CN117773148A - Rudder core forming processing method - Google Patents
Rudder core forming processing method Download PDFInfo
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- CN117773148A CN117773148A CN202311814602.6A CN202311814602A CN117773148A CN 117773148 A CN117773148 A CN 117773148A CN 202311814602 A CN202311814602 A CN 202311814602A CN 117773148 A CN117773148 A CN 117773148A
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- 238000003672 processing method Methods 0.000 title claims abstract description 10
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- 238000012805 post-processing Methods 0.000 claims abstract description 9
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Abstract
The disclosure provides a method for forming and processing a rudder core, comprising the following steps: obtaining a processing model of the rudder core according to a design size model of the rudder core; acquiring powder, and processing the powder to a solid part in a first state by adopting an SLM (selective laser sintering) molding process according to the processing model; post-processing is carried out on the first state solid part to obtain a second state solid part; and (3) carrying out finish machining on the solid part in the second state to obtain a finished part meeting the design size of the rudder core. Based on the above arrangement, the forming processing method of the rudder core provided by the embodiment of the disclosure can integrally form the framework, the skin and the rudder shaft through the SLM forming process, and the obtained rudder core part has high forming precision, good comprehensive mechanical property and high processing efficiency, is beneficial to shortening the production period, can improve the material utilization rate and is beneficial to reducing the production cost.
Description
Technical Field
The disclosure relates to the technical field of rudder core processing, in particular to a forming processing method of a rudder core.
Background
The rudder core is a thin-wall structural member with an inner cavity, which consists of a framework, a skin and a rudder shaft, and is often made of GH3625 alloy, and because the material is difficult to process, the precision requirement of parts is high, the parts cannot be integrally formed by using a traditional processing method, the forming method adopted at present is formed by adopting a mode of single mechanical processing and welding, but the forming method has long material preparation period, longer processing period and higher processing cost.
Disclosure of Invention
The present disclosure is directed to solving at least one of the technical problems existing in the prior art or related art.
For this reason, the present disclosure provides a method for forming and processing a rudder core.
In view of this, according to an embodiment of the present disclosure, a method for forming and processing a rudder core is provided, including:
obtaining a processing model of the rudder core according to the design size model of the rudder core;
acquiring powder, and processing the powder to a solid part in a first state by adopting an SLM (selective laser sintering) molding process according to a processing model;
post-processing is carried out on the first state solid part to obtain a second state solid part;
and (3) carrying out finish machining on the solid part in the second state to obtain a finished part meeting the design size of the rudder core.
In one possible embodiment, the step of obtaining a processing model of the rudder core according to the design size model of the rudder core includes:
adding machining allowance on the designed size model to obtain a first allowance model;
adding positioning allowance on the first allowance model to obtain a second allowance model;
adding a supporting allowance on the second allowance model to obtain a third allowance model;
and arranging a powder cleaning hole on the third allowance model to obtain a processing model.
In one possible embodiment, the positioning margin comprises:
the first positioning piece is positioned at one side of the rudder shaft of the first allowance model and positioned on an extension line of the opposite end of the tip end of the rudder core;
the second positioning piece is positioned at one side of the first allowance model, on which the rudder shaft machining allowance model is arranged;
the third positioning piece is positioned at one side of the first allowance model, which is far away from the rudder shaft;
the first locating piece and the second locating piece are respectively located at two sides of the rudder shaft.
In one possible embodiment, the support margin comprises:
the first supporting piece is connected to the tip of the rudder core along the length direction of the rudder shaft;
the second supporting piece is connected to one side of the rudder core, provided with the rudder shaft, along the length direction of the rudder shaft, and is arranged between the first positioning piece and the rudder shaft and/or between the second positioning piece and the rudder shaft at intervals;
the third supporting piece is arranged at the framework of the rudder core;
wherein, the one end that first support piece, second support piece, first setting element and second setting element kept away from the rudder core is located the coplanar.
In one possible embodiment, the step of obtaining the powder material and processing the powder material to the solid part in the first state by adopting the SLM forming process according to the processing model includes:
according to the size of the processing model and the material of the rudder core, a base plate is obtained and is arranged in a forming bin;
paving powder on a substrate according to a slice layer of the processing model, and scanning the powder by adopting laser to obtain a sintered base layer;
and paving powder layers layer by layer on the sintering base layer according to the slice layer of the processing model, and sintering the powder layers to obtain the solid part in the first state.
