阅读说明：本技术 一种航空用镍基高温合金焊接材料 (Nickel-based high-temperature alloy welding material for aviation ) 是由 朱新军 于 2021-08-19 设计创作，主要内容包括：本发明涉及焊接材料技术领域,尤其涉及一种航空用镍基高温合金焊接材料。采用GH3044对合金母材GH1015焊接过程中,焊接头的室温力学强度较差,容易产生微裂纹。基于上述问题,本发明提供一种航空用镍基高温合金焊接材料,其将GH3044镍合金成分中的Fe等元素含量减少后,不但没有降低其焊接性能,还在一定程度上提高了焊接稳定性和焊缝的室温力学性能,取得了意料不到的技术效果。(The invention relates to the technical field of welding materials, in particular to an aviation nickel-based superalloy welding material. In the process of welding the alloy base material GH1015 by adopting GH3044, the room-temperature mechanical strength of a welding head is poor, and microcracks are easily generated. Based on the problems, the invention provides an aviation nickel-based superalloy welding material, which is characterized in that after the content of elements such as Fe in the components of the GH3044 nickel alloy is reduced, the welding performance is not reduced, the welding stability and the room-temperature mechanical property of a welding seam are improved to a certain extent, and unexpected technical effects are achieved.)

1. The nickel-based high-temperature alloy welding material for aviation is characterized by comprising the following components in percentage by mass:

2. the nickel-based superalloy welding material for aviation according to claim 1, comprising the following components in percentage by mass:

3. the nickel-based superalloy welding material for aviation according to claim 1, wherein the welding material is prepared by the following steps:

(1) adding C, Cr, W, Si, Fe and Ni into a crucible according to the formula amount, putting the crucible into a vacuum induction furnace for vacuum induction melting, then adding Al and Ti into the crucible for refining, then adding the rest elements and filling argon, and obtaining cast ingots after casting;

(2) adding the cast ingot into a slag pool, and adding slag for electroslag remelting to obtain an electroslag ingot;

(3) and adding the electroslag ingot into a heating furnace to carry out heat treatment along with the furnace, and forging and air cooling to obtain the nickel-based high-temperature alloy welding material for aviation.

4. The nickel-based superalloy welding material for aviation according to claim 3, wherein a vacuum degree during vacuum induction melting in the step (1) is less than or equal to 12 Pa.

5. The nickel-based superalloy welding material for aviation as claimed in claim 3, wherein in the step (1), the refining vacuum degree is less than or equal to 5Pa, the refining temperature is 1510-1520 ℃, and the refining time is 50-100 min.

6. The welding material of nickel-base superalloy for aviation as claimed in claim 3, wherein the pressure of argon gas filling in step (1) is 3000-5000 Pa; the temperature during argon filling is 1500-1510 ℃.

7. The aviation nickel-based superalloy welding material according to claim 3, wherein the amount of the electroslag used in the step (2) is 5-9% of the weight of the ingot, and the electroslag comprises the following components in percentage by mass:

8. the nickel-base superalloy welding material for aviation as set forth in claim 3, wherein the heat treatment temperature in the step (3) is 1120-1150 ℃ for 50-100 min.

9. The aerospace nickel-base superalloy weld material of claim 3, wherein the forging in step (3) is performed by multiple upsets.

10. The nickel-base superalloy welding material for aviation according to claim 9, wherein the upsetting reduction is equal to or more than 30% at one time, the elongation operation is performed immediately after each upsetting, the reduction is controlled to be 30-50mm, and the deformation is controlled to be equal to or more than 50% at each time.

Technical Field

The invention relates to the technical field of welding materials, in particular to an aviation nickel-based superalloy welding material.

Background

GH3044 is a solid solution strengthened nickel-based oxidation resistant alloy, has high plasticity and medium heat strength below 900 ℃, has excellent oxidation resistance and good stamping and welding process performance, and is suitable for manufacturing parts of main combustion chambers and afterburner chambers of aircraft engines working for a long time below 900 ℃.

