CN114367713B - Machining method for segmented 3D printing turbine guide vane blank - Google Patents
Machining method for segmented 3D printing turbine guide vane blank Download PDFInfo
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- CN114367713B CN114367713B CN202210110746.2A CN202210110746A CN114367713B CN 114367713 B CN114367713 B CN 114367713B CN 202210110746 A CN202210110746 A CN 202210110746A CN 114367713 B CN114367713 B CN 114367713B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
- B23H7/00—Processes or apparatus applicable to both electrical discharge machining and electrochemical machining
- B23H7/02—Wire-cutting
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23H—WORKING OF METAL BY THE ACTION OF A HIGH CONCENTRATION OF ELECTRIC CURRENT ON A WORKPIECE USING AN ELECTRODE WHICH TAKES THE PLACE OF A TOOL; SUCH WORKING COMBINED WITH OTHER FORMS OF WORKING OF METAL
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Abstract
The invention discloses a machining method of a segmented 3D printing turbine guide vane blank, which comprises the following steps: determining an end surface reference of the guide vane blank; determining a radial reference for the guide vane blank; and carrying out full-ring material removing processing on the guide vane blank according to the determined end surface reference and the radial reference of the guide vane blank. In machining, the most important process is to determine the end face reference and the radial reference first. Only if a good machining reference is found, the subsequent end face machining and round face machining can be guaranteed to meet the form and position tolerance requirements. The processing technology method for processing the positioning reference surface based on the 3D printing multi-connected guide vane blade profile and the runner and then carrying out whole-ring material removal processing and forming has great advantages in processing accuracy, processing economy and processing time cost through designing a simple tool.
Description
Technical Field
The invention relates to the technical field of blade machining, in particular to a machining method of a segmented 3D printing turbine guide blade blank.
Background
The turbine guide vane of the modern aero-engine is generally manufactured by adopting a vane body allowance-free precision casting process, and is finally formed by local machining. In the machining process of the blank, the reference is generally established by a six-point positioning method at present to accurately position the blank, namely an unconstrained space object, and the motion of the space object has 6 degrees of freedom. Every time a datum positioning point is introduced, a constraint is added, and 6 positioning points can reduce the freedom degree of the movement of the object to zero, so that complete positioning is realized. The 6 reference target points are chosen on the theoretical profile of the geometric model. The application of the six-point positioning method needs to be realized by designing a clamp. During fixture design, the positioning element (ball head supporting pin or cylindrical pin) simulates the contact of the fixture and a theoretical positioning point on the blank to realize the accurate positioning of the blade blank. In the prior art, a complete set of complex positioning tools are required to be designed for processing the blade blank by a six-point positioning method, and the blade blank is processed in a single piece, so that the processing period is longer, and the processing of the complete set of blade blank can be completed usually within 6-12 months.
In recent years, 3D printed parts have been put to practical use in the field of aeroengine component testing. Its main advantage is quick shaping of parts. The traditional six-point positioning method is adopted to process the 3D printing turbine guide vane blank, the working procedure is complex, the processing period is usually 6-12 months, and the principle of rapid manufacturing and forming of the 3D printing vane is not met.
In machining, the most important process is to determine the end face reference and the radial reference first. Only if a good machining reference is found, the subsequent end face machining and round face machining can be guaranteed to meet the form and position tolerance requirements. Therefore, a precise and simple processing technology with short processing period for processing tools is needed. The prior art scheme is generally used for machining the real blade of the engine, and has high machining requirements and machining precision. The technical scheme is that the processing technology method comprises the steps of processing a positioning reference surface based on a blade shape and a runner, then carrying out whole-ring material removal processing and forming, and the processing period of the finished guide blade processed by the method is about 1 half month and is less than 1/3 of that of the existing processing method, so that the rapid finish machining of the 3D printing turbine guide blade blank can be realized.
Disclosure of Invention
The invention aims to provide a machining method for a segmented 3D printing turbine guide vane blank, which aims to solve the problems in the prior art.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a method of machining a segmented 3D printed turbine guide vane blank, the method comprising: determining an end surface reference of the guide vane blank; determining a radial reference for the guide vane blank; and carrying out full-ring material removing processing on the guide vane blank according to the determined end surface reference and the radial reference of the guide vane blank.
