CN113806890B - Verification method for machining process of turbine disc parts - Google Patents
Verification method for machining process of turbine disc parts Download PDFInfo
- Publication number
- CN113806890B CN113806890B CN202111103820.XA CN202111103820A CN113806890B CN 113806890 B CN113806890 B CN 113806890B CN 202111103820 A CN202111103820 A CN 202111103820A CN 113806890 B CN113806890 B CN 113806890B
- Authority
- CN
- China
- Prior art keywords
- test
- machining
- processability
- simulation
- verification
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/17—Mechanical parametric or variational design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Theoretical Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- Computer Hardware Design (AREA)
- General Engineering & Computer Science (AREA)
- Pure & Applied Mathematics (AREA)
- Mathematical Optimization (AREA)
- Mathematical Analysis (AREA)
- Computational Mathematics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Milling Processes (AREA)
Abstract
The invention discloses a verification method of a turbine disc part machining process, which relates to the field of machining, solves the problem that an optimal machining scheme and machining parameters can be determined only by researching and optimizing a heat treatment mode, a machining process, a process route and a cutter used through a large number of physical tests, and reduces the test cost, and the specific scheme is as follows: the method comprises the following steps: performing a part material processability verification test, simulating the part processability, comparing processability simulation data with test data, and verifying feasibility of a part material processability simulation scheme; simulating the feature processability of the part, and verifying the feasibility of a feature processability simulation scheme through a test; and modeling is performed after the parts are simplified through the processing characteristic reconstruction, the processing process of the parts is simulated, and the processing technology of the parts is optimized according to the comparison of the simulation data of the processing process and the technical requirements.
Description
Technical Field
The invention relates to the field of machining, in particular to a verification method of a machining process of turbine disc parts.
Background
The statements herein merely provide background information related to the present disclosure and may not necessarily constitute prior art.
The turbine disc is an important part in an aeroengine, belongs to a large-scale typical thin-wall revolving body part, and has the advantages of thin thickness, poor rigidity and easy deformation.
Besides thin-wall characteristics, other more and complex machining characteristics including circular arcs, mortises, cavities and the like exist on the turbine disk, the inner cavity is large in size and poor in openness, the semi-finishing allowance is large, the structural size is large, the accessibility of a cutter is poor, and the machining deformation is serious; the internal cavity surface is more in transfer arc and difficult to process; the mortice type is complex, the position accuracy requirement is high, and the processing difficulty is great.
And the turbine disk is used as an important hot end part of the aeroengine, and high requirements are put on the material performance of the turbine disk. High temperature alloys with high yield strength, tensile strength and good thermal stability are generally selected to operate reliably and stably in high temperature environments. However, the machinability of the superalloy is very poor, the machining efficiency is low, and the machining quality is unstable.
In actual production, high requirements are put on the integrity of the machined surface of an important working part of the turbine disc part, but the whole structure of the turbine disc part is complex in shape and poor in rigidity, and deformation is very easy to occur in machining, so that the integrity of the machined surface is affected. Particularly for machining the narrow inner cavity surface of the turbine disc, a turning process is generally adopted in the industry at present, a forming cutter is designed for machining, and the cutting force is very large in the machining process, so that the part is deformed; vibration lines are easy to generate when the forming cutter turns and switches the circular arcs, so that the formed switching circular arcs have poor consistency, the circular arc sizes are unqualified and the like.
The inventor finds that in the prior art, in order to obtain the integrity of the machined surface meeting the requirement, a great number of repeated cutting tests are needed to study and optimize the heat treatment mode, the machining process, the process route, the used cutter and the like, determine the optimal machining scheme and machining parameters, and ensure the quality requirement of the product. However, the turbine disc belongs to large complex parts, the materials and the processing cost of the turbine disc are expensive, and the test of directly using a real turbine disc blank is unrealistic, so that the test cost is extremely high.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention aims to provide a verification method for the processing technology of the turbine disc parts, which can greatly save materials and processing cost for test, does not occupy machine tool equipment on production site, can be repeatedly used for testing the integrity of the processing surface of the typical characteristics in the turbine disc, greatly reduces test cost, is beneficial to increasing the number of samples for test, and can evaluate the integrity of the processing surface of the typical characteristics of the turbine disc more reliably.