An alloy parent metal GH1015 with a high Fe content is a common aviation forming processing material, a common welding material is GH3044, and researchers find that welding arc splashing, poor arc stability and weld joint microcracks are easily generated in the actual welding process of the alloy parent metal GH1015 by adopting GH3044, and adverse effects are generated on the mechanical properties of a butt joint.

Disclosure of Invention

Aiming at the problems in the prior art, the technical problems to be solved by the invention are as follows: in the process of welding the alloy base material GH1015 by adopting GH3044, the room-temperature mechanical strength of a welding head is poor, and microcracks are easily generated.

The technical scheme adopted by the invention for solving the technical problems is as follows: the invention provides a nickel-based high-temperature alloy welding material for aviation, which comprises the following components in percentage by mass:

specifically, the nickel-based superalloy welding material for aviation comprises the following components in percentage by mass:

specifically, the nickel-based superalloy welding material for aviation is prepared by the following steps:

(1) adding C, Cr, W, Si, Fe and Ni into a crucible according to the formula amount, putting the crucible into a vacuum induction furnace for vacuum induction melting, then adding Al and Ti into the crucible for refining, then adding the rest elements and filling argon, and obtaining cast ingots after casting;

(2) adding the cast ingot into a slag pool, and adding slag for electroslag remelting to obtain an electroslag ingot;

(3) and adding the electroslag ingot into a heating furnace to carry out heat treatment along with the furnace, and forging and air cooling to obtain the nickel-based high-temperature alloy welding material for aviation.

Specifically, the vacuum degree in the vacuum induction melting in the step (1) is less than or equal to 12 Pa;

specifically, in the step (1), the refining vacuum degree is less than or equal to 5Pa, the refining temperature is 1510-1520 ℃, and the refining time is 50-100 min.

Specifically, the pressure of argon filling in the step (1) is 3000-5000 Pa; the temperature during argon filling is 1500-1510 ℃.

Specifically, the adding amount of the electric slag used in the step (2) is 5-9% of the weight of the cast ingot, and the electric slag comprises the following components in percentage by mass:

specifically, the temperature of the heat treatment in the step (3) is 1120-1150 ℃ and the time is 50-100 min.

Specifically, the forging in the step (3) is subjected to multiple upsetting and drawing.

Specifically, the upsetting reduction of one upsetting and drawing is more than or equal to 30%, the drawing operation is carried out immediately after each upsetting, the reduction is controlled to be 30-50mm, and the deformation of each upsetting is controlled to be more than or equal to 50%.

The invention has the beneficial effects that:

for the alloy parent metal GH1015 with a large Fe content, in the process of cladding welding, Fe in the parent metal can continuously migrate to a welding seam, which easily causes large change of components of welding materials at the welding seam, increases welding brittleness and has adverse effect on welding performance.

Detailed Description

The present invention will now be described in further detail with reference to examples.

In the following embodiments of the invention, the nickel-based superalloy welding material for aviation is prepared according to the following steps:

(1) adding C, Cr, W, Si, Fe and Ni into a crucible according to the formula amount, putting the crucible into a vacuum induction furnace for vacuum induction melting, then adding Al and Ti into the crucible for refining, then adding the rest elements and filling argon, and obtaining cast ingots after casting;

(2) adding the cast ingot into a slag pool, and adding slag for electroslag remelting to obtain an electroslag ingot;

(3) and adding the electroslag ingot into a heating furnace to carry out heat treatment along with the furnace, and forging and air cooling to obtain the nickel-based high-temperature alloy welding material for aviation.

The vacuum degree in the vacuum induction melting in the step (1) is less than or equal to 12 Pa;

in the step (1), the refining vacuum degree is less than or equal to 5Pa, the refining temperature is 1510-1520 ℃, and the refining time is 50-100 min.

The pressure of argon filling in the step (1) is 3000-5000 Pa; the temperature during argon filling is 1500-1510 ℃.