In one possible embodiment, the oxygen content in the forming bin is less than or equal to 1000PPM.
In one possible embodiment, the thickness of the powder layer is 0.05mm to 0.07mm;
the laser scanning interval is 0.08mm to 0.12mm;
the speed of the solid part of the laser scanning processing model is 900mm/s to 1100mm/s;
the speed of the inner contour of the laser scanning processing model is 650mm/s to 950mm/s;
the speed of the laser scanning of the outer contour of the machining pattern is 150mm/s to 450mm/s.
In one possible implementation, the step of post-processing the first state solid part to obtain the second state solid part includes:
cooling the solid parts in the first state to the indoor environment temperature in the inert gas atmosphere of the forming bin, and then taking out the solid parts in the first state;
removing the powder material remained in the solid part in the first state through the powder removing hole;
annealing the first-state solid part to obtain an annealed-state solid part;
cutting off the substrate of the solid part in the annealing state to obtain the solid part in the second state.
In a possible embodiment, the method further includes:
cutting a powder cleaning hole protruding out of the outer contour of the solid part in the second state;
and (5) plugging a powder cleaning hole on the surface of the solid part in the second state.
In a possible embodiment, the method further includes:
carrying out sand blasting treatment on the outer surface of the solid part in the second state;
wherein, the granularity of the abrasive adopted in the sand blowing treatment is 20 to 180 meshes; the pressure of the compressed air is 0.4MPa to 0.6MPa; the sand blowing distance is more than or equal to 100mm.
Compared with the prior art, the method at least comprises the following beneficial effects:
the forming processing method of the rudder core provided by the embodiment of the disclosure comprises the following steps: obtaining a processing model of the rudder core according to the design size model of the rudder core; acquiring powder, and processing the powder to a solid part in a first state by adopting an SLM (selective laser sintering) molding process according to a processing model; post-processing is carried out on the first state solid part to obtain a second state solid part; and (3) carrying out finish machining on the solid part in the second state to obtain a finished part meeting the design size of the rudder core. Based on the above arrangement, the forming processing method of the rudder core provided by the embodiment of the disclosure can integrally form the framework, the skin and the rudder shaft through the SLM forming process, and the obtained rudder core part has high forming precision, good comprehensive mechanical property and high processing efficiency, is beneficial to shortening the production period, can improve the material utilization rate and is beneficial to reducing the production cost.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the exemplary embodiments. The drawings are only for purposes of illustrating exemplary embodiments and are not to be construed as limiting the disclosure. Also, like reference numerals are used to designate like parts throughout the figures. In the drawings:
fig. 1 shows a flow diagram of a method for forming and processing a rudder core according to an embodiment of the present disclosure;
fig. 2 is a schematic structural diagram of a processing model in a method for forming and processing a rudder core according to an embodiment provided by the present disclosure.
The correspondence between the reference numerals and the component names in fig. 1 and 2 is:
a rudder shaft 100;
a first positioning member 201, a second positioning member 202, a third positioning member 203;
a first support 301, a second support 302, a third support 303;
powder cleaning hole 401.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1, according to an embodiment of the present disclosure, a method for forming and processing a rudder core is provided, including:
step S110: obtaining a processing model of the rudder core according to the design size model of the rudder core;
step S120: acquiring powder, and processing the powder to a solid part in a first state by adopting an SLM (selective laser sintering) molding process according to a processing model;
step S130: post-processing is carried out on the first state solid part to obtain a second state solid part;
step S140: and (3) carrying out finish machining on the solid part in the second state to obtain a finished part meeting the design size of the rudder core.
According to the forming processing method of the rudder core, firstly, according to a design size model of the rudder core, machining allowance sizes such as positioning allowance, supporting allowance, machining allowance and the like are increased on the original design size, and meanwhile, the design sizes of other auxiliary parts are correspondingly increased, so that a machining model of the rudder core is obtained; secondly, selecting proper powder, and adopting an SLM (Selective laser melting selective laser melting) forming process to process and form the selected powder according to the processing model until the powder accords with the processing model, so as to obtain a solid part in a first state; carrying out post-treatment on the solid part in the first state again, wherein the post-treatment comprises the treatment procedures of separating a substrate used for forming from the part, cleaning redundant powder, heat treatment, local machining and the like, so as to obtain the solid part in the second state, wherein the state of the solid part in the second state is similar to a design size model, and the deviation between the solid part in the second state and the design size model is the surface roughness and the surface size precision; and finally, carrying out finish machining on the second-state solid part, wherein the finish machining comprises the steps of removing the preset allowance size, processing the surface size precision of the second-state solid part, and processing the second-state solid part to a final size, so that the surface roughness and the surface size precision of the second-state solid part meet the design requirements, and further, obtaining the finished part meeting the design size of the rudder core.
