CN114367713A - Machining method for split type 3D printing turbine guide blade blank - Google Patents
Machining method for split type 3D printing turbine guide blade blank Download PDFInfo
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- CN114367713A CN114367713A CN202210110746.2A CN202210110746A CN114367713A CN 114367713 A CN114367713 A CN 114367713A CN 202210110746 A CN202210110746 A CN 202210110746A CN 114367713 A CN114367713 A CN 114367713A
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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 for a split type 3D printing turbine guide blade blank, which comprises the following steps: determining the end surface reference of a guide blade blank; determining a radial reference of the guide vane blank; and carrying out whole-ring material removing processing on the guide vane blank according to the determined end surface reference and radial reference of the guide vane blank. In machining, the most important process is to determine the end surface datum and the radial datum. Only when a good processing reference is found, the requirement of geometric tolerance of subsequent end face processing and round surface processing can be met. According to the processing method, the simple tool is designed, the positioning reference surface is processed based on the blade profile and the flow channel of the 3D printing multi-connected guide blade, and then the whole ring is removed, so that the processing method has great advantages in processing accuracy, processing economy and processing time cost.
Description
Technical Field
The invention relates to the technical field of blade machining, in particular to a machining method for a split type 3D printing turbine guide blade blank.
Background
The turbine guide blade of the modern aeroengine generally adopts a blade body non-allowance precision casting process to prepare a blank, and then the blank is finally formed through local machining. In the process of machining the blank, the blank is generally precisely positioned by establishing a reference through a six-point positioning method, namely, an unconstrained space object moves with 6 degrees of freedom. Every time a reference positioning point is introduced, a constraint is added, and the freedom degree of the object motion is reduced to zero by 6 positioning points, so that complete positioning is realized. The 6 reference target points were chosen on the theoretical profile of the geometric model. The application of the six-point localization method requires the design of a fixture to implement. When the fixture is designed, the positioning element (a ball bearing pin or a cylindrical pin) simulates the fixture to be in contact with a theoretical positioning point on the blank so as to realize accurate positioning of the blade blank. In the prior art, a complete set of complex positioning tool needs to be designed for processing the blade blank by a six-point positioning method, and the blade blank is processed by a single blade, so that the processing period is long, and the processing of the whole set of blade blank can be completed within 6-12 months generally.
In recent years, parts manufactured by 3D printing have been put into practical use in testing of aircraft engine parts. The main advantage is that the parts can be formed quickly. The traditional six-point positioning method is adopted to process the 3D printing turbine guide vane blank, the process is complex, the processing period is usually 6-12 months, and the principle that the 3D printing vane is rapidly manufactured and molded is not met.
In machining, the most important process is to determine the end surface datum and the radial datum. Only when a good processing reference is found, the requirement of geometric tolerance of subsequent end face processing and round surface processing can be met. Therefore, a machining process which is accurate and simple in machining tool and short in machining period is needed. The prior art scheme is usually used for machining the real blade of the engine, and the machining requirement and the machining precision are very high. The technical scheme is that the machining process method comprises the steps of machining a positioning datum plane based on the blade profile and the flow channel and then machining and forming through complete ring removing, wherein the machining period of the finished guide blade machined through the method is about 1 half month, which is less than 1/3 of the existing machining method, and the rapid fine machining of a 3D printing turbine guide blade blank can be realized.
Disclosure of Invention
The invention aims to provide a machining method for a split type 3D printing turbine guide vane blank, which aims to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme:
a method of machining a segmented 3D printed turbine guide vane blank, the method comprising: determining the end surface reference of a guide blade blank; determining a radial reference of the guide vane blank; and carrying out whole-ring material removing processing on the guide vane blank according to the determined end surface reference and radial reference of the guide vane blank.
Preferably, the step of determining the end face datum of the guide vane blank comprises: designing a half-moon-shaped equal-height stop block tool; connecting one side of the half-moon-shaped equal-height stop block tool with a standard block through a bolt, connecting the other side of the half-moon-shaped equal-height stop block tool with the blade-shaped tail edge of the guide blade blank through a bolt, and fixing the half-moon-shaped equal-height stop block tool on a linear cutting machine by using a compression nut and a screw; processing the end face C of the outer side of the upper edge plate of the guide vane blank; and (5) checking and determining that the end face C of the outer side end face of the upper edge plate of the guide blade blank meets the requirements so as to confirm that the end face machining reference meets the requirements.
