CN111122316B - Device for eliminating residual stress of aviation metal part and examining aging performance - Google Patents
Device for eliminating residual stress of aviation metal part and examining aging performance Download PDFInfo
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- CN111122316B CN111122316B CN201911289316.6A CN201911289316A CN111122316B CN 111122316 B CN111122316 B CN 111122316B CN 201911289316 A CN201911289316 A CN 201911289316A CN 111122316 B CN111122316 B CN 111122316B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
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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
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/26—Methods of annealing
- C21D1/30—Stress-relieving
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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
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/74—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material
- C21D1/773—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material under reduced pressure or vacuum
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0047—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes measuring forces due to residual stresses
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/24—Investigating strength properties of solid materials by application of mechanical stress by applying steady shearing forces
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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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Abstract
The invention provides a device for evaluating the residual stress of aviation metal parts, which comprises: dull and stereotyped mould (1), fixed platform (2), bolt (3), wherein: the fixed platform (2) is connected; the flat plate die (1) is used for bearing the test metal part (4) coated with the vacuum bag film (5); the vacuum autoclave (6) is used for carrying out an aging process for eliminating residual stress on the test metal part (4) coated with the vacuum bag film (5) and borne on the flat plate die (1), and pressing the test metal part (4) into a planar plate; and the static test platform is used for carrying out static or shear examination tests on the plate pressed into the plane to obtain the failure strength parameters, and confirming the failure strength parameters of the plate pressed into the plane as the failure strength parameters of the metal part to be examined. The device is not only accurate and reliable, but also can not damage the mechanical property of the metal part to be checked.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a device for evaluating the aging performance of eliminating residual stress of aviation metal parts.
Background
The aerospace industry uses a large number of metal materials for the manufacture of large complex section parts, which can produce residual stresses that are difficult to remove during the manufacturing process, resulting in part deformation. In order to eliminate the residual stress in the manufacturing process of the large-sized complex-section part, the aging can be carried out in an autoclave, meanwhile, the pressure is introduced in the process to lead the part to creep, and finally, the residual stress is eliminated while the part achieves the target performance.
However, after aging for residual stress relief in an autoclave, the parts generally exhibit a final morphology with curvature, and the parts with curvature cannot undergo static or shear test commonly used in engineering.
Disclosure of Invention
In view of this, in order to solve at least one technical problem in the prior art, the invention provides a device for aging performance assessment of aviation metal part residual stress removal.
The device for the aging performance assessment for eliminating the residual stress of the aviation metal part comprises:
dull and stereotyped mould 1, fixed platform 2, bolt 3, wherein:
the flat plate die 1 is arranged above the fixed platform 2 and is connected with the fixed platform 2 through a bolt 3;
the flat plate mould 1 is used for bearing a test metal part 4 coated with a vacuum bag film 5;
the vacuum autoclave 6 is used for carrying out an aging process for eliminating residual stress on the test metal part 4 coated with the vacuum bag film 5 and borne on the flat plate die 1, and pressing the test metal part 4 into a planar plate;
and the static test platform is used for carrying out static or shear examination tests on the plate pressed into the plane to obtain the failure strength parameters, and confirming the failure strength parameters of the plate pressed into the plane as the failure strength parameters of the metal part to be examined.
The advantages of the invention may be:
the properties of the metal parts to be examined are determined by testing the properties of the metal parts 4. The test metal part 4 is first formed by machining into a plate having a predetermined curvature. The test metal parts 4 were pressed into flat test pieces in order to test the final performance level after aging for eliminating residual stress. And performing static or shear examination on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter, and determining the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be examined. The device is not only accurate and reliable, but also can not damage the mechanical property of the metal part to be checked.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic diagram of an aging performance assessment device for eliminating residual stress of an aviation metal part according to an embodiment of the invention;
FIG. 2 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to an embodiment of the invention;
FIG. 3 is an isometric view of an apparatus for aging performance assessment to relieve residual stress in an aerospace metal part according to another embodiment of the invention;
FIG. 4 is a side view of a test piece tooling for aging relieving residual metal stress in accordance with an embodiment of the present invention.
The device comprises a flat plate die 1, a fixed platform 2, a bolt 3, a metal part 4 for testing, a vacuum bag film 5 and a vacuum autoclave 6.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features and illustrative embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvements, substitutions and modifications in structure, method, and apparatus without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic view of a test piece tool for eliminating residual stress of metal by aging according to an embodiment of the invention; FIG. 2 is an isometric view of a trial tool for aging relieving residual metal stress in accordance with an embodiment of the present invention; FIG. 3 is a side view of a test piece tooling for aging relieving residual metal stress in accordance with an embodiment of the present invention.