It can be appreciated that during the forming process, the rudder core part can be vertically placed, that is, the rudder shaft 100 is placed downwards, so that the forming process is convenient, and meanwhile, the supporting allowance and the positioning allowance can be utilized for auxiliary supporting, so that the stability of the part in the forming process is improved.
It should be noted that, the rudder core part is a composite structure composed of a skeleton, a skin and a rudder shaft 100, in the conventional technology, three parts such as the skeleton, the skin and the rudder shaft 100 are often processed and molded by adopting a machining mode, and finally the skeleton, the skin and the rudder shaft 100 are welded together by means of a tool in a welding mode, so that the whole process period is long, the production efficiency is low, the utilization rate of raw materials is low, and the risk of welding deformation exists. Compared with the prior art, the forming processing method of the rudder core provided by the embodiment of the disclosure can integrally form the framework, the skin and the rudder shaft 100 through the SLM forming process, and the obtained rudder core part has high forming precision, good comprehensive mechanical property and high processing efficiency, is beneficial to shortening the production period, can improve the material utilization rate and is beneficial to reducing the production cost.
In some examples, as shown in fig. 2, the step of obtaining a processing model of the rudder core according to a design size model of the rudder core includes: adding machining allowance on the designed size model to obtain a first allowance model; adding positioning allowance on the first allowance model to obtain a second allowance model; adding a supporting allowance on the second allowance model to obtain a third allowance model; a powder cleaning hole 401 is provided on the third allowance mold to obtain a processing mold.
According to the technical scheme, the step of obtaining the processing model of the rudder core according to the design size model of the rudder core comprises the steps of firstly adding processing allowance on the basis of the design size model according to the design size model to obtain a first allowance model, wherein the processing allowance is reserved for the material reduction allowance of the subsequent processing procedure, and the normal operation of the subsequent processing procedure can be facilitated; secondly, on the basis of the first allowance model, adding positioning allowance to obtain a second allowance model, wherein the positioning allowance is used for positioning the rudder core part to be formed, so that the rudder core part is prevented from shifting in the subsequent processing process to influence the processing effect; thirdly, on the basis of the second allowance model, adding supporting allowance to obtain a third allowance model, wherein the supporting allowance is used for supporting the rudder core part, so that the stability of the rudder core part is improved, the rudder core part is prevented from tilting or toppling in the forming process and the processing process, and the normal operation of the forming process and the processing process is facilitated; and finally, setting a powder cleaning hole 401 on the basis of the third allowance model to obtain a processing model, wherein the powder cleaning hole 401 is used for removing residual redundant powder materials in the formed rudder core part.
It can be understood that a plurality of powder cleaning holes 401 can be arranged, because the framework of the rudder core part is of a hollow structure, the powder cleaning holes 401 can be communicated inside the framework, and because a frame space is also formed between the inner skin of the rudder core part and the framework, the powder cleaning holes 401 can also be communicated with the frame space between the inner skin of the rudder core part and the framework; the powder cleaning hole 401 should be in communication with the inside of the rudder core part in compliance with the gravity direction so that the powder material can be discharged from the powder cleaning hole 401 under the action of gravity.
For example, a knocking vibration mode may be adopted to clean the redundant powder inside the rudder core part, so that the redundant powder flows out from the powder cleaning hole 401, and the time for cleaning the redundant powder may be more than 30 minutes, so that the redundant powder can be cleaned.
In some examples, as shown in fig. 2, the positioning margin includes: the first positioning piece 201 is positioned on one side of the first allowance model, on which the rudder shaft 100 is arranged, and is positioned on an extension line of the opposite end of the tip of the rudder core;
the second positioning piece 202 is positioned at one side of the first allowance model where the rudder shaft 100 machining allowance model is arranged; a third positioning piece 203, which is positioned at one side of the first allowance model far away from the rudder shaft 100;
wherein the first positioning piece 201 and the second positioning piece 202 are respectively positioned at two sides of the rudder shaft 100.
