Preparation method of Co-based hard-to-deform surfacing welding wire for aerospace

Abstract

The invention discloses a preparation method of a Co-based hard-to-deform surfacing welding wire for aerospace, which comprises the following steps of: 1, selecting an outer coating tube shell according to the welding wire, and calculating the powder components of an inner core; secondly, one end of the outer covering pipe shell is sealed through rotary swaging, and the outer covering pipe shell with one sealed end is obtained; 3, filling the outer coating tube shell with the inner core powder to obtain the outer coating tube shell with one sealed end filled with the powder; fourthly, the powder-filled end is sealed and covered with the tube shell in a rotary swaging mode, and the powder-filled outer covering tube shell is obtained; and fifthly, the powder filling outer covering pipe shell is drawn and sintered, and the Co-based hard-to-deform surfacing welding wire for aerospace is obtained. By designing the components of the inner core powder and the components and specifications of the outer covering pipe shell and combining drawing and sintering, stable industrial production of the multi-mark and multi-specification Co-based hard-to-deform surfacing welding wire is achieved, the welding wire can improve the quality and strength of a welding joint, stable operation of an airspace engine in an extreme environment is ensured, and the welding wire has the advantages of being simple in structure and convenient to operate. And welding defects and rework rate are reduced, and manufacturing and maintenance cost is reduced.

Description

Technical Field

[0001] The invention belongs to the technical field of welding material preparation, and in particular relates to a method for preparing a Co-based hard-to-deform cladding welding wire for aerospace. Background Art

[0002] Space engines represent the top level in the aerospace field. Their design and manufacturing involve complex working environments under extreme conditions such as high temperature, high pressure, and high speed, and require overcoming many technical difficulties. Their performance directly determines the carrying capacity and flight efficiency of spacecraft, and is the key to entering space and exploring deep space. A large number of high-temperature alloy materials and their structural parts are used in space engines. Through welding, high-quality connections can be achieved on these materials, and precise connections of these complex structures can be achieved, ensuring the strength and sealing of the connection joints, thereby ensuring the overall performance and reliability of the equipment.

[0003] Welding requires various solders, among which Co-based brazing materials have excellent process performance, high joint strength, good heat resistance, and good anti-oxidation and anti-corrosion capabilities. Therefore, they are widely used in the connection of Co-based high-temperature alloy blades and important parts that require high-temperature and long-lasting performance. High-quality and high-performance Co-based solders play a key role in the manufacturing and maintenance of aerospace engines. They can not only improve the quality and strength of welded joints and ensure the stable operation of aerospace engines in extreme environments, but also reduce welding defects and rework rates, reduce manufacturing and maintenance costs, and improve economic benefits.

[0004] Since Co-based solder has the characteristics of high melting point, high brittleness and high hardness, it is difficult to deform and plastically process. At present, it is mainly supplied in the form of powder, paste, amorphous foil and strip on the market, and is mainly used in brazing process. However, the hot end parts of aerospace engines, especially key parts such as blades, often need to be welded by surfacing process. The above-mentioned Co-based solder is difficult to meet the needs of actual working conditions, and it is difficult to directly form Co-based solder into alloy welding wire through plastic deformation processing.

[0005] Therefore, it is urgent to develop a preparation process that can mass-produce high-quality, high-performance Co-based difficult-to-deform cladding wire. Summary of the invention

[0006] The technical problem to be solved by the present invention is to provide a method for preparing a Co-based hard-to-deform overlay welding wire for aerospace in view of the above-mentioned deficiencies of the prior art. The method designs and adjusts the composition of the inner core powder and the composition and specifications of the outer tube shell, and combines the drawing and sintering processes to prepare high-quality and high-performance Co-based hard-to-deform overlay welding wire for aerospace, thereby providing more high-quality and high-performance Co-based hard-to-deform overlay welding wires for the aerospace field.

[0007] In order to solve the above technical problems, the technical solution adopted by the present invention is: a method for preparing a Co-based hard-to-deform cladding wire for aerospace, characterized in that the method comprises the following steps:

[0008] Step 1: According to the composition and specification of the outer tube shell of the Co-based hard-to-deform cladding welding wire to be prepared, the composition of the inner core powder is calculated by combining the formula; the formula is: X = AX m +BX n , where X is the mass percentage of an element in the Co-based hard-to-deform cladding wire, X m is the mass percentage of the element in the outer tube shell, A is the cross-sectional proportion of the outer tube shell in the Co-based difficult-to-deform cladding wire, X n is the mass percentage of the element in the inner core powder, and B is the cross-sectional proportion of the inner core powder in the Co-based difficult-to-deform cladding wire;

