CN116460343A - Processing method of aero-engine blade - Google Patents

Processing method of aero-engine blade Download PDF

Info

Publication number
CN116460343A
CN116460343A CN202310633988.4A CN202310633988A CN116460343A CN 116460343 A CN116460343 A CN 116460343A CN 202310633988 A CN202310633988 A CN 202310633988A CN 116460343 A CN116460343 A CN 116460343A
Authority
CN
China
Prior art keywords
blade
workpiece
clamping
base
rotating disc
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.)
Pending
Application number
CN202310633988.4A
Other languages
Chinese (zh)
Inventor
张振
张恒溥
王卓然
包自然
倪敬
李祖吉
方明川
陈俊瑜
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hangzhou Dianzi University
Original Assignee
Hangzhou Dianzi University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Hangzhou Dianzi University filed Critical Hangzhou Dianzi University
Priority to CN202310633988.4A priority Critical patent/CN116460343A/en
Publication of CN116460343A publication Critical patent/CN116460343A/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23C—MILLING
    • B23C3/00—Milling particular work; Special milling operations; Machines therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23C—MILLING
    • B23C9/00—Details or accessories so far as specially adapted to milling machines or cutter
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
    • B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
    • B23Q3/06—Work-clamping means
    • B23Q3/062—Work-clamping means adapted for holding workpieces having a special form or being made from a special material
    • B23Q3/063—Work-clamping means adapted for holding workpieces having a special form or being made from a special material for holding turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q7/00—Arrangements for handling work specially combined with or arranged in, or specially adapted for use in connection with, machine tools, e.g. for conveying, loading, positioning, discharging, sorting
    • B23Q7/02—Arrangements for handling work specially combined with or arranged in, or specially adapted for use in connection with, machine tools, e.g. for conveying, loading, positioning, discharging, sorting by means of drums or rotating tables or discs

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Jigs For Machine Tools (AREA)

Abstract

The invention discloses a processing method of an aeroengine blade. The clamping component and the limiting component are arranged at intervals; the limiting assembly comprises a limiting base and a thimble, and the limiting base is connected to the bottom plate in a sliding manner; the thimble is installed on spacing base. The clamping assembly comprises a supporting base, a rotating disc, a clamping fixing piece and a driving element. The support base is fixedly connected to the bottom plate. The rotating disc is rotatably arranged on the supporting base, and the axial center of the rotating disc coincides with the axial center of the thimble. The clamping fixing piece is fixedly connected to the rotating disc; the driving element is arranged on the supporting base; the driving element is used for driving the processed blade to rotate; according to the invention, different machining programs are adopted for the machined blade under the allowance, so that the machined blade can finish machining all blade surfaces and dead angles on the premise of no need of clamping again.