Preferably, the step of determining an end face reference of the guide vane blank comprises: designing a half-moon-shaped equal-height stop block tool; one side of the half-moon-shaped equal-height stop block tool is connected with a standard block through a bolt, the other side of the half-moon-shaped equal-height stop block tool is connected with the blade-shaped tail edge of the guide blade blank through a bolt, and the half-moon-shaped equal-height stop block tool is fixed on a linear cutting machine through a compression nut and a screw; machining the outer end face C of the upper edge plate of the guide vane blank; and checking and determining that the runout of the end face C of the outer side end face of the upper edge plate of the guide vane blank meets the requirement so as to confirm that the end face machining standard meets the requirement.
Preferably, the standard block is rectangular; and the D edge of the standard block is parallel to the outer side end face C of the upper edge plate of the guide vane blank.
Preferably, the processing of the outer end face C of the upper edge plate of the guide vane blank is performed by a slow wire cutting method.
Preferably, the step of determining a radial reference of the guide vane blank comprises: designing a disc type structure fixing tool; splicing a plurality of guide vane blanks into a whole ring, and preliminarily fixing the whole ring on the disc-type structure fixing tool; the end face of the upper edge plate of the guide vane blank is in pressing contact or small clearance fit with the disc structure fixing tool; adjusting the radial positions of the multiple guide vane blanks spliced into a whole ring; and after the flow channel size and the circumferential runout of all the blade blanks in the flow channel are checked and determined to meet the requirements, the bolts are screwed down to fix the positions of the blade blanks so as to determine the radial machining standard.
Preferably, the disc structure fixing tool comprises a plurality of bolt holes, a plurality of precise pin holes and a precise center hole; the bolt holes and the precise pin holes are uniformly distributed around the disc structure fixing tool; the diameter sizes of the cylindrical surfaces at two positions of the precise pin hole differ by 1mm, and the two modes of forward installation and reverse installation are adopted according to different installation directions for adjusting the radial position of the blade blank; the bolt holes are used for fixing the positions of the blade blanks; the precise center hole is used for radial alignment of the blade blank and flow channel height measurement.
Preferably, the radial positions of the guide vane blanks which are spliced into a whole ring are adjusted through a positioning surface at the maximum radius of the guide vane blanks, two precise pins and a feeler gauge.
Preferably, the method for adjusting the radial positions of the multiple guide vane blanks in the spliced whole ring according to the positioning surface where the radius of the guide vane blank is maximum, two precise pins and a feeler gauge comprises the following steps:
after the disc type structure fixing tool is radially aligned on a machine tool, when the distance between the guide vane blank runner and the center hole of the disc type structure fixing tool accords with the designed radius size of the disc type structure fixing tool runner, the precise pin is positively installed;
after the disc type structure fixing tool is radially aligned on the machine tool, when the distance between the guide vane blank runner and the center hole of the disc type structure fixing tool is not in accordance with the designed radius size of the disc type structure fixing tool runner, the precise pin is reversely arranged, a gap of 0.5mm is reserved, and further fine adjustment is performed through the clearance gauge.
Preferably, the step of performing full-ring blanking processing on the guide vane blank according to the determined end surface reference and radial reference of the guide vane blank comprises the following steps: carrying out wax filling processing on the disc type structure fixing tool of the guide vane blank with the determined processing standard; and after the processing is finished, melting wax, and disassembling the compression bolt to obtain a single blade finished product.
Preferably, the wax filling treatment is performed on the disc structure fixing tool before the whole-ring material removing processing is performed.
Preferably, the wax is poured into the disc-type structure fixing tool for determining the guide vane blank with the machining standard, and the wax is required to be ensured to seal each guide vane blank.
Preferably, the method is applied to a machining fixture for a guide vane blank, the fixture comprises a half-moon-shaped equal-height stop block fixture and a disc-type structure fixture, wherein,
the half-moon-shaped equal-height stop block tool is used for fixedly processing the end face of the guide vane blank;
the disc type structure fixing tool is used for fixing and processing radial machining of the guide vane blank.
Preferably, the half-moon-shaped equal-height stop block tool is designed by taking the leading edge or the trailing edge of the blade profile as a reference surface according to the 3D printing guide blade.
Preferably, the disc type structure fixing tool is designed according to the positioning processing of the 3D printing guide vane runner.
The invention has the technical effects and advantages that:
compared with the best prior art, the technical scheme comprehensively considers the processing accuracy, the processing economy and the processing time cost of the blade blank.