Preferably, the standard block is rectangular; and the edge D of the standard block is parallel to the end surface C of the outer side 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-running wire cutting method.
Preferably, the step of determining the radial reference of the guide vane blank comprises: designing a disc type structure fixing tool; splicing a plurality of guide blade blanks into a whole ring, and preliminarily fixing the whole ring on the disc type structure fixing tool; the end surface of the upper edge plate of the guide blade blank is in pressing contact with the disc type structure fixing tool or is in small clearance fit with the disc type structure fixing tool; adjusting the radial positions of the multiple guide vane blanks spliced into the whole ring; and after checking and determining that the flow passage sizes and the circumferential runout of all the blade blanks in the flow passages meet the requirements, screwing bolts to fix the positions of the blade blanks so as to determine a radial machining reference.
Preferably, the disc type structure fixing tool comprises a plurality of bolt holes, a plurality of precise pin holes and a precise central hole; the bolt holes and the precise pin holes are uniformly distributed around the disc type structure fixing tool; the diameter size difference of two cylindrical surfaces at the precise pin hole is 1mm, and the precise pin hole has a forward mounting mode and a reverse mounting mode according to different mounting directions and is used for adjusting the radial position of the blade blank; the bolt hole is used for fixing the position of the blade blank; and the precise central hole is used for radial alignment of the blade blank and flow channel height measurement.
Preferably, the radial position of the multiple guide vane blanks which are adjusted to form the whole ring is adjusted through a positioning surface at the position with the largest radius of the guide vane blank, two precise pins and a feeler gauge.
Preferably, the method for adjusting the radial position of the multi-piece guide vane blank assembled into the whole ring according to the positioning surface where the radius of the guide vane blank is maximum, the two precision pins and the feeler gauge comprises the following steps:
after the disc type structure fixing tool is aligned in the radial direction on the machine tool, when the distance between the guide blade blank flow channel and the central hole of the disc type structure fixing tool accords with the designed radius size of the disc type structure fixing tool flow channel, the precision pin is assembled normally;
after the disc type structure fixing tool is aligned in the radial direction on the machine tool, when the distance between the guide blade blank flow channel and the center hole of the disc type structure fixing tool does not accord with the designed radius size of the flow channel of the disc type structure fixing tool, the precise pin is reversely installed, a 0.5mm gap is reserved, and then the precise pin is further finely adjusted through a clearance gauge.
Preferably, the step of performing a complete ring material removing process on the guide vane blank according to the determined end surface reference and radial reference of the guide vane blank includes: performing wax filling processing on the disc type structure fixing tool of the guide blade blank with the determined processing reference; 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 type structure fixing tool before the whole-ring material removing processing is performed.
Preferably, wax is poured into the disc type structure fixing tool for the guide blade blank with the determined machining reference, and it is required to ensure that each guide blade blank is sealed by the wax.
Preferably, the method is applied to a machining fixing tool for a guide blade blank, the fixing tool comprises a half-moon-shaped equal-height stop block tool and a disc type structure fixing tool, wherein,
the half-moon-shaped equal-height stop block tool is used for fixedly processing the end face of the guide blade blank;
the disc type structure fixing tool is used for fixing and processing the radial processing of the guide blade blank.
Preferably, the half-moon-shaped equal-height stop block tool is designed by taking the front edge or the tail 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 positioning and processing of the 3D printing guide blade flow channel.
The invention has the technical effects and advantages that:
compared with the best prior art, the technical scheme comprehensively considers the machining accuracy, the machining economy and the machining time cost of the blade blank.
