CN109513925B - Thin-wall large-temperature-gradient structural component and laser direct deposition preparation method thereof - Google Patents
Thin-wall large-temperature-gradient structural component and laser direct deposition preparation method thereof Download PDFInfo
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Abstract
The invention discloses a thin-wall large-temperature-gradient structural member. A thin-wall large temperature gradient structural member sequentially comprises the following components in the temperature gradient direction of the structural member: the temperature gradient transition layer is arranged on the middle temperature layer; the temperature gradient transition layer is composed of a mixture of medium-temperature layers and high-temperature layers, the high-temperature base layer is made of the same material as the high-temperature layers, and the temperature gradient transition layer and the high-temperature base layer are used for reducing the tissue stress and the thermal stress of the large-temperature gradient structural member. The invention also discloses a laser direct deposition preparation method of the thin-wall large-temperature-gradient structural component. According to the invention, the temperature gradient transition layer and the high-temperature base layer are added in the dissimilar material gradient structure, the uniform and stable transition of the transition layer material is realized by the temperature gradient transition layer, the deposition speed of the temperature gradient transition layer and the high-temperature base layer is relatively slow, the structural stress and the thermal stress of the gradient structure are reduced, and the large temperature gradient structure integrated forming of the dissimilar material is realized.
Description
Technical Field
The invention belongs to the technical field of special metal forming processing, and relates to a thin-wall large-temperature-gradient structural component and a laser direct deposition preparation method thereof.
Background
In the process of high-speed flight of the aircraft, the temperature gradient of each part is very large, for example, the temperature of the local area of the air inlet channel is as high as 700-800 ℃, the aircraft needs to be made of high-temperature-resistant, high-strength and high-rigidity materials, and the temperature of other parts is low, so that the common titanium alloy can meet the use requirement. The titanium alloy large temperature gradient structural member with different properties is integrally manufactured to be integrally formed, the use temperature requirements of different parts of the part are met at lower cost, the problems of connection and sealing of parts are solved, and more importantly, the integral strength and rigidity of the part are improved.
Compared with the preparation of a single material, the preparation of the large temperature gradient structural part by utilizing the direct laser deposition has special difficulty, the preparation of the large temperature gradient structural part adopts different material powder, and due to different physical and chemical properties of the materials, the melting and solidification processes are different, so that harmful impurities or microcracks are easily generated; in addition, in the case of a thin-walled structure, the structure is more likely to be deformed due to stress concentration caused by abrupt changes in material composition and performance, and the structure accuracy is affected. In response to this situation, there is a need for improvements to existing methods to overcome the drawbacks of existing laser direct deposition.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a thin-wall large-temperature-gradient structural member with stable transition performance, higher overall strength and difficult crack generation and a laser direct deposition preparation method thereof. The method carries out reasonable transition layer design and process design before deposition, so that the structure performance of a transition area and the deposited part form a stable and continuous state, the performance is kept consistent, the integral strength of the structural member is increased, and cracks are avoided; in addition, when the gradient structure is prepared, deposition process parameters are changed according to the change of components, so that the structure performance of the deposited transition layer is good, and higher integral strength is kept.
The technical solution of the invention is as follows:
a thin-wall large temperature gradient structural member sequentially comprises the following components in the temperature gradient direction of the structural member: the temperature gradient transition layer is arranged on the middle temperature layer; the temperature gradient transition layer is composed of a mixture of medium-temperature layers and high-temperature layers, the high-temperature base layer is made of the same material as the high-temperature layers, and the temperature gradient transition layer and the high-temperature base layer are used for reducing the tissue stress and the thermal stress of the large-temperature gradient structural member.
In the invention, the high-temperature base layer is used as a structural layer between the temperature gradient transition layer and the high-temperature layer, so that the performances of the temperature gradient transition layer and the high-temperature layer are continuous and stable, and the integral strength of the structural member is ensured.
In the thin-wall large temperature gradient structural member, as a preferred embodiment, the total thickness of the temperature gradient transition layer (i.e., the height direction of the entire structural member) is 0.8 to 2 mm.
In the thin-wall large temperature gradient structural member, as a preferred embodiment, the total thickness of the high-temperature foundation layer (i.e., the height direction of the entire structural member) is 1 to 2 mm.