Description

Processing method of aero-engine blade
Technical Field
The invention belongs to the technical field of aero-engine blade processing, and particularly relates to a processing method of an aero-engine blade.
Background
The novel engine blade brings new problems to the processing technology while improving the engine performance. The blade profile position degree, the mounting angle, the blade crown saw teeth and other dimensions are mutually related in the machining process, the precision is high, and the blade profile is difficult to be completely qualified. The important factors are difficult precise positioning, and accumulated errors after multiple conversions from blank to machining are over the accuracy requirement of the blade, which become key factors for restricting the quality and qualification rate of the product at present.
The existing turbine working blade processing method comprises the following steps: firstly, an upper edge plate and a lower edge plate of a blade are machined, firstly, blank blade profile references are converted onto machining edge plates, and secondly, the upper edge plate and the lower edge plate which are convenient to position are machined, so that final part reference (assembly reference) tenon and tenon teeth are convenient to clamp and further process. And positioning and re-machining the bevel size of the lower edge plate and the blade crown saw teeth by the machined tenon teeth to finish the final blade profile position size and the blade crown size of the part. The method for processing the marginal plate uses four theoretical points of the selected blank blade body as measuring points, and the upper and lower marginal plate surfaces are ground and compared with a special measuring tool and a standard component to obtain four measuring point values. The method has complicated working procedures and low efficiency; the blank and the machining reference are not unified, blade measurement, calculation and adjustment are required one by one, and the precision is low; the accumulated error is large due to the fact that the standard needs to be converted twice, and the dimension is easy to exceed the tolerance after machining.
Disclosure of Invention
The invention aims to provide a processing method of an aeroengine blade.
The invention relates to a processing method of an aeroengine blade, which adopts a clamp comprising a bottom plate, and a clamping assembly and a limiting assembly which are arranged on the bottom plate; the clamping component and the limiting component are arranged at intervals; the limiting assembly comprises a limiting base and a thimble, and the limiting base is connected to the bottom plate in a sliding manner; the thimble is installed on spacing base.
The clamping assembly comprises a supporting base, a rotating disc, a clamping fixing piece and a driving element; the supporting base is fixed on the bottom plate; the rotating disc is rotationally connected to the supporting base, and the axial center of the rotating disc coincides with the axial center of the thimble; the clamping fixing piece is fixedly connected to the rotating disc; the driving element is arranged on the supporting base; the driving element is used for driving the rotating disc to rotate.
The processing method of the aero-engine blade comprises the following steps:
step one, processing a processed workpiece; the workpiece comprises a positioning part, a blade part and a clamping part which are connected in sequence. The positioning part is provided with a groove matched with the thimble. The blade part is in a cuboid shape. The workpiece is arranged between the clamping base and the limiting base, and the ejector pin is used for positioning the positioning part of the basic workpiece; the clamping fixture clamps the clamping portion of the base workpiece.
And step two, the driving element drives the workpiece to rotate to a state that the side surface of the blade part is vertical.
And thirdly, carrying out reciprocating processing along the upward edge of the blade part of the workpiece by using a rough milling cutter, so that the shape of the upward edge of the blade part of the workpiece gradually approaches to the shape of the edge of the aero-engine blade.
And step four, stopping the workpiece after the driving element drives the workpiece to rotate 180 degrees, and repeating the step three.
And fifthly, the driving element drives the workpiece to rotate to a state that the side surface of the blade part is horizontal.
And step six, using a rough milling cutter to carry out reciprocating processing on the upward side surface of the blade part of the workpiece, so that the shape of the upward side surface of the blade part of the workpiece gradually approaches to the blade surface shape of the aero-engine blade.
And step seven, the driving element drives the processed blade to rotate 180 degrees and then stops, and the step six is repeated.
Step eight, the driving element drives the processed blade to continuously rotate; meanwhile, the machining center sequentially adopts a rough milling cutter, a semi-finish milling cutter and a finish milling cutter to mill the blade part of the rotating workpiece, so that the blade part of the workpiece is machined into the shape of an aeroengine blade.
And step nine, removing the workpiece from the clamp, and cutting and removing the locating part and the clamping part on the workpiece to obtain the machined aeroengine blade.
Preferably, the limiting assembly further comprises a first bolt; the limiting base is provided with a second threaded hole; the first bolt is arranged in the first threaded hole; the first bolt can prop against the bottom plate, and the position of the limiting base is locked.
Preferably, the limiting assembly further comprises a connecting piece; the connecting piece is fixedly connected to one side, opposite to the clamping base, of the limiting base; the thimble is connected to the connecting piece in a rotating way.
Preferably, the support base is provided with a rotating groove; the rotating disc and the rotating groove form a rotating pair.
Preferably, the driving element adopts a motor; the output shaft of motor runs through the support base, with rolling disc fixed connection.
Preferably, the fixed connecting piece comprises a supporting rod and two clamping pieces; the supporting rod is fixedly connected with the rotating disc, and the central point of the supporting rod is positioned on the central axis of the rotating disc; the two clamping pieces are symmetrically arranged on the supporting rod.
Preferably, during the machining process, the clamping part of the workpiece is positioned between the two clamping pieces; the bolt screwed on the clamping piece is propped against the clamping part of the workpiece.