1. Designing an equal-height 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 silk thread; adjusting the radial position of a blade blank by using a disc type fixing tool with a precise central hole through a precise pin and a clearance gauge, 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 blade finished product;
2. according to the technical scheme, a processing standard is obtained based on the blade profile and the flow channel, and the blade profile and the flow channel position of a finished blade can meet the requirements when the processing is carried out based on the processing standard;
3. the processing technology and the processing tool in the technical scheme are simple, and the whole ring is processed at one time, so that the processing cost of the blade blank can be greatly reduced;
4. the processing period from the process formulation to the processing of the finished guide vane is about 1 half and a half, which is less than 1/3 of the processing period required by the prior art, so that the processing time can be greatly shortened;
in conclusion, the invention provides a positioning reference surface processed based on the biological blade profile and the flow channel of the guide blade blank, which can ensure that the blade profile and the flow channel position of a finished blade product meet the requirements; and the machining of the material removing, machining and forming of the whole ring greatly reduces the machining cost of the blade blank. The processing technology and the processing tool in the scheme of the invention are simple, and meanwhile, the processing period from the technology formulation to the processing of the finished guide vane is about 1 half and a half, which is less than 1/3 of the processing period required by the prior art scheme. Although the machining precision of the guide vane is lower than that of the prior art, the guide vane machining method has obvious advantages in 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 a turbine part test. The method is already used for processing the 3D printing guide blade blank in the test of the gas turbine part of a certain type of engine, and the guide blade finished product processed by the technical scheme of the invention has good installation performance and usability and can be successfully applied to the test of the turbine part 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 will 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 structural view of a guide vane of the type having a bolted mounting edge;
FIG. 2 is a schematic view of a half-moon-shaped contour block;
FIG. 3 is a schematic view of installation of half-moon-shaped equal-height stoppers;
FIG. 4 is a schematic view of end face datum machining;
FIG. 5 is a schematic view of a disc type structure fixing tool;
FIG. 6 is a schematic view of a precision pin construction;
FIG. 7 is a schematic view of radial reference adjustment;
fig. 8 is a schematic view of a full ring process.
In the figure: 1. an upper edge plate; 2. a blade leading edge; 3. a trailing edge of the blade; 4. a lower flange plate; 5. bolt holes; 6. standard blocks; 7. an equal-height stop block; 8. a guide vane blank; 9. pressing a plate; 10. a compression nut; 11. a screw; 12. fixing a tool for a disc; 13. precision pins; 14. a hold-down bolt; 15. a guide vane blank; 16. an adjustment pad; 17. the flow passage surface.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention relates to a processing technique method which processes a positioning reference surface based on 3D printing multi-connected guide blade profile and a flow channel through designing a simple tool, processes a whole ring at one time, can greatly reduce the processing cost of a blade blank, and then removes the material of the whole ring for processing and forming, and processes based on the processing reference can ensure that the blade profile and the flow channel position of a blade finished product meet the requirements.
The prior art scheme is usually used for machining the real blade of the engine, and the machining requirement and the machining precision are very high. Although the technical scheme is not as good as the prior art in the aspect of machining precision, the method has obvious advantages in machining time and machining cost, can ensure higher machining precision, and is very suitable for rapid finish machining of 3D printing guide blades in turbine component tests. In machining, the most important process is to determine the end surface datum and the radial datum. Only when a good processing reference is found, the requirement of geometric tolerance of subsequent end face processing and round surface processing can be met.
Compared with the best prior art, the technical scheme of the invention comprehensively considers the machining accuracy, the machining economy and the machining time cost. The processing period from the process formulation to the processing of the finished guide vane product is about 1 half and a half, which is less than 1/3 of the processing period required by the prior art, and the processing time can be greatly shortened. The specific implementation scheme can be divided into: determining an end face reference of a guide blade blank, determining a radial reference of the guide blade blank, and performing whole-ring material removal processing on the guide blade blank according to the determined end face reference and radial reference of the guide blade blank, wherein the specific embodiment is as follows:
the invention is based on a guide vane blank with a bolt mounting edge as shown in fig. 1, and with reference to fig. 1, the guide vane blank comprises an upper edge plate, a vane front edge, a vane tail edge, a lower edge plate and bolt holes, wherein the bolt holes are positioned on the end surface of the upper edge plate, and the vane front edge and the vane tail edge form a vane positioned between the upper edge plate and the lower edge plate.