In the thin-wall large-temperature-gradient structural member, as a preferred embodiment, the temperature gradient transition layer includes at least two sublayers, a mass percentage of a medium-temperature layer material in the sublayer close to the medium-temperature layer is greater than 50%, and a mass percentage of a medium-temperature layer material in the sublayer close to the high-temperature base layer is greater than 50%; preferably, the temperature gradient transition layer comprises three sublayers, wherein the mass percentage of the medium-temperature layer material in the sublayer close to the medium-temperature layer is 60-70%, the mass percentage of the medium-temperature layer material in the middle sublayer is the same as the mass percentage of the high-temperature layer material, and the mass percentage of the high-temperature layer material in the sublayer close to the high-temperature base layer is more than 60-70%.
In the thin-walled large temperature gradient structural member, as a preferred embodiment, the material of the intermediate temperature layer is a titanium alloy having a use temperature of 400 ℃ or lower, and the material of the high temperature layer is a high temperature titanium alloy or a Ti — Al intermetallic compound having a use temperature of 500 ℃ or higher.
A laser direct deposition preparation method of a thin-wall large temperature gradient structural member is characterized in that the large temperature gradient structural member is an integrally formed structural member and at least sequentially comprises the following steps along the temperature gradient direction of the structural member: the preparation method comprises the following steps of:
firstly, initializing laser forming equipment;
secondly, constructing a three-dimensional model of the structural part, and then subdividing the three-dimensional model to generate a laser scanning path;
selecting materials of all layers of the structural member, wherein the components of the temperature gradient transition layer comprise the materials of a medium-temperature layer and a high-temperature layer, and the material of the high-temperature base layer is the same as that of the high-temperature layer;
fourthly, performing laser direct deposition treatment according to the material of the medium temperature layer to form the medium temperature layer;
fifthly, carrying out laser direct deposition treatment on the surface of the intermediate temperature layer according to the component proportion of the temperature gradient transition layer to form the temperature gradient transition layer;
sixthly, performing laser direct deposition treatment on the surface of the temperature gradient transition layer according to the material of the high-temperature basic layer to form a high-temperature basic layer;
and seventhly, performing laser direct deposition treatment on the surface of the high-temperature base layer according to the material of the high-temperature layer to form the high-temperature layer.
In the above laser direct deposition manufacturing method, as a preferred embodiment, the method further includes a heat treatment step of heat-treating the structural member blank obtained in the seventh step; preferably, the temperature of the heat treatment is 500-650 ℃, the holding time is 1.5-2.5h, and the specific heat treatment temperature and time are changed along with the change of materials.
In the above laser direct deposition method, as a preferred embodiment, the material of the intermediate temperature layer is a titanium alloy with a use temperature of 400 ℃ or lower, and the material of the high temperature layer is a high temperature titanium alloy or a Ti — Al intermetallic compound with a use temperature of 500 ℃ or higher.
In the above laser direct deposition preparation method, as a preferred embodiment, the temperature gradient transition layer includes at least two sublayers, a mass percentage of a medium-temperature layer material in the sublayer close to the medium-temperature layer is greater than 50%, and a mass percentage of a medium-temperature layer material in the sublayer close to the high-temperature base layer is greater than 50%. More preferably, the temperature gradient transition layer comprises three sublayers, wherein the mass percentage of the medium-temperature layer material in the sublayer close to the medium-temperature layer is 60-70%, the mass percentage of the medium-temperature layer material in the middle sublayer is the same as the mass percentage of the high-temperature layer material, and the mass percentage of the high-temperature layer material in the sublayer close to the high-temperature base layer is greater than 60-70%.
In the laser direct deposition preparation method, as a preferred embodiment, the total thickness (i.e. the height direction or the temperature gradient direction) of the temperature gradient transition layer is 0.8-2 mm, and the preparation efficiency will be affected by the excessive thicknesses of the transition layer and the high-temperature base layer, and the overall strength of the structural member will not be obviously increased; too thin does not serve to enhance the overall strength of the structural member.
In the above laser direct deposition method, as a preferred embodiment, the total thickness (i.e., the height direction or the temperature gradient direction) of the high temperature base layer is 1 to 2 mm.
