阅读说明：本技术 一种用于强化镍基高温合金零件混合成型方法 (Mixed forming method for reinforced nickel-based high-temperature alloy part ) 是由 于全成 兰亚洲 史见 于 2021-09-22 设计创作，主要内容包括：本发明公开了一种用于强化镍基高温合金零件混合成型方法,采用对待成形零件进行切片,将待成形零件的强化层与非强化层的切片分开,形成两个独立打印切片程序,形成两种不同层的打印程序,然后先对内部结构进行打印成形一个打印高度层,形成内部结构,然后对强化层进行打印成形一个打印高度层,交替打印直至整体零件成形,在零件需要加强的表层形成满足强度和耐磨性要求的零件表面结构,本发明方法简单,交替成形一个打印高度层,能够使加强层与内部零件形成良好的接触层,实现高温合金的表面增强,通过本发明的方法制备的表层增强制件,表面硬度提高20％,疲劳寿命提高15％。(The invention discloses a mixed forming method for a reinforced nickel-based high-temperature alloy part, which comprises the steps of slicing a part to be formed, separating a reinforced layer and a non-reinforced layer of the part to be formed into two independent printing and slicing procedures to form two printing procedures with different layers, printing and forming a printing height layer on an internal structure to form an internal structure, printing and forming the printing height layer on the reinforced layer, alternately printing until the whole part is formed, and forming a part surface structure meeting the requirements of strength and wear resistance on a surface layer of the part to be reinforced, wherein the method is simple, the printing height layer is alternately formed, a good contact layer can be formed between the reinforced layer and the internal part, the surface reinforcement of the high-temperature alloy is realized, the surface layer of the part prepared by the method is reinforced, the surface hardness is improved by 20 percent, the fatigue life is improved by 15 percent.)

1. The mixed forming method for the reinforced nickel-based high-temperature alloy part is characterized by comprising the following steps of:

s1, slicing the part to be formed, and separating the slices of the reinforced layer and the non-reinforced layer of the part to be formed to form two independent printing slicing programs;

s2, firstly, printing a non-reinforced layer of the internal structure to form a printing height layer, and then printing a reinforced layer to form a printing height layer; the alternating printing is repeated until the integral part is formed.

2. The hybrid forming method for the reinforced nickel-base superalloy part of claim 1, wherein the non-reinforced layer is formed from GH3536 alloy powder.

3. The hybrid forming method for the reinforced nickel-based high-temperature alloy part as claimed in claim 1, wherein the forming of the reinforced layer adopts mixed powder of GH3536 alloy powder gold and TiC nano powder, and the mass ratio of the GH3536 alloy powder gold to the TiC nano powder is 0.1-3%.

4. The hybrid forming method for the reinforced nickel-base superalloy part as claimed in claim 2 or 3, wherein the grain size of the GH3536 alloy powder is 15-53 μm.

5. The hybrid forming method for the reinforced nickel-based high-temperature alloy part according to claim 2 or 3, wherein the particle size of TiC nano powder is 10-60 nm.

6. The hybrid forming method for the reinforced nickel-based superalloy part as claimed in claim 1, wherein during printing of the non-reinforced layer, a scanning speed is 800-1000 mm/s, a power is 220-320W, and a laser lapping interval is 0.1-0.12 mm.

7. The hybrid forming method for the reinforced nickel-based superalloy part as claimed in claim 1, wherein in the printing process of the reinforced layer, the scanning speed is 800-1000 mm/s, the power is 230-350W, and the laser lapping interval is 0.09-0.12 mm.

8. The hybrid forming method for strengthening a nickel-base superalloy part of claim 1, wherein the thickness of the strengthening layer is no greater than 3 mm.

9. The hybrid molding method for the reinforced nickel-based superalloy part as claimed in claim 1, wherein during the alternate printing of the non-reinforced layer and the reinforced layer, the last printing powder needs to be cleaned up before powder spreading.

10. The hybrid molding method for strengthening nickel-base superalloy parts according to claim 1, wherein the non-strong layer and the portion in contact with the strengthening layer have a sintered overlap area of less than 0.2 mm.

Technical Field

The invention belongs to the technical field of high-temperature alloy part manufacturing, and relates to a mixed forming method for a reinforced nickel-based high-temperature alloy part.