Referring to fig. 1 to 3, an apparatus for aging performance assessment for eliminating residual stress of an aviation metal part may include: the device comprises a flat plate die 1, a fixed platform 2 and a bolt 3.
Wherein: the flat plate die 1 is arranged above the fixed platform 2 and is connected with the fixed platform 2 through a bolt 3; the flat plate mould 1 is used for bearing a test metal part 4 coated with a vacuum bag film 5; the vacuum autoclave 6 is used for carrying out an aging process for eliminating residual stress on the test metal part 4 coated with the vacuum bag film 5 and borne on the flat plate die 1, and pressing the test metal part 4 into a planar plate; and the static test platform is used for carrying out static or shear examination tests on the plate pressed into the plane to obtain the failure strength parameters, and confirming the failure strength parameters of the plate pressed into the plane as the failure strength parameters of the metal part to be examined.
The metal part to be checked is a plate with a preset curvature after an aging process for eliminating residual stress. The test metal part 4 is a plate material having a predetermined curvature formed by machining.
In some embodiments, the concave surface of the pre-curved sheet material is ribbed. The flat mold 1 has grooves corresponding to the ribs. And determining the preset pressure and the preset temperature applied to the metal part to be verified based on the aging process. The specific parameters such as pressure and temperature can be flexibly set according to actual conditions.
In some embodiments, the aging performance assessment method for eliminating the residual stress of the metal part to be assessed by using the device comprises the following steps:
a sheet material with a preset curvature formed by machining is used as a metal part 4 for testing;
the vacuum bag film 5 covers the metal part 4 for the test;
the vacuum autoclave 6 carries out the aging process for eliminating residual stress on the test metal part 4 coated with the vacuum bag film 5 and carried on the flat plate die 1, and presses the test metal part 4 into a plane plate;
and the static test platform performs a static or shear test on the plate pressed into the plane to obtain a failure strength parameter, and confirms the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be checked.
The joint of the flat plate mould 1 and the flat plate mould 1 is sealed.
The invention designs a test piece tool for eliminating the residual stress of metal by time effect, which is used in an autoclave and meets the design of aerospace engineering examination test pieces.
In some embodiments, the tooling should follow the following principles:
principle 1: the lower platform should be attached to the autoclave. The lower platform is an important component of the tool, and is used for fixing a forming die in the vacuum autoclave, so that the lower platforms with different sizes are replaced aiming at the autoclaves with different diameters, and the lower platforms are ensured to be attached to the wall of the autoclave.
Principle 2: the joint of the forming die and the lower platform needs sealing treatment. The forming die is an important component of the tool, the forming die is fixed on the lower platform, the four corners of the forming die are connected with the lower platform through bolts, and the bolt joints at the four corners of the forming die must be sealed in order to guarantee a vacuum treatment environment.
Principle 3: and a vacuum pumping hole is reserved in the forming die. The forming die is an important component of the tool, and a vacuum pumping hole needs to be reserved in the center of the forming die in order to form a vacuum environment.
In some embodiments, a test piece tooling for aging elimination of metal residual stress comprises the following features:
the method is characterized in that 1, the forming die is flat;
the characteristic 2, the lower platform is jointed with the autoclave;
the forming die is connected with the lower platform through bolts;
4, placing the machined part with the curvature above a forming die;
the part is wrapped on a forming die by using a vacuum bag film;
and the characteristic 6 is that the tool is placed in a vacuum autoclave.
The advantages of the invention may be: the properties of the metal parts to be examined are determined by testing the properties of the metal parts 4. The test metal part 4 is first a plate material with a predetermined curvature formed by machining. The test metal parts 4 were pressed into flat test pieces after aging for residual stress relief in order to test the final performance level. And performing static or shear examination on the plate pressed into the plane by using a static test platform to obtain a failure strength parameter, and determining the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be examined. The device is not only accurate and reliable, but also can not damage the mechanical property of the metal part to be checked.
