CN114700769B - Aviation blade face machining, clamping and positioning method - Google Patents
Aviation blade face machining, clamping and positioning method Download PDFInfo
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- CN114700769B CN114700769B CN202210412070.2A CN202210412070A CN114700769B CN 114700769 B CN114700769 B CN 114700769B CN 202210412070 A CN202210412070 A CN 202210412070A CN 114700769 B CN114700769 B CN 114700769B
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- blade
- positioning
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- tip
- machining
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- 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
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- 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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
The invention provides a method for machining, clamping and positioning an aviation blade surface, which comprises the following steps: firstly, clamping and positioning a dovetail wedge head by using a tool according to positioning requirements; step two, the tip of the cutter type center is arranged on the end face of the tip process boss, and the aircraft blade is initially machined and positioned; step three, milling the tip technological boss by using a tool type center; step four, after the end face of the technological boss of the blade tip is processed, withdrawing the cutter type center; step five, using a claw to tightly grasp and position the end face of the tip process boss processed in the step; and step six, profile machining is carried out on the blade body. The method has simple operation flow and can be quickly popularized to the processing of the blade profiles of the same type; meanwhile, the blade profile processed by the method has the characteristics of high position degree and profile degree qualification rate.
Description
Technical Field
The invention relates to the field of aviation blade surface positioning, in particular to a clamping and positioning method for aviation blade surface processing.
Background
The existing five-axis allowance-free machining technology of the blade tends to be mature, and is actually applied to various types of aviation blades in large batch, but due to the fact that different manufacturers and different process schemes are different, the positioning method adopted by profile machining is different, and the existing mainstream dovetail type tenon tooth blade positioning and clamping method is that dovetail surface positioning is adopted, the bottom surface is pressed, and a tip hole in the tip direction is supported in an auxiliary mode.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a clamping and positioning method for machining the blade profile of aviation engine, which has the advantages of simple operation process and capability of being rapidly popularized to the machining of the blade profile of the same type; meanwhile, the blade profile processed by the method has the characteristics of high position degree and profile degree qualification rate.
The invention is realized by the following technical scheme: the machining, clamping and positioning method for the blade surfaces of the aircraft is characterized by comprising the following positioning steps:
firstly, clamping and positioning a dovetail wedge head by using a tool according to a positioning requirement;
step two, the tip of the cutter type center is arranged on the end face of the tip process boss, and the aviation engine blade is initially processed and positioned;
step three, milling the tip technological boss by using a tool type center;
step four, after the end face of the tip technological boss is machined, the cutter type center is withdrawn;
step five, using a claw to tightly grasp and position the end face of the tip process boss processed in the step;
and step six, profile machining is carried out on the blade body.
Furthermore, when the dovetail wedge head is positioned by the tool in the first step, the exhaust edge direction of the blade body is rotated to be perpendicular to the ground through equipment to be positioned.
Furthermore, when the dovetail wedge head is positioned in the first step, a five-axis machining center is selected as an adopted operating device.
Furthermore, in the first step, the positioning requirement tool and the dovetail wedge are tightly attached to each other.
Further, the tool used in the second step is a hard alloy tool.
Furthermore, when the tip of the tool type center in the second step is arranged at the initial machining position, the adopted pressing force is monitored by the current of the U shaft of the device, and the current is 1.1A-1.3A.
Furthermore, when the tip of the tool type center in the second step is arranged at the initial processing and positioning, the tip of the tool type center is pricked into the position 2-3mm inside the tip process boss 1.
Further, the milling adopted in the third step is performed according to 0.05mm milling each time.
Further, the milling in the third step is carried out according to a set program, and the milling is required until the two opposite surfaces are milled.
Further, after the tool type center is removed in the fourth step, the machining end is directly set to be a clamping jaw through replacement.
Compared with the prior art, the invention has the following beneficial technical effects: the positioning method provided by the invention has the advantages that the operation process is simple, and the method can be rapidly popularized to the processing of the blade profiles of the same type; meanwhile, the blade profile processed by the method has the characteristics of high position degree and profile degree qualification rate.