[0009] Step 2: Clean and dry the outer tube shell selected in step 1, and then perform rotary forging to seal one end to obtain an outer tube shell with one end sealed;

[0010] Step 3, filling the inner core powder selected in step 1 into the outer tube shell with one end sealed obtained in step 2, accompanied by vibration, to obtain the outer tube shell with one end sealed filled with powder;

[0011] Step 4: Forging and sealing the unsealed end of the sealed outer tube shell with one end filled with powder obtained in step 3 to obtain a powder filled outer tube shell;

[0012] Step 5: Drawing the powder-filled outer shell obtained in step 4, and then sintering it to obtain a Co-based difficult-to-deform cladding wire for aerospace.

[0013] According to the composition and specification of the selected outer tube shell of the Co-based difficult-deformation cladding welding wire to be prepared, the component elements of the prepared Co-based difficult-deformation cladding welding wire should include the element types contained in the outer tube shell, and the diameter of the outer tube shell can reach the diameter of the Co-based difficult-deformation cladding welding wire to be prepared within the maximum processing deformation range, and then the composition of the inner core powder is calculated in combination with a formula, so as to ensure that the outer tube shell and the inner core powder are prepared to meet the composition requirements, and the preparation of Co-based difficult-deformation cladding welding wires of multiple brands and specifications is realized, and the quality of the welding wire is improved by removing impurities on the surface through cleaning and drying, and one end is sealed by rotary forging to ensure that the inner core powder filled subsequently does not leak, and the inner core powder is sealed by the inner core powder. The final filling is accompanied by vibration to ensure the compaction of the inner core powder filled in the outer tube shell, which ensures the accuracy of the composition of the prepared Co-based difficult-to-deform cladding welding wire, and at the same time ensures that the inner core powder will not cause the outer shell to rupture due to insufficient fluidity during the deformation process. After the powder filling is completed, the rotary forging and sealing treatment is carried out to ensure that the inner core powder does not leak. It is processed to the target diameter by drawing, and the filling powder is sintered by a sintering process to complete the preparation of Co-based difficult-to-deform cladding welding wire for aerospace. It can not only improve the quality and strength of the welded joint and ensure the stable operation of the aerospace engine in extreme environments, but also reduce welding defects and rework rate, reduce manufacturing and maintenance costs, and improve economic benefits.

[0014] The above-mentioned method for preparing a Co-based hard-to-deform overlay welding wire for aerospace is characterized in that the Co-based hard-to-deform overlay welding wire in step 1 includes D812 overlay welding wire and CM-64 overlay welding wire. The present invention solves the problem that the traditional D812 overlay welding wire, which is difficult to plastically deform, is produced by coating and there is no corresponding overlay welding wire for CM-64 overlay welding wire by limiting the composition of the Co-based hard-to-deform overlay welding wire, wherein the brand of the CM-64 overlay welding wire is Stellite694.

[0015] The above-mentioned method for preparing a Co-based hard-to-deform overlay welding wire for aerospace is characterized in that the material of the outer tube shell in step one is a metal element or alloy with higher plasticity than the Co-based hard-to-deform overlay welding wire to be prepared, the outer tube shell is in an annealed state, and the length of the outer tube shell is less than 1000mm. The present invention selects an outer tube shell with better plasticity, and the plasticity requirement of the outer tube shell is that the diameter of the Co-based hard-to-deform overlay welding wire to be prepared can be reached within the maximum processing deformation range, so that it is suitable for subsequent drawing processing, and it is convenient to obtain a Co-based hard-to-deform overlay welding wire of suitable size. By controlling the outer tube shell to be different metal elements or alloy materials, it is suitable for preparing Co-based hard-to-deform overlay welding wires with different composition requirements. By selecting an annealed outer tube shell with a larger processable deformation, it is suitable for subsequent drawing processing deformation. By controlling the length of the outer tube shell, it is convenient for drawing deformation.

[0016] The above-mentioned method for preparing a Co-based hard-to-deform overlay welding wire for aerospace is characterized in that the mass purity of the inner core powder in step 1 is greater than 99.9%, the particle size is -100 mesh to +200 mesh, and the inner core powder includes metal element powder and intermediate alloy powder. The present invention ensures the purity of the Co-based hard-to-deform overlay welding wire and improves the quality of the welding wire by controlling the mass purity of the inner core powder. By controlling the particle size, the outer shell is prevented from being broken due to insufficient fluidity during processing. By using different metal element powders and intermediate alloy powders as the inner core powder, it is suitable for preparing Co-based hard-to-deform overlay welding wires with different composition requirements.

