​the material rack, and place the other thermocouple on the blade in the edge area of ​​the material rack; push the material rack into the vacuum furnace, ensuring that it is within the effective heating area, connect the thermocouples and the equipment, the heating temperature is (Tβ-20)℃±10℃, the holding time is 50min, after the holding time is completed, fill with argon gas with a purity ≥99.999% at 1~1.5bar, cool the parts to below 60℃, and then air cool to room temperature (0-25℃), remove the parts, mark the markings, and place them in the material frame.

[0041] Step 3: Vibratory finishing: Place the parts into a vibratory finishing machine for finishing. The finishing time is 2 hours, the frequency is set to 40-50Hz, and the abrasive medium is ceramic medium. After finishing, clean the parts with pure water to remove the finishing liquid residue on the surface of the parts. The components of the finishing liquid include: nonylphenol polyoxyethylene 6 ether, fatty acid glycerol ester, triethanolamine lauryl sulfate, sodium citrate, sodium sulfite, and deionized water.

[0042] Step 4: Thickness grouping (generally divided into 4-5 groups, each group consisting of 0.05mm thickness) and chemical milling (the bath solution is a 4:1 mixture of hydrofluoric acid and nitric acid, the temperature is 15-35 degrees Celsius, and the time is 5-10 minutes): Use an inductance meter (model: F100 touch-sensitive pneumatic inductance meter) to detect the surface thickness. For blades with thickness exceeding the tolerance (normal thickness is within the tolerance of -0.05 to +0.15mm, and the thickness exceeding the tolerance here refers to blades with abnormal thickness), chemical milling is used to remove the excess surface thickness until the process requirements are met.

[0043] Step 5: Bending and Torsion Correction: Use an inductance meter and bending and torsion testing fixture to check the flange, torsion angle, and bending dimensions of the final forging. For dimensions that exceed the tolerance, use pliers to clamp the blade and correct the values ​​of its flange, torsion angle, and bending to ensure that the flange, torsion angle, and bending dimensions meet the process requirements. The inductance meter is an F100 touch-sensitive pneumatic inductance meter, which is a testing device that conforms to national standards.

[0044] Step 6: Aging heat treatment: Place the above forgings into a vacuum heat treatment furnace, heat to 595±10℃, hold for 480min, after holding, fill with argon gas of 1~1.5bar with a purity ≥99.999%, cool the parts to below 60℃, remove from the furnace and air cool to room temperature, remove the parts, mark them and place them in the material frame.

[0045] Step 7: Final inspection and transfer to machining: Use a 10x magnifying glass to perform 100% inspection of the forgings. Check the surface of the forgings for visual defects such as cracks, folds, scratches, dents, pits, etc. Check whether the dimensions of the forging edge plate, bending, twisting angle, contour, thickness, etc. meet the process requirements. Transfer the qualified blades to machining, and perform machining processes such as milling the exhaust edge, cutting the blade tip, and milling the blade root to obtain the final finished blade.

[0046] Heat treatment temperature according to (T) β Solution heat treatment was performed at -20℃ for 50 minutes, followed by aging heat treatment at 595℃ for 480 minutes. The temperature difference allowed by the specifications was selected as much as possible to reduce deformation caused by high temperature during heat treatment. Inert gas argon was used for cooling in both solution and aging heat treatments to effectively control the cooling rate and ensure that dimensional deformation is minimized. Vacuum furnaces were used for both solution and aging heat treatments to effectively prevent surface oxidation of the titanium alloy blades.

[0047] The blade with a normal thickness that meets the process requirements is a blade with a thickness tolerance of -0.05 to +0.15 mm. The thickness deviation mentioned in this application refers to a blade with a thickness tolerance that is not within the tolerance range of -0.05 to +0.15 mm.