In the above laser direct deposition manufacturing method, as a preferred embodiment, the initializing laser forming apparatus includes: checking and preparing each system in the laser direct deposition equipment, wherein the preparing work in the step is used as a known technology in the field, and an atmosphere protection system is started to ensure that the oxygen content is lower than 50 ppm;
in the above laser direct deposition preparation method, as a preferred embodiment, in the second step, a three-dimensional model of the structural member is established by using three-dimensional modeling software Siemens NX, the three-dimensional model is subdivided by using self-contained subdivision software of laser direct deposition equipment (i.e., laser forming equipment), the thicknesses of the subdivision monolayers of the intermediate temperature layer and the high temperature layer are 0.4-0.6 mm, the thicknesses of the subdivision monolayers of the gradient transition layer and the high temperature base layer are 0.1-0.2 mm, and a CNC program (laser scanning path) generated by the subdivision software is input into the laser direct deposition equipment;
in the above laser direct deposition preparation method, as a preferred embodiment, in the third step, the component distribution ratio, the single layer thickness and the like of each layer of raw materials of the structural member are input into a powder feeder numerical control system of the laser direct deposition equipment as numerical control variable values to control the powder feeding ratio and the powder feeding rate at different positions during laser direct deposition; the powder feeding rate is related to parameters such as scanning speed, single-layer deposition thickness and the like, and the powder feeding rate of the medium-temperature layer and the high-temperature layer is preferably 1.5-3 g/min generally; the powder feeding rate of the temperature gradient transition layer and the high-temperature base layer is preferably 0.8-1 g/min.
In the above laser direct deposition method, as a preferred embodiment, in the fourth step, the process parameters of the laser direct deposition process for forming the intermediate temperature layer include: the scanning speed is 4-6 mm/s, the laser power is 1200-1800W, and the single-layer deposition thickness is 0.4-0.6 mm; if the process parameters are too high or too low, the strength and the qualification rate of the structural part are influenced, and the total deposited layer number is determined by the height of the medium-temperature layer of the prepared structural part.
In the above laser direct deposition preparation method, as a preferred embodiment, in the fifth step, the process parameters of the laser direct deposition process for forming the temperature gradient transition layer include: the scanning speed is 1.5-2.5 mm/s, the laser power is 800-1200W, and the single-layer deposition thickness is 0.1-0.2 mm (the total thickness of the transition layer is 0.8-2 mm); more preferably, the laser power is 800-1000W.
Dividing the transition layer into a plurality of laser scanning layers in the thickness direction of the layer (namely the height direction of the structural member), wherein each laser scanning layer ensures that the powder feeding amount of two materials is consistent, and uniform and stable transition of the material of the transition layer is realized;
in the above laser direct deposition preparation method, as a preferred embodiment, in the sixth step, the process parameters of the laser direct deposition process for forming the high temperature base layer include: the scanning speed is 1.5-2.5 mm/s, the laser power is 800-1200W, and the single-layer deposition thickness is 0.1-0.2 mm; more preferably, the laser power is 800-1000W.
In the preparation steps of the transition layer and the high-temperature base layer, the scanning speed and the laser power are less than those of the medium-temperature layer in the fourth step, so that the structural stress and the thermal stress of the structure are reduced, and after 5-10 layers of the high-temperature base layer are continuously deposited on the temperature gradient transition layer (the total thickness of the high-temperature base layer is 1-2 mm), the high-temperature base layer is formed; the high temperature base layer is too thick, which greatly affects the manufacturing efficiency of the structural member.
In the above laser direct deposition preparation method, as a preferred embodiment, in the seventh step, the process parameters of the laser direct deposition process for forming the high temperature layer include: the scanning speed is 4-6 mm/s (the scanning speed is the scanning linear velocity), the laser power is 1200-1800W, and the single-layer deposition thickness is 0.4-0.6 mm; through the transition of the transition layer and the basic layer, the high-temperature layer is changed into the preparation of a single material, the forming is stable, and the related parameters are increased at the moment, so that the forming efficiency can be improved. The total number of layers deposited is determined by the height of the high temperature layers of the fabricated structure.
On the basis of the high-temperature basic layer, the scanning speed and the laser power are synchronously increased, the forming efficiency is improved, and uniform and stable forming is carried out until the formation is finished.
And (3) after the blank is moved out of the forming chamber, removing the powder adhered on the surface, and then putting the blank into a heat treatment furnace for stress relief annealing treatment (the specific heat treatment process is determined according to the material used in the gradient structure).