In order to achieve the above object, the present invention is realized by the following technical scheme:
the invention provides a verification method of a turbine disc part machining process, which comprises the following steps:
performing a part material processability verification test, simulating the part processability, comparing processability simulation data with test data, and verifying feasibility of a part material processability simulation scheme;
simulating the feature processability of the part, and verifying the feasibility of a feature processability simulation scheme through a test;
and modeling is performed after the parts are simplified through the processing characteristic reconstruction, the processing process of the parts is simulated, and the processing technology of the parts is optimized according to the comparison of the simulation data of the processing process and the technical requirements.
As a further technical scheme, the part material processability verification test process comprises the following steps:
determining the type of a material processability verification test and an index for evaluating the surface integrity of a part; and constructing a test piece, and performing a material processability verification test.
As a further technical solution, the material workability verification test categories include turning tests, milling tests, drilling tests.
As a further technical scheme, in the process of material processability verification test, residual stress, work hardening and surface roughness values under different cutting amounts are measured through an orthogonal test, and the influence degree of the cutting amount on the residual stress, the work hardening and the surface roughness is obtained by adopting a range analysis method, so that the optimal cutting parameters are obtained.
As a further technical scheme, the process for simulating the feature processability of the part comprises the following steps:
and establishing a three-dimensional model for characteristic machining simulation, and simulating the three-dimensional model to obtain cutting force, cutting temperature, machined surface roughness, machined surface microhardness, machined surface layer tissue, machined surface residual stress, machined surface grain distribution and orientation, tool wear and service life in characteristic machining.
As a further technical scheme, the part characteristic machining test comprises a turning test and a milling test, wherein the part is clamped by a lathe clamp during the turning test, and the part is clamped by a 3R clamp during the milling test.
As a further technical scheme, the lathe fixture flange is provided with a plurality of flange through holes, and the middle part of the lathe fixture is provided with a cylinder structure.
As a further technical scheme, during milling test, the 3R clamp is connected with the dynamometer through the cushion block, and the cushion block is provided with a plurality of countersunk through holes.
As a further technical scheme, in the part feature processability test, the parts are subjected to pretreatment processing and simulation verification processing, and then the integrity of the processed surfaces of the parts is detected, so that test data are obtained and compared with the part feature processability simulation data.
As a further technical scheme, after the part machining process is simulated, simulation data of the part machining process are obtained, and if the simulation data are different from technical requirements, the machining process and the process parameters are optimized.
The beneficial effects of the invention are as follows:
(1) The verification method of the processing technology is respectively simulated from three hierarchical levels of material processing, feature processing and part processing, and the feasibility of a simulation scheme is verified, so that the processing technology of the part is optimized, and the physical test and simulation comprehensive mode is adopted for research, so that a large amount of materials and processing cost for the test are saved, and the test cost is reduced.
(2) In the material processability verification process, a large number of physical tests and a proper amount of simulation verification are carried out to obtain the processability and the processed surface integrity of the turbine disc material, and the simulation data are compared with the data obtained by the tests, so that the feasibility of a material processability simulation scheme is ensured.
(3) In the characteristic machining performance verification process, the machining performance and the machined surface integrity of typical characteristics in the turbine disc part are obtained through more simulation and a small amount of test verification, and the data obtained by the test are compared with simulation data, so that the feasibility of a characteristic machining performance simulation scheme is ensured.
(4) In the characteristic machining verification process, the corresponding clamp and the cushion block are designed, so that test pieces can be fixed on different equipment by utilizing the special clamp and the cushion block according to different characteristic machining requirements, and the test pieces with simplified machining characteristics can be tested by using general equipment without redesigning special equipment, thereby reducing test cost.
(5) In the verification process of the part processability, the simulation scheme for researching the comprehensive material processability and the characteristic processability is provided by combining and reconstructing the process and the characteristic, the simulation scheme for processing the actual turbine disc part is provided, simulation data are compared with the technical requirements of the actual turbine disc part, the feasibility of the part processability simulation scheme is ensured, the processing process of the turbine disc part is established by simulation in the follow-up actual production, and the processing surface integrity of the typical characteristic of the turbine disc can be reliably evaluated without carrying out a large number of physical tests.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention.
