CN112427889B - Method for reducing residual stress of forged and extruded blade - Google Patents
Method for reducing residual stress of forged and extruded blade Download PDFInfo
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- CN112427889B CN112427889B CN202011219102.4A CN202011219102A CN112427889B CN 112427889 B CN112427889 B CN 112427889B CN 202011219102 A CN202011219102 A CN 202011219102A CN 112427889 B CN112427889 B CN 112427889B
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- 238000000034 method Methods 0.000 title claims abstract description 30
- 238000001125 extrusion Methods 0.000 claims abstract description 16
- 238000005520 cutting process Methods 0.000 claims abstract description 4
- 238000010008 shearing Methods 0.000 claims description 26
- 230000005284 excitation Effects 0.000 claims description 19
- 238000013461 design Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 abstract description 3
- 238000012797 qualification Methods 0.000 abstract description 3
- 230000035882 stress Effects 0.000 description 26
- 239000000463 material Substances 0.000 description 6
- 238000004364 calculation method Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000032683 aging Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000003878 thermal aging Methods 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23D—PLANING; SLOTTING; SHEARING; BROACHING; SAWING; FILING; SCRAPING; LIKE OPERATIONS FOR WORKING METAL BY REMOVING MATERIAL, NOT OTHERWISE PROVIDED FOR
- B23D33/00—Accessories for shearing machines or shearing devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D10/00—Modifying the physical properties by methods other than heat treatment or deformation
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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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P10/00—Technologies related to metal processing
- Y02P10/20—Recycling
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- Forging (AREA)
Abstract
The utility model provides a method for cutting down forges extrusion blade residual stress, it is through setting up two vibration scissors, when getting rid of blade burr overlap, control the frequency and the feed rate of vibration scissors, and the vibration frequency of cooperation blade effectively subdues the residual stress that the blade produced in high-speed extrusion forming technology to promote the qualification rate of blade blank follow-up processing greatly.
Description
Technical Field
The invention relates to the technical field of forging, in particular to a method for reducing residual stress of a forged and extruded blade after the blade of an aero-engine is forged in an extrusion mode.
Background
The blade is one of important parts of an aeroengine, the forging of the aeroengine blade in an extrusion mode is a common manufacturing mode, in the extrusion forming process of the blade, because the uneven deformation of each layer of metal of a blade body is limited by the integrity of a forming structure, each part in the deformed metal can be caused to generate additional stress in a self-phase balance mode, and after the external acting force causing the deformation is cancelled after the extrusion process is finished, the additional stress does not disappear completely, but remains in the blade and is converted into residual stress. Such residual stresses not only affect the fatigue resistance and corrosion resistance of the blade, but also cause local bending deformation of the blade profile and affect dimensional instability during part machining.
In the prior art, residual stress caused by the high-speed extrusion forming process can be eliminated by thermal aging and/or vibration aging, for example, chinese patent 2018107209961 provides an apparatus and method for eliminating stress by using thermal aging and vibration aging. However, these solutions have high energy consumption on one hand and complex processes on the other hand, and therefore, the manufacturing cost is greatly increased.
Disclosure of Invention
The technical problem underlying the present invention is to provide a method for reducing residual stresses in forged extruded blades, in order to reduce or avoid the aforementioned problems.
In order to solve the technical problem, the invention provides a method for reducing residual stress of a forged and extruded blade, which is used for eliminating the residual stress of the blade when burrs and flashes are sheared and removed from the blade forged in an extrusion mode, and comprises the following steps:
a, horizontally clamping a blade, taking the center point of the cubic tenon part of the blade as a coordinate origin point O, taking a plane parallel to the length direction of the tenon part as a plane of a coordinate system, taking a line passing through the center point A of the blade tip of the blade as an X axis, establishing an X-Y coordinate system by taking a vertical projection view angle with the blade basin surface under and the blade back surface on, selecting a fixed excitation point C, wherein the coordinate of the fixed excitation point C is (M, 0), and the coordinate of the center point A of the blade tip of the blade is (M1，0)，0.7M1≤M≤0.9M1A fixed vibration source is arranged at the fixed excitation point C,
and B, taking the fixed excitation point C selected in the step A as a passing point, and calculating to obtain two end points B of the blade tip part in the clockwise direction3、A1And are each represented by B3、A1Respectively calculating to obtain the intersection point A of two straight lines passing through the fixed excitation point C and the other side of the blade as a starting point3、B1The coordinates of (a).