Background

In view of the high temperature resistance of the material, the nickel-based high-temperature alloy is widely applied to the preparation of aeroengine parts, particularly combustion chambers and turbine parts, and 90% of the materials are made of the nickel-based high-temperature alloy. The nickel-based high-temperature alloy still has good oxidation resistance and corrosion resistance at high temperature.

In order to realize complex functions, the single structures of a plurality of parts of the aircraft engine are complex, which increases great difficulty for processing and manufacturing. The application of the 3D printing technology provides a new method for manufacturing the complex parts. For metal 3D printing raw materials, powder of materials used for parts is mainly selected, and processes of metal 3D printing mainly include SLM (selective laser melting forming), SLS (selective laser sintering) and Laser Cladding (LC), wherein the SLM can be used most widely for forming more complex parts.

At present, only one powder can be adopted for preparing parts by adopting selective laser melting forming, the property of the material determines the ultimate performance limit of the product, for complex parts, when the complex surface layer in the part needs higher strength and wear resistance, the core part needs lower strength and relatively high plasticity, the part needs higher fatigue performance, and meanwhile, the material of the reinforcing layer is required to be based on the material of the part body and to be well combined with the part substrate; at present, after the conventional SLM printing method is used, post-processing cannot be realized.

Disclosure of Invention

The invention aims to provide a mixed forming method for a reinforced nickel-based high-temperature alloy part, which overcomes the defects of the prior art.

In order to achieve the purpose, the invention adopts the following technical scheme:

a mixed forming method for a reinforced nickel-based high-temperature alloy part comprises the following steps:

s1, slicing the part to be formed, and separating the slices of the reinforced layer and the non-reinforced layer of the part to be formed to form two independent printing slicing programs;

s2, firstly, printing a non-reinforced layer of the internal structure to form a printing height layer, and then printing a reinforced layer to form a printing height layer; the alternating printing is repeated until the integral part is formed.

Furthermore, GH3536 alloy powder is adopted for forming the non-reinforced layer.

Furthermore, the forming of the strengthening layer adopts mixed powder of GH3536 alloy powder gold and TiC nano powder, and the mass ratio of the GH3536 alloy powder gold to the TiC nano powder is 0.1-3%.

Furthermore, the granularity of the GH3536 alloy powder is 15-53 mu m.

Further, the granularity of the TiC nano powder is 10-60 nm.

Furthermore, in the printing process of the non-reinforced layer, the scanning speed is 800-1000 mm/s, the power is 220-320W, and the laser lapping interval is 0.1-0.12 mm.

Furthermore, in the process of printing the strengthening layer, the scanning speed is 800-1000 mm/s, the power is 230-350W, and the laser lapping interval is 0.09-0.12 mm.

Further, the thickness of the strengthening layer is not more than 3 mm.

Furthermore, in the alternate printing process of the non-reinforced layer and the reinforced layer, the last printing powder needs to be cleaned before powder spreading.

Furthermore, the non-strong layer and the part which is in contact with the strengthening layer have a sintering lap joint area which is less than 0.2 mm.

Compared with the prior art, the invention has the following beneficial technical effects:

the invention relates to a mixed forming method for a reinforced nickel-based high-temperature alloy part, which is characterized in that a part to be formed is sliced, a reinforced layer and a non-reinforced layer of the part to be formed are separated to form two independent printing slicing procedures to form two printing procedures of different layers, then an internal structure is printed and formed by a printing height layer, the reinforced layer is printed and formed by the printing height layer, the printing is carried out alternately until the whole part is formed, and a part surface structure meeting the requirements of strength and wear resistance is formed on a surface layer of the part needing to be reinforced.

Furthermore, GH3536 alloy powder is adopted for forming the non-strengthening layer, mixed powder of GH3536 alloy powder gold and TiC nano powder is adopted for forming the strengthening layer, surface strengthening of the high-temperature alloy is achieved, forming process parameters are close to and different, effective combination can be carried out within a height time of forming, and the strengthening effect of the surface layer of the part is greatly improved.

Furthermore, in the printing process of the non-reinforced layer and the printing process of the reinforced layer, the power is close to but different, so that alternate printing is facilitated, and errors caused by high-power switching of equipment are avoided.

Drawings

FIG. 1 is a schematic structural diagram of a part to be molded according to an embodiment of the present invention.

Wherein, 1, an inner surface layer; 2. an outer skin layer; 3. the part core.