In the above technical solution, the positioning allowance includes a first positioning element 201, a second positioning element 202 and a third positioning element 203, it is understood that the shape of the rudder core part is an obtuse triangle lacking an acute angle, if the side of the rudder shaft is assumed to be an edge of the obtuse triangle, two sides of the edge of the rudder shaft 100 are respectively an acute angle and an obtuse angle, the corresponding angle of the edge of the rudder shaft 100 is a missing angle, and the missing angle forms a short side, so that it is understood that the acute angle is a tip of the rudder core, the opposite end of the acute angle is an edge between the obtuse angle and the missing angle, where the first positioning element 201 is disposed on the edge of the rudder shaft 100 in the first allowance model and is located on an extension line of the edge between the obtuse angle and the missing angle, for implementing positioning at the position of the rudder core obtuse angle, the second positioning piece 202 is arranged on one side of the rudder shaft 100 in the first allowance model, namely, the second positioning piece 202 is positioned on the side of the rudder shaft 100 in the first allowance model, and the rudder shaft 100 is positioned between the first positioning piece 201 and the second positioning piece 202 along the extending direction of the side of the rudder shaft 100, namely, the second positioning piece 202 is positioned at the position of the side of the rudder shaft 100 near the tip of the rudder core, the first positioning piece 201 and the second positioning piece 202 are simultaneously used for positioning one side of the rudder shaft 100, the third positioning piece 203 is positioned on one side of the first allowance model far away from the rudder shaft 100, namely, the third positioning piece 203 is positioned at the short side formed by the missing angle in the rudder core part, so that the three positioning pieces can form a stable positioning structure for positioning the rudder core part at the short side formed by the missing angle, the position can be kept unchanged in the subsequent processing process of the rudder core part, the influence of the movement and the like of the rudder core part in the subsequent processing process on the processing effect is avoided.
It can be understood that the positioning allowance can also comprise fourth positioning pieces, fifth positioning pieces and the like, that is, the number of the positioning pieces can be set to be a plurality of positioning pieces, which is beneficial to improving the positioning stability.
In some examples, as shown in fig. 2, the support margin includes: a first support 301 connected to the tip of the rudder core along the length direction of the rudder shaft 100; the second supporting piece 302 is connected to one side of the rudder core provided with the rudder shaft 100 along the length direction of the rudder shaft 100, and is arranged between the first positioning piece 201 and the rudder shaft 100 and/or between the second positioning piece 202 and the rudder shaft 100 at intervals; a third support 303 disposed at the skeleton of the rudder core; wherein, the first supporting member 301, the second supporting member 302, the first positioning member 201 and the second positioning member 202 are located on the same plane at one end far away from the rudder core.
In the above technical solution, the supporting allowance includes a first supporting frame, a second supporting frame and a third supporting member 303, wherein the first supporting member 301 and the second supporting member 302 are all arranged along the length direction of the rudder shaft 100, the first supporting member 301 is connected with the tip of the rudder core, the second supporting member 302 and the rudder core are arranged at a certain interval on one side of the rudder shaft 100, the second supporting member 302 can be arranged between the first positioning member 201 and the rudder shaft 100, and the second supporting member 302 can also be arranged between the second positioning member 202 and the rudder shaft 100; the second support 302 may also be arranged between the first positioning member 201 and the rudder shaft 100 and between the second positioning member 202 and the rudder shaft 100 at the same time; the first supporting piece 301 and the second supporting piece 302 are used for integrally supporting the rudder core part, so that the rudder core part can be kept in a stable state in the subsequent processing process, one ends of the first supporting piece 301, the second supporting piece 302, the first positioning piece 201 and the second positioning piece 202, which are far away from the rudder core, are positioned on the same plane, the first supporting piece 301, the second supporting piece 302, the first positioning piece 201 and the second positioning piece 202 can be simultaneously abutted to the substrate in the forming process, the processing integrated forming is facilitated, and the first positioning piece 201 and the second positioning piece 202 can be simultaneously abutted to the supporting surface in the subsequent processing process, so that the stability of the rudder core part is improved; the third support piece 303 is arranged at the framework of the rudder core and is used for supporting the framework, so that the phenomenon that powder material falls down in the forming process of the framework can be avoided, and meanwhile, the structural strength of the framework can be improved.