[0017] The above-mentioned method for preparing a Co-based non-deformable cladding wire for aerospace is characterized in that the inner core powder in step 1 is mixed uniformly by a vacuum ball milling process. The present invention uses a vacuum ball milling process to fully mix the metal element powder and the intermediate alloy powder without introducing impurities, thereby ensuring the uniformity of the composition of the Co-based non-deformable cladding wire.

[0018] The above-mentioned method for preparing a Co-based hard-to-deform cladding wire for aerospace is characterized in that the rotary forging and sealing in step 2 and step 4 are both step-by-step rotary forging. The present invention avoids cracking of the outer tube shell caused by excessive processing by adopting step-by-step rotary forging.

[0019] The above-mentioned method for preparing a Co-based hard-to-deform cladding wire for aerospace is characterized in that the drawing in step 5 is step-by-step drawing. The present invention avoids cracking of the outer tube shell caused by excessive processing by adopting step-by-step drawing.

[0020] The above-mentioned method for preparing a Co-based non-deformable cladding wire for aerospace is characterized in that the drawing is followed by cleaning in step 5. The present invention ensures the quality of the Co-based non-deformable cladding wire by removing impurities outside the outer tube shell.

[0021] The above-mentioned method for preparing a Co-based non-deformable cladding wire for aerospace is characterized in that the sintering in step 5 is vacuum sintering. The present invention prevents the introduction of impurities and oxidation of the inner core powder through vacuum sintering, thereby ensuring the quality of the Co-based non-deformable cladding wire.

[0022] The above-mentioned method for preparing a Co-based non-deformable cladding wire for aerospace is characterized in that the Co-based non-deformable cladding wire for aerospace is used after being sheared in step 5. The present invention shears the Co-based non-deformable cladding wire for aerospace so that it is suitable for use under various conditions.

[0023] Compared with the prior art, the present invention has the following advantages:

[0024] 1. The present invention designs and adjusts the composition of the inner core powder and the composition and specifications of the outer tube shell, and combines the drawing and sintering processes to prepare high-quality, high-performance Co-based hard-to-deform cladding welding wire for aerospace, thereby providing more high-quality, high-performance Co-based hard-to-deform cladding welding wires for the aerospace field. The Co-based hard-to-deform cladding welding wire can not only improve the quality and strength of the welded joints, ensure the stable operation of the aerospace engine in extreme environments, but also reduce welding defects and rework rates, reduce manufacturing and maintenance costs, and improve economic benefits.

[0025] 2. The present invention can ensure that the content of each element in the prepared welding wire is the same as the target Co-based difficult-to-deform cladding welding wire by adjusting the composition and specifications of the outer coating shell and the composition of the inner core powder, and can also prepare a variety of standard compositions of Co-based difficult-to-deform cladding welding wires, thereby achieving the composition of the prepared Co-based difficult-to-deform cladding welding wire meeting the standards. The currently widely used Co-based difficult-to-deform cladding welding wire is consistent with the main constituent elements of the selected alloy outer coating shell, or covers the main constituent elements of the selected alloy outer coating shell.

[0026] 3. The outer tube shell selected in the present invention has good plastic processing performance. The wire can be prepared by step-by-step drawing, and wires of various specifications can be prepared by controlling the number of drawing passes, thereby achieving the prepared Co-based difficult-to-deform cladding wire specifications that meet the standards.

[0027] 4. The Co-based hard-to-deform surfacing welding wire for aerospace use of the present invention is a Co-based alloy solder with high melting point, high brittleness, high hardness, and difficult to perform plastic deformation processing, such as D812 surfacing welding wire or CM-64 surfacing welding wire. The Co-based hard-to-deform surfacing welding wire for aerospace use is mainly used in the aerospace field, such as CoCo-based hard-to-deform surfacing welding wire for surfacing welding of hot end parts such as engine blades.

[0028] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a processing technology roadmap of the Co-based hard-to-deform cladding welding wire for aerospace use of the present invention.

[0030] Figure 2 This is a physical picture of the outer tube shell and D812 cladding welding wire in Example 1 of the present invention.

[0031] Figure 3 This is a comparison diagram of the cross section of the D812 cladding wire in Example 1 of the present invention before and after grinding. DETAILED DESCRIPTION

[0032] Example 1

[0033] This embodiment is to prepare D812 cladding wire with a diameter of 2 mm and a length of 400 mm.