Step C, arranging a first vibration shear at the midpoint A of the blade tip of the blade, and arranging a second vibration shear at the endpoint B3A second vibration shear is arranged at the intersection point B of the blade body at one side and the tenon head part, and the fixed vibration source is started to ensure that the blade has the natural frequencyVibrating to make the working frequency of the first vibrating shear the same as the natural frequency of the blade and clockwise from the point A to the point A1Cutting points while allowing the second vibration shears to move from point B to point B1Point shearing is carried out to ensure that the first vibration shear shears to A1While the second vibration shear shears to B1Point, then, make the working frequency of the second vibration shear the same as the natural frequency of the blade, and clockwise from B1Point to point B3Point shearing while making the first vibration shear from A1Point direction A3Point shearing is carried out to ensure that the first vibration shear shears to A3While the second vibration shear shears to B3Point, finally, adjusting the working frequency of the first vibration shear to be less than the natural frequency of the blade and clockwise from A3Point direction A4Point shearing while keeping the working frequency of the second oscillating shear the same as the natural frequency of the blade, clockwise from B3Shearing from point A to ensure that the first vibration shear shears to point A4And shearing the second vibration shear to the point A at the same time of point, so as to complete the shearing and removing of the burr flash of the blade body part of the blade.
Preferably, in step C, the natural frequency of the blade is the natural frequency of the blade in an operating stress state at the time of design.
Preferably, the second oscillating shears are at B B1The operating frequency between the points is set to be lower than the natural frequency of the blade, and the first vibration is cut at A3 A4The operating frequency between the points is also set to be lower than the natural frequency of the blade.
Preferably, the second oscillating shears are at B B1The operating frequency between the points is 80-90% of the natural frequency of the blade, and likewise the first vibration is sheared at A3 A4The operating frequency between the points is 80-90% of the natural frequency of the blade.
The method for reducing the residual stress of the forged and extruded blade can effectively reduce the residual stress generated by the blade in the high-speed extrusion forming process while removing the burr flash of the blade through vibration shearing, thereby greatly improving the qualification rate of subsequent processing of blade blanks.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein,
FIG. 1 is a schematic diagram of a method of reducing residual stress in a forged extruded blade according to an embodiment of the present invention;
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
For an aircraft engine blade forged in an extrusion manner, particularly for an aircraft engine blade with a large size, a female die is usually formed by combining at least two parts, so that the manufactured blade can be taken out after extrusion is completed, a part of structure is left in a gap of a die of the blade manufactured in the manner, and burrs which need to be removed are usually generated on the periphery of the blade.
In the prior art, after the blade of the aircraft engine is forged in an extrusion mode, burrs and flashes can be sheared and removed by using a vibration shear. The inventor team finds that the vibration shear can enable the blade to vibrate at the periphery of the blade in the working process, if the relation with the natural frequency of the blade can be found, an additional vibration source is added, so that the residual stress of the blade is reduced through vibration in the process of removing burr and flash, and the production efficiency can be greatly improved.
FIG. 1 is a schematic diagram of a method of reducing residual stress in a forged extruded blade according to an embodiment of the present invention; referring to fig. 1, in the prior art, when a vibration shear is used to shear and remove burrs and flashes, a blade is generally horizontally placed as shown in fig. 1 so that a portion to be sheared is located on the same horizontal plane as much as possible, specifically, a center point of a cubic tenon portion of the blade may be used as a coordinate origin O point, a plane parallel to a length direction of the tenon portion may be used as a plane where a coordinate system is located, a line passing through a midpoint a of a blade tip of the blade may be used as an X-axis, and a vertical projection view angle of a basin surface of the blade and a back surface of the blade on the top of the basin surface of the blade may be used to establish an X-Y coordinate system as shown in fig. 1. The invention provides a method for reducing residual stress of a forged and extruded blade, which is used for eliminating the residual stress of the blade when the blade forged by an extrusion mode is sheared and deburred,
a, horizontally clamping a blade to enable a blade basin surface to be located at the lower part and a blade back surface to be located at the upper part, selecting a fixed excitation point C, wherein the coordinate of the fixed excitation point C is (M, 0), and the coordinate of a midpoint A point of the blade tip of the blade is (M)1，0)，0.7M1≤M≤0.9M1A fixed vibration source is arranged at the fixed excitation point C,
in the step, a fixed excitation point C which enables the blade to keep vibration at a fixed frequency in the process of removing burrs and flash of the blade is selected, and the fixed excitation point C is selected on an X axis, so that the subsequent calculation process can be effectively simplified, and the vibration effect can be guaranteed.
The natural frequency of the blade is selected to be the natural frequency of the blade in the working stress state during design, for example, for a certain type of blade, the working stress Fs is 120MPa (120N/mm)2) The natural frequency fp is 328 HZ.