The wall thickness of the thin-wall large temperature gradient structural component is not particularly limited, but the method is particularly suitable for preparing the structural component with the wall thickness of less than 2 mm.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, the temperature gradient transition layer and the high-temperature base layer are added in the dissimilar material gradient structure, the uniform and stable transition of the material of the transition layer is realized by the temperature gradient transition layer, the deposition speed of the temperature gradient transition layer and the high-temperature base layer is relatively slow, the structural stress and the thermal stress of the gradient structure are reduced, the large temperature gradient structure integrated forming of the dissimilar material is realized, and the strength of the integral structural member is improved;
(2) the invention adopts gradual transition of the material with a large temperature gradient structure, reduces the stress concentration of the material caused by abrupt change of components and performance, and effectively inhibits the deformation of a thin-wall structure;
(3) according to the invention, the stress-relief annealing treatment after the integrated forming is carried out, and meanwhile, the tissue regulation and control of the dissimilar material are carried out, so that the performance is kept consistent, the uniform and stable structure of the large-temperature gradient structure is realized, and the cracking risk is eliminated.
Drawings
FIG. 1 is a schematic diagram of laser direct deposition of a warm layer, a gradient transition layer and a high temperature base layer according to the present invention;
FIG. 2 is a schematic diagram of laser direct deposition of a high temperature layer with a conical cylinder structure according to the present invention;
FIG. 3 is a schematic diagram of laser direct deposition of a high temperature layer of a cylindrical structure according to the present invention;
FIG. 4 is a flow chart of the present invention.
Description of the drawings: 1. 2 is a powder feeder; 3 is a rotary table; 4 is a cylindrical surface; 5 is a conical surface.
Detailed Description
The invention is described in detail below with reference to the figures and specific examples.
Example 1
The TA15/Ti2AlNb thin-wall large temperature gradient conical barrel structural member is prepared by using laser direct deposition, as shown in fig. 2, a hollow rotary body (i.e. a conical barrel structural member) formed by connecting a cylindrical surface 4 and a conical surface 5 is prepared by using laser direct deposition equipment, the wall thickness is 2mm, the cylindrical surface material (barrel part material) is TA15 alloy, the conical surface material (cone part material) is Ti2AlNb alloy, the diameter phi 160mm and the height 100mm of the cylindrical surface end (barrel part) are respectively, the diameter phi 200mm and the total height 200mm of the conical surface large end (cone part large end) are respectively, and 3 is a rotary table for manufacturing the rotary body structural member.
The first step is to initialize the laser forming equipment.
Carrying out system inspection and preparation work of laser direct deposition equipment LSF-III (laser CP4000), starting an atmosphere protection system to enable the oxygen content to be lower than 50ppm, and respectively filling TA15 and Ti2AlNb alloy powder into powder feeders 1 and 2;
and secondly, generating a laser scanning path.
Establishing a gradient structure three-dimensional model by using three-dimensional modeling software Siemens NX, subdividing the three-dimensional model by using self-contained subdivision software of laser direct deposition equipment, and inputting a CNC program (laser scanning path) generated by the subdivision software into equipment;
and thirdly, designing components of a gradient structure.
Designing the component proportion of different positions of the large temperature gradient structural member, wherein the material of a middle temperature layer, namely a cylindrical surface part is TA15, the material of a high temperature layer, namely a conical surface part is Ti2AlNb, the gradient transition layer is designed into three layers, the first layer (close to the middle temperature layer) is 60 wt% TA15/40 wt% Ti2AlNb, the second layer is 50 wt% TA15/50 wt% Ti2AlNb, the third layer (close to the high temperature basic layer) is 40 wt% TA15/60 wt% Ti2AlNb, inputting the numerical control variable value into a powder feeder numerical control system of laser direct deposition equipment, and controlling the powder feeding ratio of different positions during laser direct deposition;
and fourthly, directly depositing the medium temperature layer by laser.
The deposition of the TA15 alloy portion was first performed on the substrate, as shown in fig. 1, with the process parameters set to: scanning angular speed of 2.87 degrees/s (linear speed of 4mm/s), laser power of 1500W, single-layer deposition thickness of 0.4mm, codepositing 250 layers (thickness of 100mm), and finishing the stable and rapid deposition of TA15 alloy part;
and fifthly, directly depositing the temperature gradient transition layer by laser.