FIG. 1 is a schematic overall flow diagram of a method of verification of a turbine disc type part machining process in accordance with one or more embodiments of the present invention;
FIG. 2 is a schematic illustration of a material processability verification process according to one or more embodiments of the present invention;
FIG. 3 is a schematic view of the structure of a turning test piece log, a milling test piece log, a drilling test piece log according to one or more embodiments of the present invention;
FIG. 4 is a schematic illustration of a feature processability verification process in accordance with one or more embodiments of the invention;
FIG. 5 is a schematic diagram of a front view of a lathe fixture according to one or more embodiments of the present invention;
FIG. 6 is a schematic side view of a lathe fixture according to one or more embodiments of the present invention;
FIG. 7 is a schematic block diagram of a structure according to one or more embodiments of the present invention;
FIG. 8 is a schematic illustration of a part workability verification process in accordance with one or more embodiments of the present invention;
FIG. 9 is a schematic diagram of a turning test piece structure according to one or more embodiments of the present invention;
FIG. 10 is a schematic cross-sectional view of a turning test piece according to one or more embodiments of the present invention;
FIG. 11 is a schematic view of a milling test piece structure according to one or more embodiments of the present invention;
FIG. 12 is a schematic illustration of the structure of a turning test piece turned to semi-finished piece according to one or more embodiments of the present invention;
FIG. 13 is a schematic cross-sectional view of a turning test piece turned to a semi-finished piece according to one or more embodiments of the present invention;
FIG. 14 is a schematic view of a semi-finished part turned to a finished part according to one or more embodiments of the present invention;
FIG. 15 is a schematic cross-sectional view of a semi-finished article turned into a finished article according to one or more embodiments of the present invention;
in the figure: the mutual spacing or size is exaggerated for showing the positions of all parts, and the schematic drawings are used only for illustration;
1. turning a test piece raw material; 2. milling a test piece raw material; 3. drilling a test piece raw material; 4. a cushion block; 5. a sunk through hole with the diameter of 6 mm; 6. a phi 10mm countersunk through hole; 7. milling the test piece.
Detailed Description
It should be noted that the following detailed description is illustrative and is intended to provide further explanation of the invention. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
As described in the background art, in the prior art, a great number of physical tests are needed to study and optimize a heat treatment mode, a processing technology, a process route and a cutter used to determine an optimal processing scheme and processing parameters.
Example 1
In an exemplary embodiment of the present invention, as shown in fig. 1-15, a verification method for a machining process of a turbine disc type part is provided, including the following steps:
the verification method of the processing technology is divided into three levels of material processing verification, feature processing verification and part processing verification.
The first layer is material processing verification, the layer comprises a large number of physical tests and a proper amount of simulation verification, the processing performance and the processed surface integrity of the turbine disc material are researched, a simulation scheme for researching the material processing performance is established, feasibility of the simulation scheme is verified, and the performance evaluation indexes mainly comprise cutting force, cutting temperature and processed surface roughness, processed surface microhardness, processed surface layer tissues, processed surface residual stress, processed surface grain distribution and orientation, tool wear and service life and the like in the cutting process, and the whole flow is shown in figure 2.
In the first layer, test pieces for verifying the processability of materials are required to be designed, and the test pieces are used for turning, milling and drilling respectively.
The specific flow of the first layer is as follows:
s1-1: determining test types for verifying the influence of a turbine disc processing technology on the surface integrity of a material, and determining indexes for evaluating the surface integrity;
the processing technology comprises heat treatment, turning, milling, drilling and the like, and the surface integrity index is specifically determined according to different technologies and different quality requirements.
S1-2: and setting dynamic performance parameters of the turbine disc workpiece material, and establishing constitutive equations of the material.
S1-3: the test pieces for material processing technology research are respectively used for turning the test piece raw material 1, milling the test piece raw material 2 and drilling the test piece raw material 3, and are shown in fig. 3.
S1-4: performing heat treatment and machining orthogonal tests, wherein independent variables are process parameters of different processes, and dependent variables are indexes for evaluating surface integrity;
for example, when the turning performance of the turbine disk material is studied, a cylindrical rod with phi 60mm is selected as a test piece, the test piece is subjected to turning orthogonal test, the optimal parameters of the turbine disk material turned with different turning dosages are studied, more test data are obtained to be compared with simulation result data, the residual stress, the work hardening and the surface roughness of the machined surface are selected as evaluation indexes, three factors of the cutting speed v, the feeding amount f and the cutting depth ap are selected according to the turning characteristics, each factor corresponds to 3 levels, and the turning parameters and the corresponding levels are shown in table 1.