And B, taking the fixed excitation point C selected in the step A as a passing point, and calculating to obtain two end points B of the blade tip part in the clockwise direction3、A1And are each represented by B3、A1Respectively calculating to obtain the intersection point A of two straight lines passing through the fixed excitation point C and the other side of the blade as a starting point3、B1The coordinates of (a).
In this step, it is necessary to determine the boundary points of the specific area involved in the present invention and calculate the coordinates of these boundary points, so as to facilitate the subsequent control of the feeding rate of the vibration shears in the deburring process.
For example, with A1And A3The two points are a starting point and an end point,calculating to obtain A1 A3Equation Y ═ K for the straight line correspondences1X+D1With B1And B3Two points are used as a starting point and an end point, and B is obtained by calculation1 B3Equation Y ═ K for the straight line correspondences2X+D2Calculating to obtain A1B1Slope K of the line0Thus, for A1 A3Any point An in the straight line is taken as a starting point, the equation corresponding to the straight line AnBn passing through the point C is KX-KM,
after the above equations and the corresponding parameters are obtained through calculation, the equations and the corresponding parameters can be used for subsequent parameter calculation.
Step C, arranging a first vibration shear at the midpoint A of the blade tip of the blade, and arranging a second vibration shear at the endpoint B3A second vibration shear is arranged at the intersection point B of the blade body at one side and the tenon head, the fixed vibration source is started, the blade vibrates at the natural frequency, the working frequency of the first vibration shear is the same as the natural frequency of the blade, and the blade clockwise rotates from the point A to the point A1Cutting points while allowing the second vibration shears to move from point B to point B1Point shearing is carried out to ensure that the first vibration shear shears to A1While the second vibration shear shears to B1Point, then, make the working frequency of the second vibration shear the same as the natural frequency of the blade, and clockwise from B1Point to point B3Point shearing while making the first vibration shear from A1Point direction A3Point shearing is carried out to ensure that the first vibration shear shears to A3While the second vibration shear shears to B3Point, finally, adjusting the working frequency of the first vibration shear to be less than the natural frequency of the blade and clockwise from A3Point direction A4Point shearing while keeping the working frequency of the second oscillating shear the same as the natural frequency of the blade, clockwise from B3Shearing from point A to ensure that the first vibration shear shears to point A4And shearing the second vibration shear to the point A at the same time of point, so as to complete the shearing and removing of the burr flash of the blade body part of the blade.
Through long-term practice analysis, the inventor team finds that when the vibration shears are used for removing burr flashes of the blade body part of the blade, on the premise that the blade keeps natural frequency vibration, if two vibration shears are used for synchronously shearing according to the natural frequency of the blade in the specific area selected in the step B, the residual stress of the blade can be effectively removed.
See FIG. 1 for a view because B B1The distance of the points is far greater than A A1Distance of points, and the inventors have found through practice that when using vibratory shears to remove flash from press forged blades of dissimilar materials, the feed rate can be higher when operating below the natural frequency of the material than when operating at the natural frequency of the material, and therefore in this step, the second vibratory shear is at B B1The operating frequency between the points is set to be lower than the natural frequency of the blade, so that the second vibration shear is controlled to be B1When the point is on, the first vibration shear shears simultaneously shear to A1And (4) point.
Similarly, the first vibration shears are arranged at A3 A4The operating frequency between the points is also set to be lower than the natural frequency of the blade.
For blades made of some material, the second oscillating shear is at B B1Between points and said first oscillating shear at AA1In the case that the same working frequency as the natural frequency of the material can be adopted between the points and the simultaneous completion can be ensured, the inventor unexpectedly finds that the second vibration shears at B B1Between points and said first oscillating shear at AA1Different working frequencies are adopted among the points, and the removal of the residual stress is more favorable than that of the residual stress which is respectively adopted with the working frequencies which are the same as the natural frequency of the material. Empirically, the second vibratory shear is at B B1The operating frequency between the points may be 80-90% of the natural frequency of the blade, and as such, the first vibratory shear is at A3 A4The operating frequency between the points may also be 80-90% of the natural frequency of the blade,
the present invention is most different from the prior art in that,
firstly, two vibration shears are synchronously used for shearing and removing burrs of a blade body part of the blade, and in the whole process, a fixed vibration source is arranged to apply an exciting force at a specific fixed excitation point C, so that the blade can vibrate at a natural frequency in the whole process.