The three transition layers are divided into a plurality of laser scanning layers in the layer thickness direction, each laser scanning layer ensures that the powder feeding amount of the two materials is consistent, and the uniform and stable transition of the transition layer material TA15/Ti2AlNb is realized. The technological parameters are as follows: scanning speed is 2mm/s, laser power is 1000W, single-layer deposition thickness is 0.1mm, 10 layers (thickness is 1mm, wherein the total thickness of a first transition layer is 0.3mm, the total thickness of a second transition layer is 0.3mm, and the total thickness of a third transition layer is 0.4mm) are deposited on a medium-temperature layer to form a temperature gradient layer;
and sixthly, directly depositing the high-temperature basic layer by laser to form a basic deposition layer.
After the deposition of the temperature gradient layer is finished, a Ti2AlNb base layer is deposited, and the process parameters are set as follows: scanning speed is 2mm/s, laser power is 1000W, single-layer deposition thickness is 0.2mm, 10 layers (thickness is 2mm) are continuously deposited on the transition layer, and a basic deposition layer is formed;
and seventhly, stabilizing laser direct deposition by a high-temperature layer.
The stable deposition of the high temperature layer 5 is carried out by rotating (or tilting) the turntable 3 by 15 ° (since this embodiment is an object of a large temperature gradient inlet channel part, 5 is an expansion section, which is used at a higher temperature, and thus 5 in fig. 2 is set as a cone), as shown in fig. 2. The technological parameters are as follows: the scanning speed is 4mm/s, the laser power is 1600W, the single-layer deposition thickness is 0.5mm, the scanning angular speed is variable angular speed in the deposition process, in order to ensure the same scanning line speed, the angular speed is correspondingly reduced, and a 207 layer (the thickness is 103.5mm) is codeposited to finish the forming process (when the deposition parameters of a high-temperature layer are all higher than those of a medium-temperature layer, the effect is better);
and eighthly, carrying out heat treatment after the gradient structure is directly deposited by laser.
And removing the powder adhered on the surface of the blank after the blank is moved out of the forming chamber, then putting the blank into a heat treatment furnace, and performing stress relief annealing treatment of 550 ℃ for 2h and air cooling on the blank.
The invention has not been described in detail and is in part known to those of skill in the art.
The structural member obtained in the embodiment is not deformed and has good precision, the overall strength of the structural member is 1091Mpa according to GB/T228.1-2010 metal room temperature tensile test method, the transition layer and the high-temperature base layer are free of cracks, and the product percent of pass reaches more than 95%.
Example 2
The TA15/Ti2AlNb thin-wall large-temperature-gradient cylindrical structural part is prepared by utilizing laser direct deposition, the diameter phi is 150mm, the wall thickness is 2mm, the lower end material is TA15, the height is 100mm, the upper end material is Ti2AlNb, and the height is 50 mm.
The first step is to initialize the laser forming equipment.
Carrying out system inspection and preparation work of laser direct deposition equipment LSF-III (laser CP4000), starting an atmosphere protection system to enable the oxygen content to be lower than 50ppm, and respectively filling TA15 and Ti2AlNb alloy powder into powder feeders 1 and 2;
and secondly, generating a laser scanning path.
Establishing a gradient structure three-dimensional model by using three-dimensional modeling software Siemens NX, subdividing the three-dimensional model by using self-contained subdivision software of laser direct deposition equipment, and inputting a CNC program (laser scanning path) generated by the subdivision software into equipment;
and thirdly, designing components of a gradient structure.
Designing the component distribution ratios of different positions of a large temperature gradient structure, wherein the material of a medium temperature layer is TA15, the material of a high temperature layer is Ti2AlNb, designing a transition layer into two layers, the first layer (close to the medium temperature layer) is 60 wt% TA15/40 wt% Ti2AlNb, the second layer (close to a high temperature basic layer) is 40 wt% TA15/60 wt% Ti2AlNb, inputting the numerical control variable value into a powder feeder numerical control system, and controlling the powder feeding ratios of different positions when laser is directly deposited;
and fourthly, directly depositing the medium temperature layer by laser.
The deposition of the TA15 alloy portion was first performed on the substrate, as shown in fig. 3, with the process parameters set to: scanning speed is 5mm/s, laser power is 1600W, single-layer deposition thickness is 0.5mm, 200 layers (thickness is 100mm) are co-deposited, and stable and rapid deposition of a TA15 alloy part is completed;
and fifthly, directly depositing the temperature gradient layer by laser.