Further, according to the guide vane blank, the front edge or the tail edge of the vane profile of the 3D printed multi-gang guide vane is used as a reference surface, and an equal-height block tool shown in fig. 2 is designed and processed, wherein fig. 2a is a front view of the equal-height block tool, fig. 2b is a side view of the equal-height block tool, and is used for assisting in determining the end surface reference of the guide vane blank, and referring to fig. 2, the equal-height block in the present embodiment is a half-moon-shaped block with bolt holes on two sides.
Further, according to the mode shown in fig. 3, one side of the half-moon-shaped equal-height stop block tool is fixedly connected with the standard block through a bolt.
Further, as shown in fig. 4, fig. 4a is an end face reference processing front view, and fig. 5b is an end face reference processing side view, wherein one side of the meniscus-shaped equal-height stopper tool is connected to a standard block through a bolt, the other side of the meniscus-shaped equal-height stopper tool is connected to the blade-shaped trailing edge of the guide blade blank through a bolt, and the side parallel to the end face is selected.
Further, the standard block is rectangular; and the edge D of the standard block is parallel to the end surface C of the outer side of the upper edge plate of the guide vane blank.
Furthermore, the roughness of the end face C machined by slow wire cutting can reach Ra0.8, the flatness is within 0.02mm, and the good parallelism of the machined end face and the plane of the blade profile tail edge can be ensured through the tool. The end surface reference C can therefore be used for the subsequent end surface machining of the guide vane blank.
Further, the end face C after being cut and processed by the slow wire is checked by a jump dial indicator, and the jump value is less than 0.02 and meets the requirement.
After the end surface reference of the guide vane is determined, the radial reference of the guide vane is determined, and the method specifically comprises the following steps:
and processing and designing a disc type structure fixing tool according to the flow channel positioning of the 3D printing multi-connected guide blade.
Further, as shown in fig. 5, wherein fig. 5a is a front view of a 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 comprises a plurality of bolt holes, a plurality of precise pin holes and a precise central hole (phi 16). The bolt holes and the precise pin holes are uniformly distributed around the disc; the precise pin hole is used for adjusting the radial position of the guide vane blank; the bolt hole is used for fixing the position of the guide vane blank; the precise central hole (phi 16) is used for radial alignment and flow channel height measurement.
Furthermore, a plurality of guide blade blanks with determined end surface reference are spliced into a whole ring through bolts and are preliminarily fixed on the tool. The blank upper flange department terminal surface C keeps compressing tightly contact through bolt and disc and provides main support, makes blank lower flange department terminal surface and adjusting pad keep compressing tightly contact or little clearance fit through the adjustment bed height to provide supplementary support.
Furthermore, the radial positions of the guide vane blanks spliced into the whole ring are adjusted through a positioning surface at the position with the largest radius of the guide vane blank, two precise pins and a feeler gauge.
Furthermore, the radial position of the guide vane blank is adjusted through a flow passage surface of the guide vane blank and two precision pins, wherein the structure diagram of the precision pins is shown in figure 6, the diameter sizes of two cylindrical surfaces of the precision pins have a difference of 1mm, and the guide vane blank is positively installed or reversely installed according to different installation directions.
Further, after the disc type structure fixing tool is aligned in the radial direction on the machine tool, whether the size of the flow channel and the circumferential runout of all blade blanks in the flow channel of the disc type structure fixing tool meet the requirements or not is checked.
Further, if the radial position of the blank is not met, the radial position of the blank is adjusted according to the following method: referring to fig. 7, after the disc fixture a is aligned radially on the machine tool, when the distance between the blank runner surface and the disc center hole meets the design radius of the runner, the pin is assembled; otherwise, the pin is reversely installed. When the pin is reversely installed, 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 the feeler gauge until the size of the flow channel surface of the blade blank and the circumference jump meet the requirements, and then the bolt is screwed down to fix the position of the blade blank. The number of the blades in the circumferential direction is 7, the whole circle of blades meeting the requirements on the size of a flow channel and the circumferential runout can be obtained after 7 blade blanks are subjected to the adjusting operation, and the radial machining reference of the whole machining of the guide vane blank is determined by fixing the current position.