[0048] See the attached instruction manual. Figure 2-5 A controllable tooling for heat treatment deformation of precision-forged compressor blades made of Ti6242 aerospace material, characterized in that it comprises: a base 1, a material rack 2, and a material tray 3. The material rack 2 is fixed on the base 1. A material tray fixing frame 21 is provided on the material rack 2. The material tray fixing frame 21 has four layers, with a gap reserved between adjacent material tray fixing frames 21. A material tray fixing position 22 is provided on the material tray fixing frame 21. The material tray 3 is correspondingly fixed on the material tray fixing position 22. A positioning hole 31 is provided on the material tray 3, and a positioning groove 32 is provided on the positioning hole 31. At least one hole 31 is provided, and the positioning holes 31 are evenly distributed on the material tray 3; at least one positioning groove 32 is provided on each positioning hole 31, and each positioning groove 32 is provided with a tenon fixing position 33; the base 1 and the material rack 2 are made of molybdenum-containing high-temperature alloy material, and the material tray 3 is made of mullite; the molybdenum-containing high-temperature alloy material has a high melting point, high strength and low expansion coefficient; mullite has the characteristics of high melting point, high temperature stability, low expansion coefficient and not easy to deform, and does not react with metal materials, so it does not cause secondary pollution to the heat treatment heating furnace.

[0049] The tooling of this invention is designed based on the tenon shape and size of the precision-forged blade, making it unique. By controlling the dimensional accuracy of the tooling, it ensures that the edge plate surface of the pre-forged blade retains only 1-2mm of contact surface, minimizing contact with the edge plate surface of the precision-forged blade while maintaining stability in positioning the precision-forged blade. The positioning groove 32 allows for vertical hoisting of the precision-forged blade with its center of gravity pointing downwards, reducing heating deformation in the heat treatment furnace. The tooling tray is made of mullite, which has the advantages of high temperature resistance, resistance to deformation, and no secondary pollution to the heat treatment furnace. Simultaneously, this material has a certain degree of plasticity, preventing metal softening of Ti6242 material under high-temperature heat treatment and surface defects at the contact points with the tooling material.

[0050] Example 2: Refer to the appendix of the instruction manual. Figure 6-12 A heat treatment process for the sixth-stage rotor blades of an aero-engine compressor based on Ti6242 material, comprising the following heat treatment process flow:

[0051] (1) Cleaning: Before heat treatment, a corrosion process is carried out to clean the dirt on the surface of the parts and ensure that the parts are clean and free of contamination.

[0052] (2) Solution heat treatment: Place the above forgings into a vacuum heat treatment furnace and heat them at a temperature equal to (phase transformation point T). β -20℃±10℃, hold for 50 minutes, purge with argon gas and cool to below 60℃, then air cool to room temperature: 0-25℃; T β： This indicates the temperature at the phase transition point.

[0053] (3) Vibration finishing: Put the parts into a vibration finishing machine. The finishing time is 2 hours, the frequency is set to 40 - 50 Hz, the finishing abrasive medium is ceramic medium. After finishing, wash the parts with water to remove the residual finishing liquid on the part surface.

[0054] (4) Thickness grouping and chemical milling: Use an inductance gauge to quickly detect the thickness of the profile. For the blades with out-of-tolerance thickness, adopt chemical milling to remove the excess profile thickness until it meets the process requirements.

[0055] (5) Bending and torsion correction: Use an inductance gauge and a bending and torsion detection fixture to quickly check the flange, torsion angle and bending dimensions of the final forging. For the out-of-tolerance dimensions, use a tool clamp to hold the blade and correct the values of its flange, torsion angle and bending to make its flange, torsion angle and bending dimensions meet the process requirements.

[0056] (6) Aging heat treatment: Put the above forgings into a vacuum heat treatment furnace. The heating temperature is 595 ± 10 °C, the holding time is 480 min, fill with argon gas and cool to below 60 °C, then take out of the furnace and air cool to room temperature 0 - 25 °C.

[0057] (7) Final inspection and transfer to machining: Use a 10 - power magnifying glass to conduct 100% inspection on the forgings. Check that the surface of the forgings has no visual defects such as cracks, folds, scratches, dents, pits, pitting, etc. Check that the dimensions of the flange, bending, torsion angle, contour, thickness, etc. of the forgings meet the process requirements. Transfer the above qualified blades to machining and perform machining processes such as milling the inlet and outlet edges, cutting the blade tip and milling the blade root to obtain the final finished blades.