Preferably, the rough milling cutter is of the model D8R1; the semi-finish milling cutter adopts a ball end milling cutter with the model of B6; the finish milling cutter adopts a ball end milling cutter with the model of B6J.
The invention has the beneficial effects that:
1. according to the invention, the clamping assembly is arranged, so that the blade to be processed is clamped and rotated by the clamping assembly; the process of machining each surface of the machined blade does not need to be clamped for many times; the blade to be processed is avoided in the process of clamping for many times; a horizontal or vertical offset is generated on the determined coordinate axes, so that the blade after the machining is finished has serious quality problems.
2. According to the invention, the motor is arranged, and the motor output shaft drives the processed blade to rotate in cooperation with the milling cutter of the processing center; so that the processed blade is continuously replaced relative to the surface of the milling cutter; the milling dead angle of the milling cutter is avoided, and meanwhile, the processing distance required to travel by the milling cutter is reduced.
Drawings
Fig. 1 is a schematic diagram of the overall structure of the present invention.
Fig. 2 is a top view of the present invention.
FIG. 3 is a schematic view of a thimble according to the present invention.
FIG. 4 is a schematic diagram of a blade processed according to the present invention, before and after processing.
Wherein: 1. a bottom plate; 2. a limit base; 3. clamping the fixing piece; 4. a thimble; 5. a support base; 6. a rotating disc; 7. a positioning part; 8. a blade portion; 9. and a clamping part.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, 2 and 3, a machining fixture for an aircraft engine blade comprises a base plate 1, and a clamping assembly and a limiting assembly mounted on the base plate 1. The clamping component and the limiting component are arranged at intervals. The limiting assembly comprises a limiting base 2, a first bolt, a connecting piece and a thimble 4. The limiting base 2 is arranged on the bottom plate 1 in a sliding manner. The limiting base 2 is provided with a second threaded hole; the first bolt is installed in the first threaded hole. When the limiting assembly slides to a required position, the first bolt is rotated, so that the position between the limiting base 2 and the bottom plate 1 is fixed. The connecting piece fixed connection is just to clamping assembly's one side at spacing base 2. The thimble 4 is fixedly connected to the connecting piece. Before machining the machined blade, machining a groove on one side of the machined blade. Through this recess, the ejector pin 4 positions the blade to be machined.
As shown in fig. 1 and 2, the clamping assembly includes a support base 5, a rotating disc 6, a clamping fixture 3, and a motor. The supporting base 5 is fixedly connected to the bottom plate 1. A rotating groove is formed in one side surface, opposite to the limiting component, of the supporting base 5; the rotating disk 6 and the rotating groove form a rotating pair. The central axis of the rotating disc 6 coincides with the central axis of the thimble 4. The motor is fixedly connected to one side surface of the supporting base 5, which is away from the limiting component; and the output shaft of the motor penetrates through the supporting base 5 and is fixedly connected with the rotating disc 6. The output shaft of the motor is arranged coaxially with the central axis of the rotating disc 6.
The clamping fixture 3 is mounted on a rotating disc 6. The fixed connecting piece comprises a supporting rod and two clamping pieces. The supporting rod is fixedly connected with the rotating disc 6, and the central point of the supporting rod is positioned on the central axis of the rotating disc 6. The two clamping pieces are L-shaped and symmetrically fixed on the supporting rod, and a clamping groove is formed between the two clamping pieces. The two clamping pieces are provided with first threaded holes. The two clamping pieces are used for supporting one side, away from the limiting assembly, of the processed blade; and the processed blade is fixed by installing a compression bolt in the first threaded hole.
As shown in fig. 4, a method for machining an aero-engine blade using the aforementioned machining jig includes the steps of:
step one, processing a processed workpiece; the workpiece comprises a positioning part 7, a blade part 8 and a clamping part 9 which are connected in sequence. The positioning part is provided with a groove matched with the thimble. The blade part is in a cuboid shape, and six surfaces of the blade part are respectively two side surfaces (two surfaces with the largest area), two end surfaces (surfaces connected with the positioning part and the clamping part) and two edge surfaces (corresponding to two side edges of the blade). Installing a workpiece between the clamping assembly and the limiting assembly; the clamping fixture 3 clamps a clamping portion 9 at one end of the workpiece. The thimble 4 butts against a groove on the positioning part 7 at the other end of the workpiece, thereby realizing the positioning and supporting of the other end of the workpiece.
And step two, rotating the workpiece to a state with the side face vertical through a motor.
And thirdly, carrying out reciprocating processing along the upward edge of the blade part 8 of the workpiece by using a D8R1 type milling cutter, so that the shape of the upward edge of the blade part 8 of the workpiece gradually approaches to the shape of the edge of the blade of the aeroengine.
And step four, stopping the workpiece after the motor drives the workpiece to rotate 180 degrees, and repeating the step three.
And fifthly, the driving element drives the workpiece to rotate to a state that the side surface of the blade part 8 is horizontal.
And step six, using a milling cutter of the D8R1 model to carry out reciprocating processing on the upward side surface of the blade part 8 of the workpiece, so that the shape of the upward side surface of the blade part 8 of the workpiece gradually approaches to the blade surface shape of the aero-engine blade.
And step seven, stopping the workpiece after the motor drives the workpiece to rotate 180 degrees, and repeating the step six.
And step eight, driving the workpiece to continuously rotate by the motor at the speed of 0.5 r/min. Meanwhile, the machining center sequentially adopts a D8R1 type milling cutter, a B6 type ball end milling cutter and a B6J type ball end milling cutter to sequentially perform rough milling, semi-finish milling and finish milling on the surface of the workpiece, so that the blade part 8 of the workpiece is processed into the shape of an aeroengine blade.
And step nine, removing the workpiece from the clamp, and cutting and removing the locating part and the clamping part on the workpiece to obtain the machined aeroengine blade.