Further, after the flow passage sizes and the circumferential runout of all the blade blanks of the flow passage are checked and confirmed again to meet requirements, the bolts are screwed to fix the positions of the blade blanks, and thus the radial machining reference is determined.
In machining, the most important process is to determine the end surface datum and the radial datum. Only when a good processing reference is found, the requirement of geometric tolerance of subsequent end face processing and round surface processing can be met. In the embodiment, the end surface reference and the radial reference are determined based on the blade profile and the flow channel of the blade blank, and the blade profile and the flow channel of the finished blade can meet the requirements by processing based on the processing reference.
After the end face machining and radial machining reference is determined, the whole ring material removing machining can be performed, and as shown in fig. 8, a plurality of guide blade blanks are fixed in a disc tool through screw ring forming. The specific steps of the whole ring material removing processing are as follows:
and carrying out wax filling treatment on the disc type structure fixing tool of the guide blade blank with the determined processing reference, and confirming to ensure that each blade blank in the disc type tool is completely sealed by wax. Therefore, scrap iron in the machining 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 knife lines is reduced.
Further, after wax is poured and cured completely, common material removing processing is carried out on the guide blade blank on the disc type structure fixing tool.
Further, after the processing is finished, melting wax, and disassembling the compression bolt to obtain a single guide vane finished product.
In the embodiment, the whole ring is processed at one time, so that the processing cost of the blade blank is greatly reduced. Meanwhile, the processing period from the process formulation to the processing of the finished guide vane is about 1 half and a half, which is less than 1/3 of the processing period required by the prior technical scheme, and the processing time is also greatly shortened.
The prior art scheme is usually used for machining the real blade of the engine, and the machining requirement and the machining precision are very high. Although the technical scheme is not as good as the prior art in the aspect of machining precision, the method has obvious advantages in machining time and machining cost, can ensure higher machining precision, and is very suitable for rapid finish machining of 3D printing guide blades in turbine component tests.
The working principle and the 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 front edge or the tail edge of the blade profile is taken as a reference surface, an equal-height stop block tool is designed, and an end surface reference is machined through a slow silk thread machining process; designing a disc type fixing tool with a precise central hole by taking the blade-shaped flow passage as a reference, adjusting the radial position of a blade blank through a positioning surface at the minimum radius position of the guide blade blank, a precise pin and a clearance gauge, and determining a machining radial reference; and before the whole ring is machined, wax filling treatment is carried out, wax is melted after the machining is finished, and a pressing bolt is disassembled to obtain a single blade finished product. The processing technology and the processing tool in the technical scheme of the invention are simple, the whole ring is processed at one time, the processing cost of the blade blank can be greatly reduced, meanwhile, the processing period from the technology formulation to the processing of the finished guide blade is about 1 half and a half, which is less than 1/3 of the processing period required by the prior technical scheme, and the processing time is greatly shortened.
Finally, it should be noted that: 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 or portions thereof without departing from the spirit and scope of the invention.
Claims (14)
1. A machining method for a split 3D printing turbine guide vane blank, characterized in that the method comprises:
determining the end surface reference of a guide blade blank;
determining a radial reference of the guide vane blank;
and carrying out whole-ring material removing processing on the guide vane blank according to the determined end surface reference and radial reference of the guide vane blank.
2. The method of claim 1 wherein the step of determining the end face datum for the guide vane blank comprises:
designing a half-moon-shaped equal-height stop block tool;
connecting one side of the half-moon-shaped equal-height stop block tool with a standard block through a bolt, connecting the other side of the half-moon-shaped equal-height stop block tool with the blade-shaped tail edge of the guide blade blank through a bolt, and fixing the half-moon-shaped equal-height stop block tool on a linear cutting machine by using a compression nut and a screw;
processing the end face C of the outer side of the upper edge plate of the guide vane blank;
and (5) checking and determining that the end face C of the outer side end face of the upper edge plate of the guide blade blank meets the requirements so as to confirm that the end face machining reference meets the requirements.