Detailed Description

The invention is described in further detail below with reference to the accompanying drawings:

a mixed forming method for a reinforced nickel-based high-temperature alloy part comprises the following steps:

s1, slicing the part to be formed, and separating the slices of the reinforced layer and the non-reinforced layer of the part to be formed to form two independent printing slicing programs;

s2, firstly, printing the internal structure to form a printing height layer, and then printing the reinforcing layer to form a printing height layer; the alternating printing is repeated until the integral part is formed.

Forming the non-reinforced layer by adopting GH3536 alloy powder;

the strengthening layer is formed by adopting mixed powder of GH3536 alloy powder gold and TiC nano powder, and the mass ratio of the GH3536 alloy powder gold to the TiC nano powder is 0.1-3%.

And uniformly mixing GH3536 alloy powder gold and TiC nano powder by adopting a planetary ball mill.

The granularity of the GH3536 alloy powder is 15-53 mu m, and the granularity of the TiC nano powder is 10-60 nm.

In the printing process of the non-reinforced layer, the scanning speed is 800-1000 mm/s, the power is 220-320W, and the laser lapping distance is 0.1-0.12 mm;

in the strengthening layer printing process, the scanning speed is 800-1000 mm/s, the power is 230-350W, and the laser lapping interval is 0.09-0.12 mm;

in the embodiment, as shown in fig. 1, in the part, both the outer surface layer 2 and the inner surface layer 1 need to be strengthened, and the part core 3 is formed by using nickel-based superalloy powder, which specifically comprises the following steps:

s1, weighing sufficient GH3536/TiC combined powder and nickel-based superalloy powder, and respectively filling the powder into two independent powder paving devices, wherein SLM laser selective melting forming equipment provided with a mixed powder device is adopted in the method; the SLM selective laser melting forming equipment is connected with a powder cleaning device;

s2, carrying out process design on the part model by adopting three-dimensional software, and extracting a surface layer model to be reinforced, wherein the thickness of the surface layer to be reinforced is not more than 3 mm;

s3, slicing and subdividing the part model, and independently subdividing the surface layer to be reinforced and other areas to form two sets of printable programs;

s4, guiding the slicing program into SLM laser selective melting forming equipment;

s5, starting equipment to print and form the metal parts, and firstly, spreading powder to a non-reinforced area to form; a layer of GH3536 powder is laid by the powder scraping system, a laser power supply is started, and a non-reinforced area of the part is selectively sintered; the scanning speed is 800-1000 mm/s, the power is 220-320W, and the laser lapping interval is 0.1-0.12 mm;

s6, starting a cleaning device of the powder scraping system, and performing reciprocating motion for 2-3 times to clean powder in the surface area of the printed part;

s7, laying a layer of GH3536/TiC combined powder by a powder scraping system, and sintering a surface layer region needing to be strengthened by adopting laser; the scanning speed is 800-1000 mm/s, the power is 230-350W, and the laser lapping interval is 0.09-0.12 mm;

s8, starting a cleaning device of the powder scraping system, and performing reciprocating motion for 2-3 times to clean powder in the surface area of the printed part;

and S9, paving a layer of GH3536 powder by a powder scraping system, and selectively sintering the non-strengthened area of the part by laser.

Step 10 repeats steps 6 to 9 until the entire part is printed.

And the part model is subjected to process optimization, a surface layer model needing to be reinforced is extracted, and the thickness of the reinforced layer is less than 3 mm. And combining the reinforced layer model and other non-reinforced layer models to form the original model state of the part.

When the laser is sintered selectively, the contact part of the non-strong layer and the strengthening layer has a sintering lap joint area smaller than 0.2 mm.

The fatigue life of the surface layer reinforced part prepared by the method is prolonged by more than 15%.

The invention provides a preparation method of a nickel-based high-temperature alloy based on micro-nano reinforcement, which is characterized in that a metal part with a soft base material at the core part and a micro-nano reinforcement material inside or partially inside a complex cavity is prepared through improved SLM equipment, so that the surface reinforcement of the high-temperature alloy is realized. The surface-reinforced part prepared by the method has the advantages that the surface hardness is improved by 20 percent, and the fatigue life is prolonged by 15 percent.

The above embodiments of the present invention are not limited to the above embodiments, and any other changes, modifications, substitutions, combinations, and simplifications which do not depart from the spirit and principle of the present invention should be construed as equivalents thereof, and they are included in the scope of the present invention.