1. Designing a contour stop block by taking the front edge or the tail edge of the blade profile as a reference surface, and processing an end surface reference through a slow wire; adjusting the radial position of a blade blank through a precise pin and a feeler gauge by using a disc type fixing tool with a precise center hole, and aligning a radial reference; before the whole ring processing, wax filling treatment is carried out, after the processing is finished, wax is melted, and a compression bolt is disassembled to obtain a single-piece blade finished product;
2. according to the technical scheme, the processing standard is obtained based on the blade profile and the flow channel, and the blade profile and the flow channel position of the finished blade product can be ensured to meet the requirements by processing based on the processing standard;
3. the processing technology and the processing tool in the technical scheme of the invention are simple, and the processing is one-time processing of the whole ring, so that the processing cost of the blade blank can be greatly reduced;
4. according to the technical scheme, the processing period from process formulation to processing of the finished guide blade is about 1 half month, and is less than 1/3 of the processing period required by the prior art scheme, so that the processing time can be greatly shortened;
in summary, the invention provides a method for processing a positioning reference surface based on the biological blade profile and the runner of the guide blade blank, which can ensure that the blade profile and the runner position of the finished blade product meet the requirements; and then the whole ring is removed, and the processing cost of the blade blank is greatly reduced. The processing technology and the processing tool in the scheme of the invention are simple, and meanwhile, the processing period from technological formulation to processing of the finished guide vane is about 1 half month, which is less than 1/3 of the processing period required by the prior art scheme. Although the method is inferior to the prior art in terms of machining precision, the method has obvious advantages in terms of machining time and machining cost, can ensure higher machining precision, and is very suitable for rapid finish machining of the 3D printing guide vane in the turbine part test. The invention is used for processing the 3D printing guide vane blank of the gas turbine part test of a certain engine, and the guide vane finished product processed by the technical scheme of the invention has good installability and usability and can be successfully applied to the turbine part test of an aeroengine.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
Drawings
FIG. 1 is a schematic view of a type of vane construction with a bolted mounting edge;
FIG. 2 is a schematic view of a half-moon shaped contour stop;
FIG. 3 is a schematic illustration of a half-moon shaped contour stop installation;
FIG. 4 is a schematic diagram of end face referencing;
FIG. 5 is a schematic view of a disc type structure fixing tool;
FIG. 6 is a schematic diagram of a precision pin configuration;
FIG. 7 is a schematic view of radial reference adjustment;
fig. 8 is a schematic diagram of a full-circle process.
In the figure: 1. an upper edge plate; 2. a blade leading edge; 3. blade trailing edge; 4. a lower edge plate; 5. bolt holes; 6. standard square blocks; 7. a contour stop; 8. a guide vane blank; 9. a pressing plate; 10. a compression nut; 11. a screw; 12. a disc fixing tool; 13. a precision pin; 14. a compression bolt; 15. a guide vane blank; 16. an adjustment pad; 17. a flow path surface.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention discloses a processing technique which is characterized in that a positioning reference surface is processed based on a 3D printing multi-connected guide vane profile and a runner through a simple tooling, and the processing technique is one-time processing for whole rings, so that the processing cost of vane blanks can be greatly reduced, and then the processing technique is one-time material removing processing and forming, and the processing based on the processing reference can ensure that the profile and the runner position of vane finished products meet the requirements.
The prior art scheme is generally used for machining the real blade of the engine, and has high machining requirements and machining precision. The technical scheme is inferior to the prior art scheme in the aspect of machining precision, but has obvious advantages in the aspects of machining time and machining cost, can ensure higher machining precision, and is very suitable for rapid fine machining of the 3D printing guide vane in the turbine part test. In machining, the most important process is to determine the end face reference and the radial reference first. Only if a good machining reference is found, the subsequent end face machining and round face machining can be guaranteed to meet the form and position tolerance requirements.
Compared with the best prior art, the technical scheme comprehensively considers the processing accuracy, the processing economy and the processing time cost. The technical scheme of the invention has a processing period from process formulation to processing of the finished guide vane of about 1 half month, which is less than 1/3 of the processing period required by the prior art scheme, and can greatly shorten the processing time. Specific embodiments can be divided into: determining an end face reference of a guide vane blank, determining a radial reference of the guide vane blank, and carrying out full-ring material removal processing on the guide vane blank according to the determined end face reference and the radial reference of the guide vane blank, wherein the three parts are as follows:
the invention is based on a kind of guide vane blank with a bolt mounting edge shown in fig. 1, and referring to fig. 1, the guide vane blank comprises an upper edge plate, a vane leading edge, a vane trailing edge, a lower edge plate and bolt holes, wherein the bolt holes are positioned on the end face of the upper edge plate, and the vane leading edge and the vane trailing edge form a vane positioned between the upper edge plate and the lower edge plate.