The two transition layers are divided into a plurality of laser scanning layers in the thickness direction, each laser scanning layer ensures that the powder feeding amount of the two materials is consistent, and the uniform and stable transition of the transition layer material TA15/Ti2AlNb is realized. The technological parameters are as follows: scanning speed is 2mm/s, laser power is 1200W, single-layer deposition thickness is 0.1mm, 8 layers (thickness is 0.8mm, wherein the total thickness of a first transition layer is 0.2mm, the total thickness of a second transition layer is 0.3mm, and the total thickness of a third transition layer is 0.3mm) are deposited on the medium-temperature layer, and a temperature gradient layer is formed;
and sixthly, directly depositing the high-temperature basic layer by laser to form a basic deposition layer.
After the deposition of the temperature gradient layer is finished, a Ti2AlNb base layer is deposited, and the process parameters are set as follows: scanning speed is 2mm/s, laser power is 1200W, single-layer deposition thickness is 0.15mm, 10 layers (thickness is 1.5mm) are continuously deposited on the transition layer, and a basic deposition layer is formed;
and seventhly, stabilizing laser direct deposition by a high-temperature layer.
A stable deposition of the high temperature layer 6 is performed as shown in fig. 3. The technological parameters are as follows: the scanning speed is 6mm/s, the laser power is 1800W, the single-layer deposition thickness is 0.5mm, 100 layers (the thickness is 50mm) are co-deposited, and the forming process is finished;
and eighthly, carrying out heat treatment after the gradient structure is directly deposited by laser.
And removing the powder adhered on the surface of the blank after the blank is moved out of the forming chamber, then putting the blank into a heat treatment furnace, and performing stress relief annealing treatment of 550 ℃ for 2h and air cooling on the blank.
The invention has not been described in detail and is in part known to those of skill in the art.
The structural part obtained by the embodiment is not deformed and has good precision, the integral strength is 1051Mpa, the transition layer and the high-temperature base layer have no cracks, and the product percent of pass reaches more than 95%.
Example 3
The procedure of this example was the same as in example 1 except that the total thickness of the transition layers was 0.6mm (the thickness of each of the three transition layers was 0.2mm) and the total thickness of the high temperature foundation layer was 0.5 mm.
In the preparation process of the structural member obtained by the embodiment, the gradient transition layer and the high-temperature base layer are easy to crack or cause structural member deformation, and the product yield is influenced.
Example 4
The procedure of this example was the same as in example 1 except that the total thickness of the transition layers was 3mm (the thickness of each of the three transition layers was 1mm) and the total thickness of the high-temperature foundation layer was 3 mm.
The preparation time of the gradient transition layer and the high-temperature base layer of the structural part obtained by the embodiment is longer, and the forming efficiency of the structural part is influenced.
Example 5
The other operation steps and methods were the same as in example 1 except that the process parameters of the fifth step and the sixth step were different from those of example 1. The fifth step and the sixth step of this embodiment are as follows:
the fifth step: the three transition layers are divided into a plurality of laser scanning layers in the layer thickness direction, each laser scanning layer ensures that the powder feeding amount of the two materials is consistent, and the uniform and stable transition of the transition layer material TA15/Ti2AlNb is realized. The technological parameters are as follows: scanning speed is 3mm/s, laser power is 1300W, single-layer deposition thickness is 0.3mm, 3 layers (thickness is 0.9mm, wherein the total thickness of a first transition layer is 0.3mm, the total thickness of a second transition layer is 0.3mm, and the total thickness of a third transition layer is 0.3mm) are deposited on the medium temperature layer, and a temperature gradient layer is formed;
sixthly, depositing a Ti2AlNb base layer after the deposition of the temperature gradient layer is finished, wherein the process parameters are as follows: the scanning speed is 3mm/s, the laser power is 1300W, the single-layer deposition thickness is 0.4mm, 5 layers (the thickness is 2mm) are continuously deposited on the transition layer, and a basic deposition layer is formed.
The overall strength of the structural part obtained in the embodiment is 1002Mpa, and the product percent of pass reaches 70%.
Example 6
The other operation steps and methods were the same as in example 1 except that the process parameters in the fourth to seventh steps were different from those in example 1. The fourth to seventh steps of the present embodiment are as follows:
and fourthly, directly depositing the medium temperature layer by laser.
The deposition of the TA15 alloy portion was first performed on the substrate, as shown in fig. 1, with the process parameters set to: the scanning speed is 6mm/s, the laser power is 1800W, the single-layer deposition thickness is 0.6mm, 167 layers (the thickness is 100mm) are co-deposited, and the stable and rapid deposition of the TA15 alloy part is completed;
and fifthly, directly depositing the temperature gradient transition layer by laser.