In some examples, the step of obtaining the powder material and processing the powder material into the solid part in the first state using the SLM molding process according to the processing model includes: according to the size of the processing model and the material of the rudder core, a base plate is obtained and is arranged in a forming bin; paving powder on a substrate according to a slice layer of the processing model, and scanning the powder by adopting laser to obtain a sintered base layer; and paving powder layers layer by layer on the sintering base layer according to the slice layer of the processing model, and sintering the powder layers to obtain the solid part in the first state.
In the above technical solution, the step of obtaining the powder material and processing the powder material to the solid part in the first state by adopting the SLM molding process according to the processing model includes: firstly, acquiring a proper substrate according to the size of a processing model and the material of a rudder core, installing the selected substrate in a forming bin, and adjusting the position of the substrate to ensure proper treatment position of the substrate; secondly, paving powder materials on a substrate according to a slice layer of the processing model, and adopting laser to scan the powder materials to sinter the powder materials, so as to obtain a sintering base layer: and finally, on the basis of sintering the base layer, continuously paving powder layer by layer according to the slice layers of the processing model, and sintering the powder layer by adopting laser until all slice layers in the processing model are sintered, so that the solid part in the first state can be obtained, and the obtained solid part in the first state has higher precision and better comprehensive mechanical property.
It will be appreciated that since the molding process using the SLM molding process is sintered layer by layer, the tooling pattern is sliced prior to molding to form a plurality of sliced layers stacked one upon another.
It will be appreciated that the SLM forming process uses equipment with a doctor blade for spreading the powder, which often uses a rubber blade, and the doctor blade is removed to see the extent of damage before the forming process is performed, and a new doctor blade is replaced if necessary.
In some examples, the oxygen content within the forming bin is less than or equal to 1000PPM.
In the technical scheme, the oxygen content in the molding bin cannot be too high, and the powder material and the oxygen can be subjected to oxidation reaction due to the too high oxygen content, so that the molding effect is affected, and the oxygen content can be set to be less than or equal to 1000PPM.
In some examples, the thickness of the powder layer is 0.05mm to 0.07mm; the laser scanning interval is 0.08mm to 0.12mm; the speed of the solid part of the laser scanning processing model is 900mm/s to 1100mm/s; the speed of the inner contour of the laser scanning processing model is 650mm/s to 950mm/s; the speed of the laser scanning of the outer contour of the machining pattern is 150mm/s to 450mm/s.
In the technical scheme, the thickness of the powder layer can be 0.05mm to 0.07mm, and the laser scanning interval can be 0.08mm to 0.12mm; the speed of the laser scanning processing the solid part of the model can be 900mm/s to 1100mm/s; the speed of the laser scanning processing model inner contour can be 650mm/s to 950mm/s; the speed of the outer contour of the laser scanning processing model can be 150mm/s to 450mm/s, and based on the parameter setting, the quality and the strength of the solid part in the first state can be improved, the solid part in the first state has better dimensional accuracy and surface roughness, and the forming efficiency can be maintained.
In some examples, as shown in fig. 2, the step of post-processing the first state solid part to obtain the second state solid part includes: cooling the solid parts in the first state to the indoor environment temperature in the inert gas atmosphere of the forming bin, and then taking out the solid parts in the first state; powder remaining in the solid part in the first state is removed through the powder removing hole 401; annealing the first-state solid part to obtain an annealed-state solid part; cutting off the substrate of the solid part in the annealing state to obtain the solid part in the second state.
In the above technical solution, the step of post-processing the first state solid part to obtain the second state solid part includes: firstly, cooling a first-state solid part to indoor environment temperature in an inert gas atmosphere of a forming bin, and taking out the first-state solid part, wherein inert gases such as nitrogen, argon and the like; secondly, removing the powder material remained in the solid part in the first state through the powder material cleaning hole; the solid part in the first state is annealed again to obtain the solid part in the annealed state, and the process can improve or eliminate the structural defects and residual stress caused in the forming process, prevent the part from deforming and cracking and is beneficial to improving the comprehensive performance of the solid part in the first state; and finally cutting off the substrate of the solid part in the annealing state to obtain the solid part in the second state.