[0034] This embodiment includes the following steps:

[0035] Step 1: According to the composition of D812 cladding wire, see Table 1, select the outer tube shell with an outer diameter of 3mm, a wall thickness of 0.2mm, and an annealed L605 alloy tube. The composition is shown in Table 2. The outer tube shell accounts for 24.9% of the cross section, and the inner core powder accounts for 75.1% of the cross section. Combined with the formula X = AX m +BX n The composition of the inner core powder is shown in Table 3. According to Table 3, the inner core powder is selected as Co, Cr, Fe, W, Si, C single substance powder and MnFe, FeB master alloy powder with a mass purity greater than 99.9% and a particle size of -100 mesh to +200 mesh, and the selected inner core powder is mixed uniformly by vacuum ball milling process;

[0036] Table 1 (Unit: wt.%)

[0037] Co Cr Fe Mn W Si C B margin 25～32 ≤5 ≤2 7～10 ≤2 1～1.7 0.004～0.005

[0038] Table 2 (Unit: wt.%)

[0039] Co Cr Fe Mn W Si C P S margin 20.15 0.08 1.54 15 0.12 0.1 ＜0.01 ＜0.01

[0040] Table 3 (Unit: wt.%)

[0041] Co Cr Fe Mn W Si C B margin 33.27 5.3 2.15 8.34 2.62 1.96 0.006

[0042] The calculation process is as follows: Cr element calculation, taking X as 30, A as 24.9%, X m is 20.15, B is 75.1%, according to the formula X = AX m +BX n , we get X n is 33.27, and the calculation results are shown in Table 3;

[0043] Step 2: Clean the outer surface of the outer tube shell selected in step 1 with ethanol and dry it, and then perform rotary forging and sealing at one end step by step, wherein the diameters of the rotary forging dies are 2 mm to 4 mm, 1 mm to 3 mm, and 1 mm, respectively, to obtain an outer tube shell with one end sealed;

[0044] Step 3, filling the inner core powder selected in step 1 into the outer tube shell with one end sealed obtained in step 2, accompanied by vibration, to obtain the outer tube shell with one end sealed filled with powder;

[0045] Step 4: The unsealed end of the sealed outer tube shell of the powder-filled end obtained in step 3 is sealed by rotary forging step by step, wherein the diameters of the rotary forging dies are 2 mm to 4 mm, 1 mm to 3 mm, and 1 mm, respectively, to obtain a powder-filled outer tube shell;

[0046] Step 5: The powder-filled outer tube shell obtained in step 4 is drawn step by step and then cleaned, wherein the diameters of the step-by-step drawing are 2.8mm, 2.6mm, 2.4mm, 2.2mm, and 2.0mm respectively, and then vacuum sintered at 1100°C and finally sheared to obtain multiple sections of D812 aerospace cladding wire with a diameter of 2mm and a length of 400mm.

[0047] Figure 2 This is a physical picture of the outer tube shell and D812 cladding welding wire in this embodiment. Figure 2 The upper middle part is the outer tube shell, and the lower part is the D812 cladding wire. Figure 2 It can be seen that the outer tube shell has good surface quality and straightness, and the prepared D812 cladding wire has good surface quality and straightness, indicating that the Co-based difficult-to-deform cladding wire prepared in this embodiment has higher quality.

[0048] Figure 3 This is a comparison diagram of the cross section of the D812 cladding wire in this embodiment before and after grinding. Figure 3 The left side is before polishing, and the right side is after polishing. Figure 3 It can be seen that the inner core powder and the outer tube shell maintain good concentricity, indicating that the deformation uniformity is maintained during the processing. In addition, through the polished cross section, it can be seen that the sintered inner core powder has been solidified, ensuring the reliability of the welding wire during the surfacing process.

[0049] Example 2

[0050] This embodiment is to prepare a CM64 cladding wire with a diameter of 1.8 mm and a length of 300 mm.

[0051] Step 1: According to the composition of CM64 cladding wire, see Table 4, select the outer tube shell with an outer diameter of 3mm, a wall thickness of 0.1mm, and an annealed nickel tube. The composition is shown in Table 5. The outer tube shell cross-section accounts for 12.9%, and the inner core powder cross-section accounts for 87.1%. Combined with the formula X = AX m +BX n The composition of the inner core powder is shown in Table 6. According to Table 6, the inner core powder is selected as Co, Cr, Fe, Ni, W, Si single substance powder with a mass purity greater than 99.9% and a particle size of -100 mesh to +200 mesh and MnFe, VFe, FeB intermediate alloy powder, and the selected inner core powder is mixed uniformly by vacuum ball milling process;