[0058] In this embodiment, the above heat treatment process steps are used to successfully produce the forgings of the sixth - stage compressor rotor blades of the aero - engine made of Ti6242 material. After 100% visual inspection, the forgings have a complete shape, and there are no defects such as cracks, folds and pressing injuries on the surface; the dimensional characteristics of the forgings are qualified. Randomly select forgings and mechanical property test bars from them to conduct metallographic structure and mechanical property tests. The results are shown in the blade profile dimension report of the forgings (refer to the appendix of the specification Figure 6 ).

[0059] As Figure 6 shown: By detecting the maximum thickness, inlet edge thickness, outlet edge thickness, torsion angle, bending profile dimensions of the cross - sections of the forging blades 1 - 1..9 - 9, each index meets the dimensional accuracy requirements of the drawing.

[0060] Macro - structure: No cracks, folds, pores, segregation, metal or non - metal inclusions and other metallurgical defects visible to the naked eye are found. The longitudinal macro - structure of the blade body of the forging is shown in the appendix of the specification Figure 7 .

[0061] High-magnification microstructure: conforms to HB 7726–2002 and AMS4928 specifications, with uniform α+β microstructure and no requirement for elongated α phase. High-magnification microstructure of forgings (as per the attached specification). Figure 8 (As shown). α and β represent the alpha phase and beta phase, respectively.

[0062] Room temperature tensile properties: The room temperature tensile properties of the heat-treated forgings from the examples were tested. The results of the room temperature tensile properties of the forgings are shown in the attached document. Figure 9 (As shown in the figure). It can be seen that the results obtained are all better than the standard requirements.

[0063] like Figure 9 As shown: Test data for samples 1# / 2# / 3# represent one batch; test data for samples 4# / 5# / 6# represent another batch. The tensile strength, yield strength, elongation (5D), and end-face shrinkage of the blades were tested under the same heat treatment conditions: solution temperature 980℃ and aging temperature 595℃. All indicators exceeded the specifications and met the requirements.

[0064] Hydrogen content testing: The hydrogen content of the heat-treated forgings from this example was tested. The hydrogen content test results for the forgings in this example are shown in the attached manual. Figure 10 (As shown in the figure). It can be seen that the results obtained are all better than the standard requirements.

[0065] like Figure 10 As shown: Test data for samples 1# / 2# / 3# represent one batch; test data for samples 4# / 5# / 6# represent another batch. Test method: ASTM E1447-22; Hydrogen content data for blade forgings were tested under the same heat treatment temperatures: solution temperature 980℃ and aging temperature 595℃. The hydrogen content test results for each sample ranged from 19 to 33 ppm, far less than the specification requirement of ≤150 ppm, thus meeting the specification requirements.

[0066] pass Figures 11-12 As shown, after heat treatment using the method of this invention, the bending deformation and torsional deformation data of 30 series of blades after heat treatment are analyzed and tested. It can be seen that by implementing this method, and by measuring the blade profile dimensions before and after heat treatment using 9 cross-sections from 1-1 to 9-9 of the forged blades, the blade profile deformation during the heat treatment process is controllable. The bending deformation is between -0.15 and -0.35, and the torsional deformation is between 0 and -0.5, showing good consistency and high reliability. Iterative compensation for the final forging dimensions and bending / torsion correction based on the deformation law of heat treatment can significantly improve the quality pass rate and production efficiency of the blades.