Claims (8)

1. A processing method of an aeroengine blade is characterized by comprising the following steps of: the clamp adopted by the processing method comprises a bottom plate (1), a clamping assembly and a limiting assembly, wherein the clamping assembly and the limiting assembly are arranged on the bottom plate (1); the clamping component and the limiting component are arranged at intervals; the limiting assembly comprises a limiting base (2) and a thimble (4), and the limiting base (2) is connected to the bottom plate (1) in a sliding manner; the thimble (4) is arranged on the limit base (2);
the clamping assembly comprises a supporting base (5), a rotating disc (6), a clamping fixing piece (3) and a driving element; the supporting base (5) is fixed on the bottom plate (1); the rotating disc (6) is rotationally connected to the supporting base (5), and the axial center of the rotating disc (6) coincides with the axial center of the thimble (4); the clamping fixing piece (3) is fixedly connected to the rotating disc (6); the driving element is arranged on the supporting base; the driving element is used for driving the rotating disc (6) to rotate;
the processing method of the aero-engine blade comprises the following steps:
step one, processing a processed workpiece; the workpiece comprises a positioning part, a blade part and a clamping part which are connected in sequence; the positioning part is provided with a groove matched with the thimble; the blade part is in a cuboid shape; the workpiece is arranged between the clamping base and the limiting base (2), and the thimble (4) is used for providing positioning for the positioning part of the basic workpiece; a clamping part for clamping the basic workpiece by the clamping fixing piece (3);
step two, the driving element drives the workpiece to rotate to a state that the side surface of the blade part is vertical;
performing reciprocating processing along the upward edge of the blade part of the workpiece by using a rough milling cutter, so that the shape of the upward edge of the blade part of the workpiece gradually approaches to the shape of the edge of the aero-engine blade;
step four, the driving element drives the workpiece to rotate 180 degrees and then stops, and the step three is repeated;
step five, the driving element drives the workpiece to rotate to a state that the side surface of the blade part is horizontal;
step six, using a rough milling cutter to carry out reciprocating processing on the upward side surface of the blade part of the workpiece, so that the shape of the upward side surface of the blade part of the workpiece gradually approaches to the blade surface shape of the aero-engine blade;
step seven, the driving element drives the processed blade to rotate 180 degrees and then stops, and the step six is repeated;
step eight, the driving element drives the processed blade to continuously rotate; simultaneously, a machining center sequentially adopts a rough milling cutter, a semi-finish milling cutter and a finish milling cutter to mill blade parts of a rotating workpiece, so that the blade parts of the workpiece are machined into the shape of an aero-engine blade;
and step nine, removing the workpiece from the clamp, and cutting and removing the locating part and the clamping part on the workpiece to obtain the machined aeroengine blade.
2. The method for machining an aircraft engine blade according to claim 1, wherein: the limiting assembly further comprises a first bolt; a second threaded hole is formed in the limit base (2); the first bolt is arranged in the first threaded hole; the first bolt can prop against the bottom plate (1) and lock the position of the limiting base (2).
3. The method for machining an aircraft engine blade according to claim 1, wherein: the limiting assembly further comprises a connecting piece; the connecting piece is fixedly connected to one side, opposite to the clamping base, of the limiting base (2); the thimble (4) is rotationally connected to the connecting piece.
4. The method for machining an aircraft engine blade according to claim 1, wherein: a rotating groove is formed in the supporting base (5); the rotating disc (6) and the rotating groove form a rotating pair.
5. The method for machining an aircraft engine blade according to claim 1, wherein: the driving element adopts a motor; an output shaft of the motor penetrates through the supporting base (5) and is fixedly connected with the rotating disc (6).
6. The method for machining an aircraft engine blade according to claim 1, wherein: the fixed connecting piece comprises a supporting rod and two clamping pieces; the supporting rod is fixedly connected with the rotating disc (6), and the central point of the supporting rod is positioned on the central axis of the rotating disc (6); the two clamping pieces are symmetrically arranged on the supporting rod.
7. The method for machining an aircraft engine blade according to claim 6, wherein: in the processing process, the clamping part of the workpiece is positioned between the two clamping pieces; the bolt screwed on the clamping piece is propped against the clamping part of the workpiece.
8. The method for machining an aircraft engine blade according to claim 1, wherein: the model of the rough milling cutter is D8R1; the semi-finish milling cutter adopts a ball end milling cutter with the model of B6; the finish milling cutter adopts a ball end milling cutter with the model of B6J.
CN202310633988.4A 2023-05-31 2023-05-31 Processing method of aero-engine blade Pending CN116460343A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202310633988.4A CN116460343A (en) 2023-05-31 2023-05-31 Processing method of aero-engine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202310633988.4A CN116460343A (en) 2023-05-31 2023-05-31 Processing method of aero-engine blade