The three transition layers are divided into a plurality of laser scanning layers in the layer thickness direction, each laser scanning layer ensures that the powder feeding amount of the two materials is consistent, and the uniform and stable transition of the transition layer material TA15/Ti2AlNb is realized. The technological parameters are as follows: scanning speed is 2.5mm/s, laser power is 1200W, single-layer deposition thickness is 0.15mm, 7 layers (thickness is 1mm, wherein the total thickness of a first transition layer is 0.3mm, the total thickness of a second transition layer is 0.3mm, and the total thickness of a third transition layer is 0.4mm) are deposited on the medium-temperature layer, and a temperature gradient layer is formed;
and sixthly, directly depositing the high-temperature basic layer by laser to form a basic deposition layer.
After the deposition of the temperature gradient layer is finished, a Ti2AlNb base layer is deposited, and the process parameters are set as follows: the scanning speed is 2.5mm/s, the laser power is 1200W, the single-layer deposition thickness is 0.15mm, 14 layers (the thickness is 2mm) are continuously deposited on the transition layer, and a basic deposition layer is formed;
and seventhly, stabilizing laser direct deposition by a high-temperature layer.
The turntable 3 is rotated (or tilted) by 15 deg. for a stable deposition of the high temperature layer 5, as shown in fig. 2. The technological parameters are as follows: the scanning speed is 6mm/s, the laser power is 1800W, the single-layer deposition thickness is 0.5mm, the scanning angular speed is variable angular speed in the deposition process, in order to ensure the same scanning line speed, the angular speed is correspondingly reduced, and the forming process is finished by co-depositing 207 layers (the thickness is 103.5 mm).
The overall strength of the structural part obtained in the embodiment is 1025Mpa, and the product percent of pass reaches 90%.
Example 7
The procedure of this example was the same as in example 1 except that the gradient transition layer had only one layer, and the composition of the transition layer was 50 wt% of the material of the middle temperature layer and 50 wt% of the material of the high temperature layer.
The overall strength of the structural part obtained in the embodiment is 1020Mpa, and the product percent of pass reaches 80%.
Comparative example 1
This comparative example is the same as example 1 except that the sixth step of example 1 is omitted and the high temperature base layer is laser directly deposited.
In the preparation process of the structural member obtained by the comparative example, the gradient transition layer and the high-temperature layer are cracked, and the preparation of the high-temperature layer cannot be continuously completed.
Claims (13)
1. The thin-wall large temperature gradient structural member is characterized by sequentially comprising the following components in the temperature gradient direction of the structural member:
the temperature gradient transition layer is arranged on the middle temperature layer; the middle temperature layer is made of titanium alloy with the use temperature of below 400 ℃, and the high temperature layer is made of high-temperature titanium alloy or Ti-Al intermetallic compound with the use temperature of above 500 ℃; the total thickness of the temperature gradient transition layer is 0.8-2 mm, and the total thickness of the high-temperature basic layer is 1-2 mm;
the temperature gradient transition layer comprises a mixture of medium-temperature layer materials and high-temperature layer materials, the high-temperature base layer is made of the same material as the high-temperature layer materials, and the temperature gradient transition layer and the high-temperature base layer are used for reducing the structural stress and the thermal stress of the structural part; the thin-wall large temperature gradient structural part is prepared by adopting laser direct deposition, in the preparation steps of the temperature gradient transition layer and the high-temperature basic layer, the scanning speed and the laser power are less than those in the preparation of the medium-temperature layer, and in the preparation step of the high-temperature layer, the scanning speed and the laser power are greater than those in the preparation of the high-temperature basic layer.
2. The thin-walled large temperature gradient structural member of claim 1, wherein said temperature gradient transition layer comprises at least two sublayers, wherein the mass percentage of the medium temperature layer material in the sublayers close to said medium temperature layer is more than 50%, and the mass percentage of the high temperature layer material in the sublayers close to said high temperature base layer is more than 50%.
3. The thin-wall large-temperature-gradient structural member as claimed in claim 2, wherein the temperature gradient transition layer comprises three sublayers, the mass percentage of the medium-temperature layer material in the sublayers close to the medium-temperature layer is 60-70%, the mass percentage of the medium-temperature layer material in the middle sublayers is the same as that of the high-temperature layer material, and the mass percentage of the high-temperature layer material in the sublayers close to the high-temperature base layer is 60-70%.