Furthermore, the direction of the exhaust edge of the blade body is rotated to be perpendicular to the ground through equipment to be positioned, and the deviation of the basin back direction caused by the self weight of the blade can be effectively reduced. In addition, the device uses the same equipment to switch the cutter and the clamping end, so that the convenience in use is greatly improved, and the use and the operation of workers in the field are greatly facilitated.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the embodiments or technical descriptions will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a certain type of engine blade before finish machining in a method for machining, clamping and positioning an aircraft blade surface according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a cutter type center of the aircraft blade surface machining, clamping and positioning method provided by the embodiment of the invention;
fig. 3 is a schematic view of a claw structure of a clamping and positioning method for processing a blade profile of an aircraft according to an embodiment of the present invention;
fig. 4 is a schematic processing diagram of step three of the method for processing, clamping and positioning the blade profile of the aircraft according to the embodiment of the present invention;
fig. 5 is a schematic diagram of a step of machining, clamping and positioning a blade profile of an aircraft according to an embodiment of the present invention;
in the figure: the blade tip process boss 1, the blade body 2, the dovetail wedge 3, the leading edge 4 and the trailing edge 5.
Detailed Description
In the following, only certain exemplary embodiments are briefly described. As those skilled in the art would realize, the described embodiments may be modified in various different ways, all without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature, and not as restrictive.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; the connection can be mechanical connection, electrical connection or communication; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. The first feature being "under," "beneath," and "under" the second feature includes the first feature being directly above and obliquely above the second feature, or simply meaning that the first feature is at a lesser level than the second feature.
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In an operation project, the aeroengine blade surface processing, clamping and positioning method comprises a blade tip technological boss 1, a blade body 2, a dovetail wedge 3, a front edge 4 and a rear edge 5, wherein the aeroengine blade comprises the blade tip technological boss 1, the blade body 2 and the dovetail wedge 3, an exhaust edge is axially arranged on the aeroengine blade along the blade body 2, and the blade tip technological boss 1 and the dovetail wedge 3 are respectively arranged at two ends of the blade body 2; the following steps are specifically used:
step 1, clamping and clamping the dovetail wedge 3 by using a tool according to positioning requirements, wherein the dovetail wedge is required to be tightly attached during clamping and positioning;
step 2, the air inlet and outlet side direction of the aviation blades is rotated to be perpendicular to the ground by the operation equipment, wherein the air inlet and outlet side direction is the direction from the front edge to the rear edge or from the rear edge to the front edge, so that the direction perpendicular to the ground can effectively reduce the deflection of the basin back direction caused by the self weight of the blades; meanwhile, the operating equipment selects a five-axis machining center used for machining the blade;
and 5, removing the tip of the equipment, replacing a special clamping jaw, tightly clamping the surface of the process boss processed in the step 4 by using the clamping jaw, and simultaneously processing the molded surface.
In the specific operation process: firstly, clamping a part to enable the air inlet and outlet edge direction of the part to be vertical to the ground, and reducing the influence of gravity; using a proper pressing force top center, and then processing a tip technological boss 1 by adopting a set program; after the machining is finished, the cutter is withdrawn from the tip process boss 1, and a specific clamping jaw is used for clamping the process diagram table top; and finishing positioning and carrying out formal processing on the blade body 2.
While there have been shown and described what are at present considered the fundamental principles and essential features of the invention and its advantages, it will be apparent to those skilled in the art that the invention is not limited to the details of the foregoing exemplary embodiments, but is capable of other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art. The above contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention should not be limited thereby, and any modification made on the basis of the technical idea proposed by the present invention falls within the protection scope of the claims of the present invention.