Table 1 turning parameters and corresponding levels
When the orthogonal test is carried out, the level of the orthogonal test factors is shown in table 2, the magnitudes of the residual stress, the work hardening and the surface roughness values under different cutting amounts are measured through the orthogonal test, the influence degree of the cutting amount on the residual stress, the work hardening and the surface roughness is explored by adopting a range analysis method, and the optimal cutting parameters are found.
TABLE 2 level of orthogonal test factors
S1-5: the machining performance of the turbine disc material is simulated, a three-dimensional model of a principle verification body is established in three-dimensional modeling software, the three-dimensional model is imported into finite element simulation software, boundary conditions and initial conditions are set, turning machining simulation is conducted on the turbine disc material, and data of residual stress, work hardening, surface roughness and the like of the machined surface are obtained.
S1-6: and comparing the evaluation index data obtained by simulation with the data obtained by the test, and verifying the feasibility of the simulation scheme of the processing performance of the turbine disc material.
In the first layer, the cutting machining principle is researched through simulation and the feasibility of a simulation scheme is verified, so that the test data of the machining property of the turbine disc material is obtained, the reliability of the test data is ensured, and the materials and the machining cost of the test are saved.
The second level in this embodiment is feature machinability verification because complex parts are composed of various machined features, and needs to be studied for different machined features, including more simulation simulations with a small number of test verifications, researching the machinability and machined surface integrity of typical features in turbine disk parts, and verifying the feasibility of feature machinability simulation schemes.
Wherein, typical characteristics include internal cavity characteristic turning, transitional arc characteristic turning, thin-wall characteristic turning, groove characteristic milling and the like, and performance evaluation indexes also comprise cutting force, cutting temperature, machined surface roughness, machined surface microhardness, machined surface layer tissues, machined surface residual stress, machined surface grain distribution and orientation, tool wear and service life and the like in the machining process, and the whole flow is shown in fig. 4.
The specific flow of the second layer is as follows:
s2-1: and establishing a three-dimensional model for characteristic machining simulation in three-dimensional modeling software, wherein the three-dimensional model comprises a thin-wall characteristic turning model, a switching arc characteristic turning model, an internal cavity characteristic turning model, a slot characteristic milling model and the like.
S2-2: the three-dimensional model is imported into finite element simulation software, a material constitutive model, boundary conditions, initial conditions, contact conditions and the like are set, and typical feature turning and milling processability in S2-1 is simulated, so that data such as cutting force, cutting temperature and processed surface roughness, processed surface microhardness, processed surface layer tissue, processed surface residual stress, processed surface grain distribution and orientation, cutter abrasion and service life and the like in feature processing are obtained.
S2-3: a test piece for verifying a characteristic machining simulation scheme is prepared, wherein the test piece comprises typical characteristics of an inner cavity, a switching arc, a thin wall, a groove and the like, the typical characteristics are simplified from characteristics of actual turbine disc parts, and the test piece is made of turbine disc materials.
The test piece in the hierarchy is formed by simplifying the processing characteristics of the actual turbine disk part, and the test piece needs to be specially designed and correspondingly needs to be designed and manufactured to be tested by a special fixture.
For turning test, a fixture shown in figures 5-6 is designed to clamp a feature machining turning test piece, wherein the flange of the lathe fixture is provided with six flange through holes, the six flange through holes are in one-to-one correspondence with the countersunk holes of the flange of the turning test piece, the positioning surface is a large end surface, and the fixture comprises a triangular chuck clamping part of the lathe with the length of 50mm and the diameter phi of 50 mm.
For milling test, a 3R clamp is used for clamping a characteristic machining milling test piece, and the clamp is required to be fixed on a dynamometer due to the fact that the cutting force in the milling process is required to be measured, so that a cushion block 4 for connecting the clamp and the dynamometer is designed and manufactured, as shown in fig. 7, two sides of the cushion block are provided with phi 6mm countersunk through holes 5 which are symmetrical left and right and are uniformly distributed in an arrayed mode, positioning and fixing are carried out through hinging inner hexagon bolts and the dynamometer, four phi 6mm countersunk through holes 5 which are uniformly distributed in the circumference are arranged on the bottom surface of the cushion block, and a phi 10mm countersunk through hole 6 is formed in the center of the circumference and is positioned and fixed through hinging the inner hexagon bolts and the clamp.