The adding amount of the electric slag used in the step (2) is 5-9% of the weight of the cast ingot, and the electric slag comprises the following components in percentage by mass:

the temperature of the heat treatment in the step (3) is 1120-1150 ℃, and the time is 50-100 min.

And (4) forging for multiple upsetting and drawing.

The upsetting reduction of one upsetting and drawing is more than or equal to 30 percent, the drawing operation is carried out immediately after each upsetting, the reduction is controlled to be 30-50mm, and the deformation of each upsetting is controlled to be more than or equal to 50 percent.

Example 1

The nickel-based high-temperature alloy welding material for the aviation comprises the following components in percentage by mass:

example 2

The nickel-based high-temperature alloy welding material for the aviation comprises the following components in percentage by mass:

example 3

The nickel-based high-temperature alloy welding material for the aviation is characterized by comprising the following components in percentage by mass:

example 4

The nickel-based high-temperature alloy welding material for the aviation comprises the following components in percentage by mass:

example 5

The nickel-based high-temperature alloy welding material for the aviation comprises the following components in percentage by mass:

comparative example 1 is compared with example 1 except that the comparative example 1 contains 4% by mass of Fe.

Comparative example 2 is compared with example 1 except that the content of Si in comparative example 2 is 0.8% by mass.

Comparative example 3 is compared with example 1, except that comparative example 3 further contains Mo in an amount of 1.5% by mass.

And (3) performance testing:

keeping the temperature of the nickel alloy forgings obtained in the embodiments 1-5 and the comparative examples 1-3 at 1100 ℃ for 1h, and carrying out hot continuous rolling to obtain a wire rod with the diameter of 6.55 mm; and then carrying out solid solution on the wire rod for 1h in molten salt at 1100 ℃, carrying out acid pickling for 30min, carrying out 5-8 times of rough drawing on the wire rod, sequentially carrying out electrolytic cleaning by using a 60% sulfuric acid solution, drying, hydrogen-charging annealing, electrolytic cleaning by using a 60% sulfuric acid solution, washing, drying, hydrogen-charging annealing at 1100 ℃, cooling, and carrying out 5-8 times of fine drawing to obtain the 1-2mm welding wire.

The alloy welding wires obtained in examples 1-5 and comparative examples 1-3 and a commercially available GH3044 alloy welding wire are used as welding materials, cladding welding is carried out on a base metal alloy GH1015 in a gas shielded welding mode, wherein the shielding gas contains 5% of hydrogen, the welding speed is 5cm/min, the wire feeding speed is 1.5-1.8m/s, the welding current is 50-60A, and the room-temperature mechanical properties of a welding joint are tested by GB/T2651-2008 'welding joint tensile test method', and the test results are shown in Table 1.

TABLE 1

Test item

Splash condition

Weld seam

Arc stability

Tensile strength (MPa)

Elongation (%)

Location of fracture

Example 1

Good taste

Beautiful appearance

Good taste

651

40

Base material

Example 2

Good taste

Beautiful appearance

Good taste

664

43

Base material

Example 3

Good taste

Beautiful appearance

Good taste

680

46

Base material

Example 4

Good taste

Beautiful appearance

Good taste

658

41

Base material

Example 5

Good taste

Beautiful appearance

Good taste

670

42

Base material

Comparative example 1

Big (a)

With air holes

Difference (D)

605

28

At the welding seam

Comparative example 2

In

Has micro cracks

Difference (D)

622

33

Base material

Comparative example 3

In

In general

Difference (D)

614

37

At the welding seam

GH3044 alloy

In

Has micro cracks and pores

Difference (D)

556

25

At the welding seam

In light of the foregoing description of the preferred embodiment of the present invention, many modifications and variations will be apparent to those skilled in the art without departing from the spirit and scope of the invention. The technical scope of the present invention is not limited to the content of the specification, and must be determined according to the scope of the claims.