Further, according to the above-mentioned guide vane blank, according to the 3D printed multi-gang guide vane, the blade profile leading edge or trailing edge is used as a reference surface, and a contour stop tool as shown in fig. 2 is designed and processed, where fig. 2a is a front view of the contour stop tool, and fig. 2b is a side view of the contour stop tool, which is used to assist in determining an end surface reference of the guide vane blank, and referring to fig. 2, the contour stop in this embodiment is a half-moon stop with bolt holes on two sides.
Furthermore, according to the mode shown in fig. 3, one side of the half-moon-shaped equal-height stop block tool is connected and fixed with the standard block through a bolt.
Further, as shown in fig. 4, fig. 4a is an end surface reference machining front view, fig. 5b is an end surface reference machining side view, one side of the half-moon-shaped equal-height stop block tool is connected with a standard block through a bolt, the other side of the half-moon-shaped equal-height stop block tool is connected with a blade-shaped tail edge of the guide blade blank through a bolt, and one side parallel to the end surface is selected.
Further, the standard block is rectangular; and the D edge of the standard block is parallel to the outer side end face C of the upper edge plate of the guide vane blank.
Furthermore, the roughness of the end face C processed through slow wire cutting can reach Ra0.8, the flatness is within 0.02mm, and the good parallelism of the processed end face and the plane where the blade profile tail edge is located can be ensured through the tool. The end face reference C can thus be used for subsequent end face processing of the guide vane blank.
Further, the end face C after the slow wire cutting processing is checked by a run-out dial indicator, and the run-out value is less than 0.02, so that the requirement is met.
After the end surface reference of the guide vane is determined, the radial reference of the guide vane is determined, and the specific steps are as follows:
and according to the runner positioning of the 3D printing multi-connected guide vane, a disc structure fixing tool is processed and designed.
Further, as shown in fig. 5, in which fig. 5a is a front view of the disc type structure fixing tool, and fig. 5b is a side view of the disc type structure fixing tool, the disc type structure fixing tool includes a plurality of bolt holes, a plurality of precision pin holes, and a precision center hole (Φ16). The bolt holes and the precise pin holes are uniformly distributed around the disc; the precise pin holes are used for adjusting the radial positions of the guide vane blanks; the bolt holes are used for fixing the positions of the guide vane blanks; the precision center hole (phi 16) is used for radial alignment and flow channel height measurement.
Furthermore, the multiple guide vane blanks with the determined end face standard are spliced into a whole ring through bolts, and the whole ring is preliminarily fixed on a tool. The end face C at the upper edge plate of the blank is kept in pressing contact with the disc through bolts to provide main support, and the end face at the lower edge plate of the blank is kept in pressing contact with the adjusting pad or in small clearance fit through adjusting the height of the pad to provide auxiliary support.
Further, the radial positions of the guide vane blanks spliced into the whole ring are adjusted through the positioning surface at the maximum radius of the guide vane blanks, two precise pins and a feeler gauge.
Further, the radial position of the blank is adjusted through the guide vane blank flow surface and two precise pins, wherein the precise pin structure diagram is shown in fig. 6, the diameter sizes of two cylindrical surfaces of the precise pins are different by 1mm, and the two modes of forward installation and reverse installation are provided according to different installation directions.
Further, after the disc type structure fixing tool is radially aligned on the machine tool, whether the runner sizes and the circumference runout of all the blade blanks in the disc type structure fixing tool runner meet the requirements or not is checked.
Further, if the radial position of the blank is not satisfactory, the radial position adjustment of the blank is carried out according to the following method: referring to fig. 7, after the reference of the disc tooling a is radially aligned on the machine tool, when the distance between the flow passage surface of the blank and the central hole of the disc accords with the designed radius size of the flow passage, the pin is positively installed; otherwise, the pin is reversely arranged. When the pin is reversely assembled, a gap of 0.5mm is reserved between the pin and the upper edge plate, the radial position of the guide vane blank can be finely adjusted by inserting a feeler gauge until the size of a runner of the runner face of the vane blank and the circumferential runout meet the requirements, and then the bolt is screwed to fix the position of the vane blank. The number of the blades is 7 in the circumferential direction, and after the 7 blades are subjected to the adjustment operation, the whole circle of blades with the size of the flow channel and the circumferential runout meeting the requirements can be obtained, and the radial machining standard of the whole machining of the guide vane blank is determined by fixing the current position.