In this embodiment, taking the characteristics of the cavity, the switching arc and the thin wall in the turbine disc as examples, a turning test piece shown in fig. 9-10 is constructed to carry out turning test.
Wherein, turning test piece includes following characteristics:
(1) The turning test piece is forged into a blank by using a die forging process, and the workpiece material is turbine disc material.
(2) The turning test piece contained six flange countersinks at the flange with a bore diameter of phi 6.6mm, through which the test piece was secured to a custom made special lathe fixture, shown in figures 5-6, using a phi 6mm hinged socket head cap screw.
(3) The turning test piece comprises an phi 60mm inner cylinder at the center, which is cut by wire-cut electric discharge machining, and the cut phi 60mm outer cylinder can be recycled for other turning tests.
Also, taking the turbine disk slot milling feature as an example, a milling test piece 7 as shown in fig. 11 was constructed to perform a milling test.
Wherein, milling test piece includes following characteristics:
(1) In order to study the influence of the first-level process on the second-level process, the integrity of the processed surfaces of the first level and the second level is conveniently compared, and enough sampling length is required to be reserved, so that the thickness of the milling test piece is required to be greater than or equal to 15mm.
(2) The milling test piece needs to reserve enough clamp clamping length to reduce the processing deformation of the test piece and reduce the processing vibration.
(3) Most of the remaining part of the milling test piece was removed by means of a wire-cut electric discharge machine.
S2-4: and performing verification tests of feature processability simulation results, including turning tests, milling tests and the like, wherein the verification tests comprise pretreatment processing and simulation verification processing.
Taking the characteristic of turning the inner cavity of the turbine disc as an example, the pretreatment processing refers to rough machining and semi-finishing of the inner cavity surface, and turning the turning test piece in S2-3 to the size of the semi-finished piece after rough machining and semi-finishing, as shown in fig. 12-13.
The semi-finishing turning parameters are determined according to the requirements of a process card or a simulation scheme, simulation verification processing refers to finishing of an inner cavity surface, and a semi-finishing piece is turned to the size of the finishing piece, as shown in fig. 14-15; the finish turning parameters are determined according to the process card and the simulation parameters, and the control simulation is identical to the process parameters of the verification test so as to verify the feasibility of the feature machining simulation scheme.
And detecting the integrity of the finished machined surface to obtain test data, wherein the indexes comprise cutting force, cutting temperature, machined surface roughness, machined surface microhardness, machined surface layer structure, machined surface residual stress, machined surface grain distribution and orientation, cutter abrasion, service life and the like in the machining process.
S2-5: and comparing the data obtained by the test with the evaluation index data obtained by the simulation, and verifying the feasibility of the simulation scheme of the typical characteristic machining performance of the turbine disk.
In the second level, the influence of the typical characteristics of the turbine disc part on the machined surface integrity is researched by combining simulation and test, a simulation scheme for researching the characteristic machining property is formulated, and the feasibility of the characteristic machining simulation scheme is verified by test, so that the machining surface integrity test of the typical characteristics in the turbine disc can be repeated, the test cost is greatly reduced, the number of samples of the test is increased, and the machining surface integrity of the typical characteristics of the turbine disc can be evaluated more reliably.
The third layer is the actual part processability simulation, and the third layer is mainly used for carrying out simulation research on the processability and the processed surface integrity of the actual turbine disk part so as to achieve the purposes of saving cost and predicting in advance.
In the first level and the second level, a simulation scheme of the machining performance of the turbine disk material and a simulation scheme of the machining performance of typical characteristics of the turbine disk have been researched, feasibility verification is carried out, in the third level, the simulation schemes of the first level and the second level are combined, a simulation scheme of the machining of an actual turbine disk part is provided through process and characteristic combination reconstruction, the flow of the research scheme is shown in fig. 8, and the machining process of the turbine disk part is preferably established through simulation.
The specific flow of the third-level research scheme is as follows:
s3-1: and establishing a three-dimensional model simplified by the actual turbine disc part through processing characteristic reconstruction in three-dimensional modeling software.