[0052] Table 4 (Unit: wt.%)

[0053] Co Cr Fe Mn Ni W Si V B margin 25～30 ≤2 ≤0.5 9～12 18～23 ≤0.5 0.5～1.5 0.01～0.03

[0054] Table 5 (unit: wt.%)

[0055] Ni C P S Other impurities margin ≤0.5 ≤0.01 ≤0.01 ≤0.05

[0056] Table 6 (Unit: wt.%)

[0057] Co Cr Fe Mn W Si V B margin 30 2.5 0.5 21 0.5 1.2 0.04

[0058] Step 2: Clean the outer surface of the outer tube shell selected in step 1 with ethanol and dry it, and then perform rotary forging and sealing at one end step by step, wherein the diameters of the rotary forging dies are 2 mm to 4 mm, 1 mm to 3 mm, and 1 mm, respectively, to obtain an outer tube shell with one end sealed;

[0059] Step 3, filling the inner core powder selected in step 1 into the outer tube shell with one end sealed obtained in step 2, accompanied by vibration, to obtain the outer tube shell with one end sealed filled with powder;

[0060] Step 4: The unsealed end of the sealed outer tube shell of the powder-filled end obtained in step 3 is sealed by rotary forging step by step, wherein the diameters of the rotary forging dies are 2 mm to 4 mm, 1 mm to 3 mm, and 1 mm, respectively, to obtain a powder-filled outer tube shell;

[0061] Step 5: The powder-filled outer tube shell obtained in step 4 is drawn step by step and then cleaned, wherein the diameters of the step-by-step drawing are 2.8 mm, 2.6 mm, 2.4 mm, 2.2 mm, 2.0 mm, and 1.8 mm, respectively, and then vacuum sintered at 1100°C and finally sheared to obtain multiple sections of CM64 cladding wire for aerospace with a diameter of 1.8 mm and a length of 300 mm.

[0062] The above is only a preferred embodiment of the present invention and does not limit the present invention in any way. Any simple modification, change and equivalent change made to the above embodiment according to the technical essence of the present invention still falls within the protection scope of the technical solution of the present invention.

Claims

1. A method for preparing a Co-based hard-to-deform cladding wire for aerospace, characterized in that: The method comprises the following steps: Step 1: According to the composition and specification of the outer tube shell of the Co-based hard-to-deform cladding welding wire to be prepared, the composition of the inner core powder is calculated by combining the formula; the formula is: X = AX m +BX n , where X is the mass percentage of an element in the Co-based hard-to-deform cladding wire, X m is the mass percentage of the element in the outer tube shell, A is the cross-sectional proportion of the outer tube shell in the Co-based difficult-to-deform cladding wire, X n is the mass percentage of the element in the inner core powder, and B is the cross-sectional proportion of the inner core powder in the Co-based difficult-to-deform cladding wire; Step 2: Clean and dry the outer tube shell selected in step 1, and then perform rotary forging to seal one end to obtain an outer tube shell with one end sealed; Step 3, filling the inner core powder selected in step 1 into the outer tube shell with one end sealed obtained in step 2, accompanied by vibration, to obtain the outer tube shell with one end sealed filled with powder; Step 4: Forging and sealing the unsealed end of the sealed outer tube shell with one end filled with powder obtained in step 3 to obtain a powder filled outer tube shell; Step 5: Drawing the powder-filled outer shell obtained in step 4, and then sintering it to obtain a Co-based difficult-to-deform cladding wire for aerospace.

2. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The Co-based hard-to-deform surfacing welding wire described in step 1 includes D812 surfacing welding wire and CM-64 surfacing welding wire.

3. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The material of the outer tube shell in step 1 is a metal element or alloy with higher plasticity than the required Co-based difficult-to-deform cladding welding wire, the outer tube shell is in an annealed state, and the length of the outer tube shell is less than 1000 mm.

4. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The mass purity of the inner core powder in step 1 is greater than 99.9%, and the particle size is -100 mesh to +200 mesh. The inner core powder includes metal element powder and intermediate alloy powder.

5. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The inner core powder in step 1 is mixed evenly by vacuum ball milling process.

6. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The rotary forging and sealing in step 2 and step 4 are both performed step by step.

7. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The drawing in step 5 is step-by-step drawing.

8. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: Clean after pulling as described in step five.

9. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The sintering in step 5 is vacuum sintering.

10. The method for preparing a Co-based hard-to-deform cladding wire for aerospace according to claim 1, characterized in that: The Co-based difficult-to-deform cladding wire for aerospace use described in step five is cut and then used.

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