It will be appreciated that the holes provided in the part itself may also be used as the purge holes 401.
It is understood that the powder cleaning can be performed in a vibration mode, compressed air, ultrasonic cleaning, and a combination of the above modes, and is not limited in this way.
The first step is to clean the powder material in a knocking vibration mode for more than 30 minutes, so that the powder material flows out through a powder material cleaning hole; secondly, hoisting the solid part in the first state by using a crane in an angle conversion mode, cleaning the vibration powder for more than 30 minutes, and changing different hoisting points to incline the substrate by different angles so as to realize multidirectional powder cleaning; thirdly, high-pressure air can be adopted to carry out inflation and purging on the inside of the parts from each powder cleaning hole, and the cleaning time is more than 30 minutes; and the second step and the third step are repeatedly executed for 3 to 4 times until no obvious powder flows out, and finally, nondestructive detection can be combined, so that the powder inside the part can be thoroughly cleaned.
In some examples, further comprising: cutting a powder cleaning hole 401 protruding out of the outer contour of the solid part in the second state; the powder cleaning hole 401 on the surface of the solid part in the second state is plugged.
In the above technical solution, the method for forming and processing the rudder core further includes: after the powder cleaning is finished, the powder cleaning holes 401 protruding out of the outer contour of the solid part in the second state can be cut and removed, and the powder cleaning holes 401 on the surface of the solid part in the second state are blocked in a welding mode, so that other pollutants can be prevented from entering from the powder cleaning holes 401.
Note that, in the process of plugging the powder cleaning hole 401, care should be taken not to plug the hole of the part.
In some examples, as shown in fig. 1, further comprising: carrying out sand blasting treatment on the outer surface of the solid part in the second state; wherein, the granularity of the abrasive adopted in the sand blowing treatment is 20 to 180 meshes; the pressure of the compressed air is 0.4MPa to 0.6MPa; the sand blowing distance is more than or equal to 100mm.
In the above technical solution, the method for forming and processing the rudder core further includes: the outer surface of the solid part in the second state is subjected to sand blasting treatment, so that the oxide skin and greasy dirt on the surface of the part are improved, the smoothness and flatness of the surface of the part are improved, and meanwhile, the adhesive force and corrosion resistance of the surface of the part can be increased, so that the reliability and the service life of the part are improved.
In the technical scheme, the granularity of the abrasive adopted in the sand blowing treatment is 20-180 meshes, so that the part after sand blowing has good surface roughness; the compressed air pressure is 0.4MPa to 0.6MPa, so that the roughness of the surface of the part can be ensured to meet the requirement, and the sand blowing efficiency can be ensured; the sand blowing distance is more than or equal to 100mm, which is beneficial to ensuring the surface roughness of the parts.
It is understood that the holes communicated with the inner cavity of the part are blocked before sand blowing, so that the abrasive is prevented from entering the inner cavity of the part.
In this disclosure, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance; the term "plurality" means two or more, unless expressly defined otherwise. The terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; "coupled" may be directly coupled or indirectly coupled through intermediaries. The specific meaning of the terms in this disclosure will be understood by those of ordinary skill in the art as the case may be.
In the description of the present disclosure, it should be understood that the directions or positional relationships indicated by the terms "upper", "lower", "left", "right", "front", "rear", etc., are based on the directions or positional relationships shown in the drawings, are merely for convenience in describing the present disclosure and simplifying the description, and do not indicate or imply that the devices or units referred to must have a specific direction, be configured and operated in a specific direction, and thus should not be construed as limiting the present disclosure.
In the description of the present specification, the terms "one embodiment," "some embodiments," "particular embodiments," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present disclosure. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is merely a preferred embodiment of the present disclosure, and is not intended to limit the present disclosure, so that various modifications and changes may be made to the present disclosure by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present disclosure should be included in the protection scope of the present disclosure.
Claims (10)
1. The forming processing method of the rudder core is characterized by comprising the following steps of:
obtaining a processing model of the rudder core according to a design size model of the rudder core;
acquiring powder, and processing the powder to a solid part in a first state by adopting an SLM (selective laser sintering) molding process according to the processing model;
post-processing is carried out on the first state solid part to obtain a second state solid part;
and (3) carrying out finish machining on the solid part in the second state to obtain a finished part meeting the design size of the rudder core.