S3-2: the three-dimensional model is imported into finite element simulation software, a constitutive model, boundary conditions, initial conditions, contact conditions and the like are set, simulation is carried out on the machining process of the turbine disk, required result data are obtained, and the result data are compared with technical requirements, so that the aim of optimizing the machining process is achieved.
In the third level, a simulation scheme verified by material processability and feature processability is used for simulating an actual part simplified model, so that cutting force, cutting temperature, processed surface roughness, processed surface microhardness, processed surface layer tissues, processed surface residual stress, processed surface grain distribution and orientation, cutter abrasion, service life and other data in the processing of the turbine disc part are obtained, the data are compared with technical requirements, the optimization of a processing technology is realized, a large number of repeated cutting tests are not needed, and the test cost is reduced.
It will be appreciated that the specifications are for the design parameters of the turbine disk in actual production.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
1. The verification method of the processing technology of the turbine disc parts is characterized by comprising the following steps of:
performing a part material processability verification test, simulating the part processability, comparing processability simulation data with test data, and verifying feasibility of a part material processability simulation scheme;
the part material processability verification test process is as follows:
determining the type of a material processability verification test and an index for evaluating the surface integrity of a part; constructing a test piece, and performing a material processability verification test;
in the material processing verification test process, the magnitudes of residual stress, work hardening and surface roughness values under different cutting dosages are measured through an orthogonal test, and the influence degree of the cutting dosages on the residual stress, the work hardening and the surface roughness is obtained by adopting a range analysis method, so that the optimal cutting parameters are obtained;
simulating feature processability of the part, and verifying the feature processability simulation through experiments
Feasibility of the scheme;
the process for simulating the feature processability of the part comprises the following steps:
establishing a three-dimensional model for characteristic machining simulation, and simulating the three-dimensional model to obtain cutting force, cutting temperature, machined surface roughness, machined surface microhardness, machined surface layer tissue, machined surface residual stress, machined surface grain distribution and orientation, tool wear and service life in characteristic machining;
simplifying the part through processing characteristic reconstruction, modeling, simulating the processing process of the part, and optimizing the processing technology of the part according to the comparison of the simulation data of the processing process and the technical requirements;
in the machining test, the parts are subjected to pretreatment machining and simulation verification machining, the integrity of the machined surfaces of the parts is detected, test data are obtained, and the test data are compared with the machining simulation data of the features of the parts.
2. The method of verifying a machining process for a turbine disc type part according to claim 1, wherein the material workability verification test type includes a turning test, a milling test, and a drilling test.
3. The method of verifying a machining process for a turbine disc type part according to claim 1, wherein the part characteristic workability test includes a turning test in which the part is clamped by a lathe jig and a milling test in which the part is clamped by a 3R jig.
4. The method for verifying a machining process of a turbine disc type part according to claim 3, wherein the lathe fixture flange is provided with a plurality of flange through holes, and a cylinder structure is arranged in the middle of the lathe fixture.
5. A method of verifying a turbine disc type part machining process according to claim 3, wherein the 3R clamp is connected to the load cell via a spacer block in a milling test, the spacer block having a plurality of countersunk through holes.