[0067] The above-described embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A heat treatment method for precision-forged compressor blades made of Ti6242 aerospace material, characterized in that: Includes the following steps: Step 1: Cleaning: Before heat treatment, an etching process is carried out to clean the surface dirt of the parts and ensure that the parts are clean and free of contamination. The etching process contains six cleaning tanks, which are divided into alkaline washing, pure water washing, pure water washing, etching washing, pure water washing, and hot pure water washing. The six tanks are operated in sequence to complete the cleaning process. The corrosion cleaning tank contains a liquid composition of hydrofluoric acid and nitric acid in an 8:1 ratio; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 30-60 seconds. The alkaline cleaning tank contains a liquid composition of a 20-25% concentration cleaning agent and pure water; the cleaning temperature is 15-35 degrees Celsius, and the cleaning time is 3-5 minutes. The pure water cleaning tank contains pure water; the cleaning time is 2-3 minutes, and the temperature is 15-35 degrees Celsius. The hot pure water cleaning tank contains pure water; the cleaning temperature is 70-80 degrees Celsius, and the cleaning time is 2-3 minutes. Step 2: Solution heat treatment: Place the above forgings into a vacuum heat treatment furnace and heat them to the phase transformation point T. β -20℃±10℃, the T β The temperature indicates the phase transition point; after heat preservation, it is purged with argon gas and cooled to below 60℃, then air-cooled to 0-25℃; Step 3: Vibratory finishing: Place the parts into a vibratory finishing machine for finishing. After finishing, wash the parts with pure water to remove any residual finishing liquid from the surface of the parts. Step 4: Thickness grouping and chemical milling: Use an inductance meter to detect the thickness of the profile. For blades with excessive thickness, the excess profile thickness needs to be removed until the process requirements are met. Step 5: Bending and Torsion Correction: Inspect the flange, torsion angle and bending dimensions of the final forging. For dimensions that are out of tolerance, use pliers to hold the blade and correct the values ​​of its flange, torsion angle and bending to make its flange, torsion angle and bending dimensions meet the process requirements. Step 6: Aging heat treatment: Place the above forgings into a vacuum heat treatment furnace, heat to 595±10℃, hold at the temperature, then cool to below 60℃ with argon gas, and air cool to room temperature: 0-25℃ after removing from the furnace. Step 7: Final inspection and transfer to machining: Inspect the blades and transfer the qualified blades to machining, and perform milling of the exhaust edge, cutting of the blade tip and milling of the blade root to obtain the final finished blade.

2. The heat treatment method for precision-forged compressor blades made of Ti6242 material according to claim 1, characterized in that: The heat preservation time in step 2 is 50 minutes; the heat preservation time in step 6 is 480 minutes.

3. The heat treatment method for precision-forged compressor blades made of Ti6242 material according to claim 1, characterized in that: In step 3, the polishing time is 2 hours, the frequency is set to 40-50Hz, and the polishing abrasive medium is selected as ceramic medium.

4. The heat treatment method for precision-forged compressor blades made of Ti6242 material according to claim 1, characterized in that: In step 4, the excess surface thickness of the blades with excessive thickness is removed by chemical milling.

5. The heat treatment method for precision-forged compressor blades made of Ti6242 material according to claim 1, characterized in that: In step 5, the flange, torsion angle and bending dimensions of the final forging are inspected using an inductance meter and a bending and torsion testing fixture.

6. The heat treatment method for precision-forged compressor blades made of Ti6242 material according to claim 1, characterized in that: In step 7, a 10x magnifying glass is used to perform a 100% inspection of the forging. The surface of the forging is checked for visual defects such as cracks, folds, scratches, dents, pits, and pockmarks. The dimensions of the forging's edge plate, bending, twisting, contour, and thickness are checked to see if they meet the process requirements.

7. A controllable tooling fixture for heat treatment deformation of precision-forged compressor blades made of aerospace Ti6242 material, used to perform the heat treatment method for precision-forged compressor blades made of aerospace Ti6242 material as described in claim 1, characterized in that, include: The base (1), the material rack (2), and the material tray (3) are provided. The material rack (2) is fixed on the base (1). The material rack (2) is provided with a material tray fixing frame (21). The material tray fixing frame (21) has four layers. There is a gap between adjacent material tray fixing frames (21). The material tray fixing frame (21) is provided with a material tray fixing position (22). The material tray (3) is fixed on the material tray fixing position (22). The material tray (3) is provided with a positioning hole (31). The positioning hole (31) is provided with a positioning groove (32).

8. The controllable tooling for heat treatment deformation of precision-forged compressor blades made of Ti6242 material according to claim 7, characterized in that: At least one positioning hole (31) is provided, and the positioning holes (31) are evenly distributed on the material tray (3).

9. The controllable tooling for heat treatment deformation of precision-forged compressor blades made of Ti6242 material according to claim 8, characterized in that: At least one positioning groove (32) is provided on each positioning hole (31), and each positioning groove (32) is provided with a tenon fixing position (33).

10. The controllable tooling for heat treatment deformation of aerospace Ti6242 material compressor precision forging blades according to claim 7, characterized in that: The base (1) and the rack (2) are made of a high-temperature alloy containing molybdenum; the tray (3) is made of mullite.

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