Secondly, calculating and obtaining B according to the fixed excitation point C3、A1、A3、B1Four characteristic points, so that the two vibrating shears meet the specific relation between the feeding speed and the shearing length in the whole working process. (for example, the coordinates and equations obtained in step B can be used to obtain the real-time controlled feed rate of the vibratory shear via calculus)
The method for reducing the residual stress of the forged and extruded blade can effectively reduce the residual stress generated by the blade in the high-speed extrusion forming process while removing the burr flash of the blade through vibration shearing, thereby greatly improving the qualification rate of subsequent processing of blade blanks.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (3)
1. A method for reducing residual stress of a forged extruded blade, which is used for eliminating residual stress of the blade when a burr flash is sheared and removed from the blade forged by an extrusion mode, and comprises the following steps:
step A, horizontally clamping the blade,the method comprises the steps of taking the center point of a cubic tenon part of a blade as a coordinate origin point O, taking a plane parallel to the length direction of the tenon part as a plane of a coordinate system, taking a line passing through a midpoint A point of the blade tip of the blade as an X axis, establishing an X-Y coordinate system by taking a vertical projection view angle with the blade basin surface under and the blade back surface on, selecting a fixed excitation point C, taking the coordinate of the fixed excitation point C as (M, 0), and taking the coordinate of the midpoint A point of the blade tip of the blade as (M1，0），0.7M1≤M≤0.9M1A fixed vibration source is arranged at the fixed excitation point C,
and B, taking the fixed excitation point C selected in the step A as a passing point, and calculating to obtain two end points B of the blade tip part in the clockwise direction3、A1And are each represented by B3、A1Respectively calculating to obtain the intersection point A of two straight lines passing through the fixed excitation point C and the other side of the blade as a starting point3、B1Is determined by the coordinate of (a) in the space,
step C, arranging a first vibration shear at the midpoint A of the blade tip of the blade, and arranging a second vibration shear at the endpoint B3A second vibration shear is arranged at the intersection point B of the blade body at one side and the tenon head, the fixed vibration source is started, the blade vibrates at the natural frequency, the working frequency of the first vibration shear is the same as the natural frequency of the blade, and the blade clockwise rotates from the point A to the point A1Cutting points while allowing the second vibration shears to move from point B to point B1Point shearing is carried out to ensure that the first vibration shear shears to A1While the second vibration shear shears to B1Point, the second vibration is cut at B B1The operating frequency between the points is set to be lower than the natural frequency of the blade, after which the operating frequency of the second vibratory shear is made to be the same as the natural frequency of the blade and is clockwise from B1Point to point B3Point shearing while making the first vibration shear from A1Point direction A3Point shearing is carried out to ensure that the first vibration shear shears to A3While the second vibration shear shears to B3Point, finally, adjust the first vibration shear at A3 A4The operating frequency between the points being set lower than that of the bladeNatural frequency and clockwise from A3Point direction A4Point shearing while keeping the working frequency of the second oscillating shear the same as the natural frequency of the blade, clockwise from B3Shearing from point A to ensure that the first vibration shear shears to point A4And shearing the second vibration shear to the point A at the same time of point, so as to complete the shearing and removing of the burr flash of the blade body part of the blade.
2. The method of reducing residual stress in a forged extruded blade of claim 1 wherein in step C, said blade natural frequency is the natural frequency of said blade at design time in an operating stress state.
3. The method of reducing residual stress in a forged extrusion blade of claim 1 wherein said second vibratory shear is B B1The operating frequency between the points is 80-90% of the natural frequency of the blade, and likewise the first vibration is sheared at A3 A4The operating frequency between the points is 80-90% of the natural frequency of the blade.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011219102.4A CN112427889B (en) | 2020-11-04 | 2020-11-04 | Method for reducing residual stress of forged and extruded blade |
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| CN202011219102.4A CN112427889B (en) | 2020-11-04 | 2020-11-04 | Method for reducing residual stress of forged and extruded blade |
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| JP2002332519A (en) * | 2001-05-14 | 2002-11-22 | Kawasaki Steel Corp | Method for reducing camber after strip cutting in steel sheet |
| US6558485B2 (en) * | 2001-08-13 | 2003-05-06 | General Electric Company | Laser shock peening with an explosive coating |
| CN107937709A (en) * | 2017-12-26 | 2018-04-20 | 南宁邃丛赋语科技开发有限责任公司 | A kind of vibration ageing device eliminated for workpiece residual stress |
| CH714900B1 (en) * | 2018-04-08 | 2021-01-15 | Crossnet Consulting Ag | Measurement of residual stress and residual stress relief through acoustic vibration. |
| CN108774667B (en) * | 2018-07-04 | 2019-11-08 | 中国工程物理研究院机械制造工艺研究所 | A kind of device and method for eliminating stress using heat aging and oscillating aging collaboration |
| CN110000626B (en) * | 2019-05-20 | 2022-03-29 | 大连海洋大学 | Stress reduction device on surface of raceway of bearing ring |
| CN110773699B (en) * | 2019-11-10 | 2021-02-09 | 中国航发南方工业有限公司 | Method for controlling extrusion forming residual stress of forged blade |
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