2. The method of forming a rudder core according to claim 1, wherein the step of obtaining the processing model of the rudder core according to the design size model of the rudder core comprises:
adding machining allowance on the design size model to obtain a first allowance model;
adding positioning allowance on the first allowance model to obtain a second allowance model;
adding a supporting allowance on the second allowance model to obtain a third allowance model;
and arranging a powder cleaning hole on the third allowance model to obtain the processing model.
3. The method of forming a rudder core according to claim 2, wherein the positioning margin includes:
the first positioning piece is positioned at one side of the rudder shaft of the first allowance model and positioned on an extension line of the opposite end of the tip of the rudder core;
the second positioning piece is positioned at one side of the first allowance model, on which the rudder shaft machining allowance model is arranged;
the third positioning piece is positioned at one side of the first allowance model, which is far away from the rudder shaft;
the first locating piece and the second locating piece are respectively located on two sides of the rudder shaft.
4. A method of forming a rudder core according to claim 3, wherein the support margin comprises:
the first supporting piece is connected to the tip of the rudder core along the length direction of the rudder shaft;
the second supporting piece is connected to one side, provided with the rudder shaft, of the rudder core along the length direction of the rudder shaft, and is arranged between the first positioning piece and the rudder shaft and/or between the second positioning piece and the rudder shaft at intervals;
the third supporting piece is arranged at the framework of the rudder core;
the first supporting piece, the second supporting piece, the first positioning piece and one end, far away from the rudder core, of the second positioning piece are located on the same plane.
5. The method for forming and processing the rudder core according to claim 3, wherein the step of obtaining the powder material and processing the powder material into the solid part in the first state by adopting the SLM forming process according to the processing model comprises:
according to the size of the processing model and the material of the rudder core, a substrate is obtained, and the substrate is installed in a forming bin;
paving the powder on the substrate according to the slice layer of the processing model, and scanning the powder by adopting laser to obtain a sintered base layer;
and paving powder layers layer by layer on the sintering base layer according to the slice layer of the processing model, and sintering the powder layers to obtain the solid part in the first state.
6. The method for forming a rudder core according to claim 5, wherein,
the oxygen content in the molding bin is less than or equal to 1000PPM.
7. The method for forming a rudder core according to claim 5, wherein,
the thickness of the powder layer is 0.05mm to 0.07mm;
the laser scanning interval is 0.08mm to 0.12mm;
the speed of the laser scanning the solid part of the processing model is 900mm/s to 1100mm/s;
the speed of the laser scanning the inner contour of the processing model is 650mm/s to 950mm/s;
the laser scans the outer contour of the working model at a speed of 150mm/s to 450mm/s.
8. The method of claim 5, wherein the step of post-processing the first state solid part to obtain a second state solid part comprises:
cooling the first-state solid part to indoor environment temperature in the inert gas atmosphere of the forming bin, and then taking out the first-state solid part;
removing the powder material remained in the solid part in the first state through the powder removing hole;
annealing the first state solid part to obtain an annealed state solid part;
cutting off the substrate of the annealed solid part to obtain the solid part in the second state.
9. The method of forming a rudder core according to claim 8, further comprising:
cutting the powder cleaning hole protruding out of the outer contour of the solid part in the second state;
and sealing the powder cleaning hole on the surface of the solid part in the second state.
10. The method of forming a rudder core according to claim 8, further comprising:
performing sand blasting treatment on the outer surface of the second-state solid part;
wherein, the granularity of the abrasive adopted in the sand blowing treatment is 20 to 180 meshes; the pressure of the compressed air is 0.4MPa to 0.6MPa; the sand blowing distance is more than or equal to 100mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311814602.6A CN117773148A (en) | 2023-12-26 | 2023-12-26 | Rudder core forming processing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311814602.6A CN117773148A (en) | 2023-12-26 | 2023-12-26 | Rudder core forming processing method |
Publications (1)
| Publication Number | Publication Date |
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| CN117773148A true CN117773148A (en) | 2024-03-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311814602.6A Pending CN117773148A (en) | 2023-12-26 | 2023-12-26 | Rudder core forming processing method |
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| Country | Link |
|---|---|
| CN (1) | CN117773148A (en) |
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2023
- 2023-12-26 CN CN202311814602.6A patent/CN117773148A/en active Pending
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