Claims (7)
1. The machining, clamping and positioning method for the blade surfaces of the aircraft is characterized by comprising the following positioning steps:
clamping and positioning the dovetail wedge head (3) by using a tool according to positioning requirements, wherein the clamping and positioning comprise the steps that an operation device rotates the air inlet and outlet side direction of an aircraft blade to be vertical to the ground, and the air inlet and outlet side direction is the direction that the front edge points to the rear edge or the rear edge points to the front edge;
step two, the tip of the cutter type center is arranged on the end face of the blade tip technological boss (1) to perform initial processing and positioning on the aviation blade, wherein the cutter type center is pricked into the blade tip technological boss by 12-3mm under proper pressure and is formed by grinding through a cutter;
step three, milling a technical boss of the blade tip on the back side of the basin by taking the tip shaft as a symmetry shaft according to a set program until two opposite surfaces of the technical boss of the blade tip symmetrical by the tip shaft are milled surfaces;
step four, after the end face of the tip technological boss (1) is machined, the cutter type center is withdrawn;
step five, using a clamping jaw to tightly grasp and position the end face of the tip technological boss (1) processed in the step four;
sixthly, profile machining is carried out on the blade body (2).
2. The aircraft blade profile machining, clamping and positioning method as claimed in claim 1, wherein in the first step of positioning the dovetail wedge (3), a five-axis machining center is selected as an operating device.
3. The aircraft blade profile machining, clamping and positioning method as claimed in claim 1, wherein in the first step, the positioning requires that the fixture and the dovetail (3) are tightly attached to each other.
4. The aircraft blade profile machining, clamping and positioning method as claimed in claim 1, wherein the tool used in the second step is a cemented carbide tool.
5. The method for machining, clamping and positioning the airfoil surface of the aviation blade in the claim 1, wherein when the tip of the tool center in the second step is arranged at the initial machining position, the adopted pressing force is monitored by the current of a U shaft of the equipment, and the current is 1.1-1.3A.
6. The clamping and positioning method for machining the blade surface of the aircraft as recited in claim 1, wherein the milling adopted in the third step is performed by milling according to 0.05mm each time.
7. The method for machining, clamping and positioning the airfoil surface of the aircraft blade as claimed in claim 1, wherein in the fourth step, after the tool type center is withdrawn, the center is replaced by a special jaw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412070.2A CN114700769B (en) | 2022-04-19 | 2022-04-19 | Aviation blade face machining, clamping and positioning method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210412070.2A CN114700769B (en) | 2022-04-19 | 2022-04-19 | Aviation blade face machining, clamping and positioning method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114700769A CN114700769A (en) | 2022-07-05 |
| CN114700769B true CN114700769B (en) | 2023-01-31 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210412070.2A Active CN114700769B (en) | 2022-04-19 | 2022-04-19 | Aviation blade face machining, clamping and positioning method |
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Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102029537B (en) * | 2010-11-11 | 2012-08-29 | 西北工业大学 | Precise positioning fixture for numerical control machining of thin-wall blade |
| DE102011011495B4 (en) * | 2011-02-17 | 2013-05-08 | Lufthansa Technik Ag | Apparatus for repairing gas turbine blades |
| CN102975050A (en) * | 2012-11-30 | 2013-03-20 | 无锡透平叶片有限公司 | Rotary mill clamp structure of blade with tenon tooth root |
| CN103846706B (en) * | 2014-03-20 | 2016-04-20 | 西北工业大学 | The special stretching device of a kind of blade parts milling |
| CN104028983B (en) * | 2014-07-01 | 2016-04-27 | 东方电气集团东方汽轮机有限公司 | A kind of fir-tree root class turbine blade manufacturing process |
| CN205927972U (en) * | 2016-08-29 | 2017-02-08 | 中航动力股份有限公司 | Fan big blades profile mills quick resilient mounting positioner |
| HUE047520T2 (en) * | 2016-11-29 | 2020-04-28 | Gf Machining Solutions Ag | Method for material removing machining of a turbine blade and machine tool for carrying out such a method |
| CN106392714B (en) * | 2016-12-21 | 2019-01-18 | 中国南方航空工业(集团)有限公司 | A kind of compressor blade clamping method and the fixture used |
| CN109365884A (en) * | 2018-12-17 | 2019-02-22 | 中国航发动力股份有限公司 | A kind of rotor blade tip cutting off processing method and its application |
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| CN114700769A (en) | 2022-07-05 |
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