Publications (1)

Publication Number Publication Date
CN116460343A true CN116460343A (en) 2023-07-21

Family

ID=87181003

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202310633988.4A Pending CN116460343A (en) 2023-05-31 2023-05-31 Processing method of aero-engine blade

Country Status (1)

Country Link
CN (1) CN116460343A (en)

Similar Documents

Publication Publication Date Title
CN210677068U (en) Gantry type coarse-fine composite five-axis precision machine tool
CN108480923B (en) Method for precisely machining large thin-wall revolving body part
CN109531196B (en) A benchmark conversion equipment for rotor blade tenon processing
CN113182906B (en) Aeroengine turbine blade machining clamp and clamping method thereof
CN104646686A (en) Microscope eyepiece base housing turning method
CN103752918A (en) Zero-position cutting and finish-milling process for air channel molded line of air compressor moving blade
CN215281032U (en) Adjustable positioning and stopping device for inner cavity hole machining
CN108237374B (en) Three-axis linkage machining method for curved surface of multi-blade rotating wheel
CN210255284U (en) Four-axis rotating tool clamp
CN116460343A (en) Processing method of aero-engine blade
CN111318905A (en) Machine tool coordinate pedestal
CN213196543U (en) Machine tool coordinate pedestal
CN210648885U (en) Aeroengine wheel disk mortise linear cutting indexing fixture
CN110977070B (en) Fixing device and method for blade tenon in linear cutting
CN87202772U (en) Universal working carriage
CN111037314B (en) Large blade milling and polishing machine tool
CN110666449B (en) Machining method for aluminum alloy virtual reference part
CN108788258B (en) Blisk composite numerical control milling double-upright-column structure machine tool
CN112296399A (en) Special boring fixture
CN111571153A (en) Method for machining blade profile of Kaplan turbine blade
CN213105682U (en) Tooling clamp of 20-type drilling and milling machine tool
CN110900451B (en) High-efficient accurate positioning fixture
CN112405110B (en) Precision positioning device for included angle between cutting edge of turning tool and valve core
CN213531649U (en) Processing tool for symmetrical fan-shaped grooves of epoxy framework
CN214237235U (en) Milling machine processing work piece bolt hole tool

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