Further, after the runner sizes and the circumferential runout of all the blade blanks of the runner are checked and confirmed again to meet the requirements, the bolts are screwed down to fix the positions of the blade blanks, and therefore the radial machining standard is determined.
In machining, the most important process is to determine the end face reference and the radial reference first. Only if a good machining reference is found, the subsequent end face machining and round face machining can be guaranteed to meet the form and position tolerance requirements. In the embodiment, the end surface datum and the radial datum are determined based on the blade profile and the flow channel of the blade blank, and the blade profile and the flow channel position of the finished blade product can meet the requirements by processing based on the processing datum.
After the end face machining and radial machining references are determined, full-ring material removal machining can be performed, and as shown in fig. 8, a plurality of guide vane blanks are fixed in a disc tool in a ring forming manner through screws. The specific steps of the whole ring material removing processing are as follows:
and (3) carrying out wax filling treatment on the disc-type structure fixing tool for determining the guide vane blank with the machining standard, and confirming and ensuring that each vane blank in the disc-type structure fixing tool is completely sealed by wax. Therefore, scrap iron in the processing process can be prevented from entering the air film hole and the cold air channel, the rigidity of the whole ring structure can be increased, and the generation of vibration cutter lines is reduced.
Further, after the wax is filled and the wax is completely solidified, the guide vane blank on the disc structure fixing tool is subjected to common material removing processing.
Further, after the processing is finished, wax is melted, and the pressing bolt is disassembled, so that a single guide vane finished product can be obtained.
In the embodiment, the processing cost of the blade blank is greatly reduced through one-time processing of the whole ring. Meanwhile, the processing period from process formulation to processing of the finished guide vane is about 1 half month, which is less than 1/3 of the processing period required by the prior art scheme, and the processing time is greatly shortened.
The prior art scheme is generally used for machining the real blade of the engine, and has high machining requirements and machining precision. The technical scheme is inferior to the prior art scheme in the aspect of machining precision, but has obvious advantages in the aspects of machining time and machining cost, can ensure higher machining precision, and is very suitable for rapid fine machining of the 3D printing guide vane in the turbine part test.
The working principle and the working process of the device are as follows:
according to the technical scheme, the machining accuracy, the machining economy and the machining time cost are comprehensively considered, the blade-shaped front edge or the tail edge is taken as a reference surface, a contour stop block tool is designed, and an end face reference is machined through a slow wire machining process; a disc type fixing tool with a precise center hole is designed by taking a blade-shaped runner as a reference, the radial position of a blade blank is adjusted through a positioning surface at the minimum radius of the blade blank, a precise pin and a feeler gauge, and a machining radial reference is determined; and (3) before the whole ring processing, carrying out wax filling treatment, melting wax after the processing is finished, and disassembling the compression bolt to obtain the finished product of the single blade. The processing technology and the processing tool in the technical scheme of the invention are simple, the processing cost of the blade blank can be greatly reduced for one-time processing of the whole ring, and meanwhile, the processing period from technological formulation to processing of the finished guide blade is about 1 half month, which is less than 1/3 of the processing period required by the prior art scheme, and the processing time is greatly shortened.
Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present invention.
Claims (14)
1. A method of machining a segmented 3D printed turbine guide vane blank, the method comprising:
determining an end surface reference of a guide vane blank based on a half-moon-shaped contour stop block tool;
determining a radial reference of the guide vane blank based on a disc type structure fixing tool;
and carrying out full-ring material removing processing on the guide vane blank according to the determined end surface reference and the radial reference of the guide vane blank.
2. The method of claim 1, wherein the step of determining an end face reference of the guide vane blank comprises:
designing a half-moon-shaped equal-height stop block tool;
one side of the half-moon-shaped equal-height stop block tool is connected with a standard block through a bolt, the other side of the half-moon-shaped equal-height stop block tool is connected with the blade-shaped tail edge of the guide blade blank through a bolt, and the half-moon-shaped equal-height stop block tool is fixed on a linear cutting machine through a compression nut and a screw;
machining the outer end face C of the upper edge plate of the guide vane blank;
and checking and determining that the runout of the end face C of the outer side end face of the upper edge plate of the guide vane blank meets the requirement so as to confirm that the end face machining standard meets the requirement.
3. The method of claim 2, wherein the step of determining the position of the substrate comprises,
the standard block is rectangular;
and the D edge of the standard block is parallel to the outer side end face C of the upper edge plate of the guide vane blank.
4. The method of claim 2, wherein the step of determining the position of the substrate comprises,
and the outer side end face C of the upper edge plate of the guide vane blank is processed by a slow wire cutting method.
5. The method of claim 1, wherein the step of determining a radial reference for the guide vane blank comprises:
designing a disc type structure fixing tool;
splicing a plurality of guide vane blanks into a whole ring, and preliminarily fixing the whole ring on the disc-type structure fixing tool;
the end face of the upper edge plate of the guide vane blank is in pressing contact or small clearance fit with the disc structure fixing tool;
adjusting the radial positions of the multiple guide vane blanks spliced into a whole ring;
and after the flow channel size and the circumferential runout of all the blade blanks in the flow channel are checked and determined to meet the requirements, the bolts are screwed down to fix the positions of the blade blanks so as to determine the radial machining standard.
6. The method of claim 5, wherein the disc structure fixing tool comprises a plurality of bolt holes, a plurality of precision pin holes and a precision center hole;
the bolt holes and the precise pin holes are uniformly distributed around the disc structure fixing tool;
the diameter sizes of the cylindrical surfaces at two positions of the precise pin hole differ by 1mm, and the two modes of forward installation and reverse installation are adopted according to different installation directions for adjusting the radial position of the blade blank;
the bolt holes are used for fixing the positions of the blade blanks;
the precise center hole is used for radial alignment of the blade blank and flow channel height measurement.
7. The method of claim 5, wherein the radial position of the pieced-together ring of multiple guide vane blanks is adjusted by a locating surface at which the radius of the guide vane blank is greatest, two precision pins, and a feeler gauge.
8. The method of claim 7, wherein adjusting the radial position of the piecewise full ring of multiple guide vane blanks based on the locating surface where the radius of the guide vane blank is greatest, two precision pins, and a feeler gauge comprises:
after the disc type structure fixing tool is radially aligned on a machine tool, when the distance between the guide vane blank runner and the center hole of the disc type structure fixing tool accords with the designed radius size of the disc type structure fixing tool runner, the precise pin is positively installed;
after the disc type structure fixing tool is radially aligned on the machine tool, when the distance between the guide vane blank runner and the center hole of the disc type structure fixing tool is not in accordance with the designed radius size of the disc type structure fixing tool runner, the precise pin is reversely arranged, a gap of 0.5mm is reserved, and further fine adjustment is performed through the clearance gauge.
9. The method of claim 1, wherein the step of full-ring blanking the guide vane blank based on the determined end face reference and radial reference of the guide vane blank comprises:
carrying out wax filling processing on a disc-type structure fixing tool of the guide vane blank with the determined processing standard;
and after the processing is finished, melting wax, and disassembling the compression bolt to obtain a single blade finished product.
10. The method of claim 9, wherein the step of determining the position of the substrate comprises,
the wax filling treatment is carried out on the disc type structure fixing tool, and the wax filling treatment is carried out before the whole-ring material removing processing is carried out.
11. The method according to claim 9 or 10, wherein,
and (3) carrying out wax filling on the disc-type structure fixing tool for determining the guide vane blank with the machining standard, wherein the wax is required to be ensured to seal each guide vane blank.
12. The method according to any of the claims 1-9, characterized in that the method is applied to a machining fixture for a guide vane blank, the fixture comprising a half-moon contour stop fixture and a disc-like structure fixture, wherein,
the half-moon-shaped equal-height stop block tool is used for fixedly processing the end face of the guide vane blank;
the disc type structure fixing tool is used for fixing and processing radial machining of the guide vane blank.
13. The method of claim 12, wherein the step of determining the position of the probe is performed,
the half-moon-shaped equal-height stop block tool is designed by taking the leading edge or the trailing edge of a blade shape as a reference surface according to the 3D printing guide blade.
14. The method of claim 12, wherein the step of determining the position of the probe is performed,
the disc type structure fixing tool is designed according to the 3D printing guide vane runner positioning machining.
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