3. The method of claim 2,
the standard block is rectangular;
and the edge D of the standard block is parallel to the end surface C of the outer side of the upper edge plate of the guide vane blank.
4. The method of claim 2,
and processing the outer end face C of the upper edge plate of the guide blade blank by a slow-speed 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 blade blanks into a whole ring, and preliminarily fixing the whole ring on the disc type structure fixing tool;
the end surface of the upper edge plate of the guide blade blank is in pressing contact with the disc type structure fixing tool or is in small clearance fit with the disc type structure fixing tool;
adjusting the radial positions of the multiple guide vane blanks spliced into the whole ring;
and after checking and determining that the flow passage sizes and the circumferential runout of all the blade blanks in the flow passages meet the requirements, screwing bolts to fix the positions of the blade blanks so as to determine a radial machining reference.
6. The method of claim 5, wherein the disc type structure fixing tool comprises a plurality of bolt holes, a plurality of precise pin holes and a precise central hole;
the bolt holes and the precise pin holes are uniformly distributed around the disc type structure fixing tool;
the diameter size difference of two cylindrical surfaces at the precise pin hole is 1mm, and the precise pin hole has a forward mounting mode and a reverse mounting mode according to different mounting directions and is used for adjusting the radial position of the blade blank;
the bolt hole is used for fixing the position of the blade blank;
and the precise central 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 plurality of guide vane blanks assembled into the complete ring is adjusted by the locating surface at which the radius of the guide vane blank is the largest, two precision pins and a feeler gauge.
8. The method of claim 7 wherein adjusting the radial position of the split multi-piece vane blank according to the positioning surface at which the vane blank radius is greatest, the two precision pins and the feeler comprises:
after the disc type structure fixing tool is aligned in the radial direction on the machine tool, when the distance between the guide blade blank flow channel and the central hole of the disc type structure fixing tool accords with the designed radius size of the disc type structure fixing tool flow channel, the precision pin is assembled normally;
after the disc type structure fixing tool is aligned in the radial direction on the machine tool, when the distance between the guide blade blank flow channel and the center hole of the disc type structure fixing tool does not accord with the designed radius size of the flow channel of the disc type structure fixing tool, the precise pin is reversely installed, a 0.5mm gap is reserved, and then the precise pin is further finely adjusted through a clearance gauge.
9. The method of claim 1, wherein the step of machining the guide vane blank with a full ring of material removed from the guide vane blank based on the determined end face datum and radial datum comprises:
performing wax filling processing on a disc type structure fixing tool of the guide blade blank with the determined processing reference;
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,
and the wax filling treatment is carried out on the disc type structure fixing tool before the whole ring material removing processing is carried out.
11. The method according to claim 9 or 10,
and (4) filling wax into the disc type structure fixing tool of the guide blade blank with the determined machining reference, wherein the wax is required to be ensured to seal each guide blade blank.
12. The method according to any one of claims 1 to 9, wherein the method is applied to a machining fixture for a guide vane blank, the fixture comprising a half-moon-shaped contour 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 blade blank;
the disc type structure fixing tool is used for fixing and processing the radial processing of the guide blade blank.
13. The method of claim 12,
the half-moon-shaped equal-height stop block tool is designed by taking the front edge or the tail edge of the blade profile as a reference surface according to the 3D printing guide blade.
14. The method of claim 12,
the disc type structure fixing tool is designed according to positioning and processing of the 3D printing guide blade flow channel.
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| CN114850799A (en) * | 2022-05-23 | 2022-08-05 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite turbine outer ring machining tool and machining method |
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| CN104070250A (en) * | 2014-07-09 | 2014-10-01 | 淮海工业集团有限公司 | Numerically-controlled machining electrode for densely-distributed closed blades |
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| CN114850799A (en) * | 2022-05-23 | 2022-08-05 | 西安鑫垚陶瓷复合材料有限公司 | Ceramic matrix composite turbine outer ring machining tool and machining method |
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| CN114367713B (en) | 2023-06-20 |
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