4. The laser direct deposition preparation method of the thin-wall large temperature gradient structural component as claimed in any one of claims 1 to 3, wherein the structural component is an integrally formed structural component, and at least sequentially comprises the following components in the temperature gradient direction of the structural component: the preparation method comprises the following steps of:
firstly, initializing laser forming equipment;
secondly, constructing a three-dimensional model of the structural part, and then subdividing the three-dimensional model to generate a laser scanning path;
selecting the raw material materials of each layer of the structural member, wherein the components of the temperature gradient transition layer comprise the materials of a medium-temperature layer and a high-temperature layer, and the material of the high-temperature base layer is the same as that of the high-temperature layer;
fourthly, performing laser direct deposition treatment according to the material of the medium temperature layer to form the medium temperature layer;
fifthly, carrying out laser direct deposition treatment on the surface of the intermediate temperature layer according to the component proportion of the temperature gradient transition layer to form the temperature gradient transition layer;
sixthly, performing laser direct deposition treatment on the surface of the temperature gradient transition layer according to the material of the high-temperature basic layer to form a high-temperature basic layer;
and seventhly, performing laser direct deposition treatment on the surface of the high-temperature base layer according to the material of the high-temperature layer to form the high-temperature layer.
5. The laser direct deposition preparation method of the thin-walled large temperature gradient structural component according to claim 4, wherein in the first step, the initializing laser forming equipment comprises: and (4) carrying out system inspection and preparation work in the laser direct deposition equipment, and starting an atmosphere protection system to enable the oxygen content to be lower than 50 ppm.
6. The laser direct deposition preparation method of the thin-wall large temperature gradient structure according to claim 4, characterized in that in the second step, a three-dimensional model of the structure is established by using three-dimensional modeling software Siemens NX, the three-dimensional model is subdivided by using self-contained subdivision software of laser direct deposition equipment, the thicknesses of the subdivision single layers of the medium-temperature layer and the high-temperature layer are 0.4-0.6 mm, the thicknesses of the subdivision single layers of the temperature gradient transition layer and the high-temperature basic layer are 0.1-0.2 mm, and a CNC program generated by the subdivision software is input into the laser direct deposition equipment.
7. The laser direct deposition preparation method of the thin-wall large-temperature-gradient structural member as claimed in claim 4, wherein in the third step, the component distribution ratio and the single-layer thickness of each layer of the structural member are input into a powder feeder numerical control system of the laser direct deposition apparatus as numerical control variable values to control the powder feeding ratio and the powder feeding rate at different positions during laser direct deposition.
8. The laser direct deposition preparation method of the thin-wall large temperature gradient structural component according to claim 4, wherein in the fourth step, the process parameters of the laser direct deposition treatment for forming the intermediate temperature layer comprise: the scanning speed is 4-6 mm/s, the laser power is 1200-1800W, and the single-layer deposition thickness is 0.4-0.6 mm.
9. The laser direct deposition preparation method of the thin-wall large temperature gradient structural component according to claim 4, wherein in the fifth step, the process parameters of the laser direct deposition treatment for forming the temperature gradient transition layer comprise: the scanning speed is 1.5-2.5 mm/s, the laser power is 800-1200W, and the single-layer deposition thickness is 0.1-0.2 mm.
10. The laser direct deposition preparation method of the thin-wall large temperature gradient structural member according to claim 9, wherein the laser power is 800-1000W.
11. The laser direct deposition preparation method of the thin-wall large temperature gradient structural component as claimed in claim 4, wherein in the sixth step, the process parameters of the laser direct deposition treatment for forming the high temperature base layer include: the scanning speed is 1.5-2.5 mm/s, the laser power is 800-1200W, and the single-layer deposition thickness is 0.1-0.2 mm.
12. The laser direct deposition preparation method of the thin-wall large temperature gradient structural member according to claim 11, wherein the laser power is 800-1000W.
13. The laser direct deposition preparation method of the thin-wall large temperature gradient structural component according to claim 4, wherein in the seventh step, the process parameters of the laser direct deposition treatment for forming the high temperature layer include: the scanning speed is 4-6 mm/s, the laser power is 1200-1800W, and the single-layer deposition thickness is 0.4-0.6 mm.
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