It should be noted that the above-mentioned flow operations may be combined and applied in different degrees, and for simplicity, implementation manners of various combinations are not described again, and those skilled in the art may flexibly adjust the sequence of the above-mentioned operation steps according to actual needs, or flexibly combine the above-mentioned steps, and the like.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (7)
1. The utility model provides a device that ageing performance of eliminating aviation metal parts residual stress was examined which characterized in that contains:
dull and stereotyped mould (1), fixed platform (2), bolt (3), wherein:
the flat plate die (1) is arranged above the fixed platform (2) and is connected with the fixed platform (2) through bolts (3);
the flat plate die (1) is used for bearing the test metal part (4) coated with the vacuum bag film (5);
the vacuum autoclave (6) is used for carrying out an aging process for eliminating residual stress on the test metal part (4) coated with the vacuum bag film (5) and borne on the flat plate die (1), determining preset pressure and preset temperature applied to the metal part to be verified based on the aging process, and pressing the test metal part (4) into a planar plate;
and the static test platform is used for carrying out static or shear examination tests on the plate pressed into the plane to obtain the failure strength parameters, and confirming the failure strength parameters of the plate pressed into the plane as the failure strength parameters of the metal part to be examined.
2. The apparatus of claim 1, wherein:
the metal part to be checked is a plate with a preset curvature after an aging process for eliminating residual stress.
3. The apparatus of claim 1, wherein:
the metal part (4) for testing is a plate material with a preset curvature formed by machining.
4. The apparatus of claim 1, wherein:
the concave surface of the plate with the preset curvature is provided with ribs.
5. The apparatus of claim 3, wherein:
the flat mold (1) is provided with grooves corresponding to the ribs.
6. The device of claim 1, wherein the aging performance assessment method for eliminating the residual stress of the metal part to be assessed by using the device comprises the following steps:
a plate with a preset curvature formed by machining is used as a metal part (4) for testing;
the vacuum bag film (5) covers the metal part (4) for the test;
the vacuum autoclave (6) carries out an aging process for eliminating residual stress on the test metal part (4) coated with the vacuum bag film (5) and borne on the flat mold (1), and presses the test metal part (4) into a planar plate;
and the static test platform performs a static or shear test on the plate pressed into the plane to obtain a failure strength parameter, and confirms the failure strength parameter of the plate pressed into the plane as the failure strength parameter of the metal part to be checked.
7. The apparatus of any one of claims 1-6, wherein:
the joint of the flat plate mould (1) and the flat plate mould (1) is sealed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911289316.6A CN111122316B (en) | 2019-12-13 | 2019-12-13 | Device for eliminating residual stress of aviation metal part and examining aging performance |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911289316.6A CN111122316B (en) | 2019-12-13 | 2019-12-13 | Device for eliminating residual stress of aviation metal part and examining aging performance |
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| CN111122316A CN111122316A (en) | 2020-05-08 |
| CN111122316B true CN111122316B (en) | 2022-11-18 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4730474A (en) * | 1985-04-01 | 1988-03-15 | Hitachi, Ltd. | Method of relieving residual stress in metal pipe |
| CN103091162A (en) * | 2013-01-10 | 2013-05-08 | 河北省首钢迁安钢铁有限责任公司 | Method for measuring prescribed total elongation strength Rt value of hot rolled coil |
| CN103691793A (en) * | 2013-12-20 | 2014-04-02 | 中南大学 | One-step forming method of aging-strengthening aluminum alloy integral wall plate based on autoclave |
| CN109016563A (en) * | 2018-07-25 | 2018-12-18 | 西南交通大学 | A kind of device and method for eliminating residual stress of composites control curing deformation |
| CN209513479U (en) * | 2018-12-14 | 2019-10-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shear fatigue test part |
-
2019
- 2019-12-13 CN CN201911289316.6A patent/CN111122316B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4730474A (en) * | 1985-04-01 | 1988-03-15 | Hitachi, Ltd. | Method of relieving residual stress in metal pipe |
| CN103091162A (en) * | 2013-01-10 | 2013-05-08 | 河北省首钢迁安钢铁有限责任公司 | Method for measuring prescribed total elongation strength Rt value of hot rolled coil |
| CN103691793A (en) * | 2013-12-20 | 2014-04-02 | 中南大学 | One-step forming method of aging-strengthening aluminum alloy integral wall plate based on autoclave |
| CN109016563A (en) * | 2018-07-25 | 2018-12-18 | 西南交通大学 | A kind of device and method for eliminating residual stress of composites control curing deformation |
| CN209513479U (en) * | 2018-12-14 | 2019-10-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of shear fatigue test part |
Non-Patent Citations (1)
| Title |
|---|
| 大直径直缝埋弧焊管成形过程对毛坯板机械性能的影响;蔡星周;《中国优秀博硕士学位论文全文数据库(博士)工程科技Ⅰ辑》;20141215(第12期);第5、16-19页 * |
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