6. The method for verifying a machining process of a turbine disc type part according to claim 1, wherein simulation data of the machining process of the part is obtained after the machining process of the part is simulated, and if the simulation data is different from technical requirements, the machining process and the process parameters are optimized.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111103820.XA CN113806890B (en) | 2021-09-18 | 2021-09-18 | Verification method for machining process of turbine disc parts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111103820.XA CN113806890B (en) | 2021-09-18 | 2021-09-18 | Verification method for machining process of turbine disc parts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113806890A CN113806890A (en) | 2021-12-17 |
| CN113806890B true CN113806890B (en) | 2023-07-14 |
Family
ID=78896047
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111103820.XA Active CN113806890B (en) | 2021-09-18 | 2021-09-18 | Verification method for machining process of turbine disc parts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113806890B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115310213B (en) * | 2022-10-12 | 2023-01-17 | 玛斯特轻量化科技(天津)有限公司 | Method and device for simulation verification of part connection accessibility |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7933679B1 (en) * | 2007-10-23 | 2011-04-26 | Cessna Aircraft Company | Method for analyzing and optimizing a machining process |
| CN102819651A (en) * | 2012-08-20 | 2012-12-12 | 西北工业大学 | Simulation-based parameter optimizing method for precise casting process of single crystal turbine blade |
| CN103500252A (en) * | 2013-09-26 | 2014-01-08 | 西安工业大学 | Thin-walled workpiece cutting condition optimization machining method based on finite element analysis |
| CN109614748A (en) * | 2018-12-28 | 2019-04-12 | 上海理工大学 | Binding test and emulation technology promote the structural optimization method of machine dynamic characteristics |
| CN110083967A (en) * | 2019-05-07 | 2019-08-02 | 湖北工业大学 | A kind of sbrasive belt grinding process parameter optimizing and evaluation index mathematical model modeling method |
-
2021
- 2021-09-18 CN CN202111103820.XA patent/CN113806890B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7933679B1 (en) * | 2007-10-23 | 2011-04-26 | Cessna Aircraft Company | Method for analyzing and optimizing a machining process |
| CN102819651A (en) * | 2012-08-20 | 2012-12-12 | 西北工业大学 | Simulation-based parameter optimizing method for precise casting process of single crystal turbine blade |
| CN103500252A (en) * | 2013-09-26 | 2014-01-08 | 西安工业大学 | Thin-walled workpiece cutting condition optimization machining method based on finite element analysis |
| CN109614748A (en) * | 2018-12-28 | 2019-04-12 | 上海理工大学 | Binding test and emulation technology promote the structural optimization method of machine dynamic characteristics |
| CN110083967A (en) * | 2019-05-07 | 2019-08-02 | 湖北工业大学 | A kind of sbrasive belt grinding process parameter optimizing and evaluation index mathematical model modeling method |
Non-Patent Citations (2)
| Title |
|---|
| 薄壁件加工变形仿真及工艺参数优选;张春燕;许丰;程德俊;陈慧;;组合机床与自动化加工技术(06);全文 * |
| 铣削加工仿真及工艺参数优化;盘家俊;罗樟圳;文章;尹婷婷;王兵;;现代制造技术与装备(05);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113806890A (en) | 2021-12-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105171158B (en) | A kind of turborotor taper air film hole processing technology | |
| CN101659012B (en) | Method for processing container glass mold | |
| CN105252342B (en) | Detect the detection test specimen and detection method of five-axle number control machine tool Machining of Curved Surface ability | |
| CN102319989B (en) | Manufacturing method of airplane horizontal tail beam edge strip | |
| CN102941447A (en) | Manufacture machining process of bolt | |
| CN113806890B (en) | Verification method for machining process of turbine disc parts | |
| Wang et al. | Improving the machining accuracy of thin-walled parts by online measuring and allowance compensation | |
| CN110936108B (en) | Machining method for improving assembly precision of thin-wall annular casing type parts | |
| Costa et al. | Development of hydraulic clamping tools for the machining of complex shape mechanical components | |
| CN112792569A (en) | Piston cylinder shell turning and milling combined machining clamp | |
| CN205111323U (en) | A anchor clamps that is used for turbine guide blade toper air film spot facing work | |
| CN106493503A (en) | A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity | |
| Boivie et al. | Development of a hybrid manufacturing cell; integration of additive manufacturing with CNC machining | |
| Beňo et al. | Operation safety and performance of milling cutters with shank style holders of tool inserts | |
| CN112355576B (en) | Machining method for high-precision wing-shaped elastic shaft part | |
| CN111103082B (en) | Method for improving precision of measuring three-dimensional residual stress by deep hole method | |
| CN103381555B (en) | A kind of Square tool for complicated Machining of Shaft-type Parts | |
| CN202752879U (en) | Sliding valve tool of double screw rod compressor | |
| Yang et al. | Research on straightness error detection and quality control of multi-crankshaft bores for large medium speed engine block | |
| CN112571091A (en) | Tool position refitting method of economical numerical control lathe | |
| CN112222482A (en) | Special machining clamp for crank parts | |
| Yang et al. | A novel method of experimental evaluation on BTA tool geometries | |
| CN110936185A (en) | Complicated structural part clamp | |
| Cui et al. | Optimization of cutting conditions in hard milling with the performance of cemented carbide tool material considered | |
| CN216576631U (en) | Finish machining tool for large stainless steel sheet annular part |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |