CN112179794B - Device for testing fatigue strength of tenon root of composite material blade - Google Patents
Device for testing fatigue strength of tenon root of composite material blade Download PDFInfo
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- CN112179794B CN112179794B CN202011033283.1A CN202011033283A CN112179794B CN 112179794 B CN112179794 B CN 112179794B CN 202011033283 A CN202011033283 A CN 202011033283A CN 112179794 B CN112179794 B CN 112179794B
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- 239000002131 composite material Substances 0.000 title claims abstract description 90
- 238000012360 testing method Methods 0.000 title claims abstract description 36
- 238000001514 detection method Methods 0.000 claims abstract description 14
- 238000012544 monitoring process Methods 0.000 claims description 13
- 238000009659 non-destructive testing Methods 0.000 claims description 8
- 238000004891 communication Methods 0.000 claims description 2
- 230000032798 delamination Effects 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 8
- 230000003068 static effect Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000012812 general test Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
- 238000009864 tensile test Methods 0.000 description 1
Classifications
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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
- G01N3/32—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces
- G01N3/36—Investigating strength properties of solid materials by application of mechanical stress by applying repeated or pulsating forces generated by pneumatic or hydraulic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
Abstract
The invention provides a device for testing the fatigue strength of the tenon root of a composite material blade, which comprises the following components: the method comprises the steps of placing the tenons of the to-be-tested composite material blade in the tenon fixing groove, attaching the tenon fixing groove to the tenon sizes of the to-be-tested composite material blade, applying combined force load to the composite material blade tenon through the radial force application tool by the radial force application shaft and the circumferential force application shaft, carrying out real-time internal layering and damage detection of the tenon through the nondestructive detection unit, and testing the fatigue resistance of the blade tenon.
Description
Technical Field
The invention belongs to the technical field of blade fatigue strength testing, relates to a blade tenon root fatigue strength testing device, and particularly relates to a composite material blade tenon root fatigue strength testing device, which adopts an equivalent method to realize static loading research and load adjustment aiming at a composite material tenon root structure, and realizes independent and combined application of radial and circumferential loads, thereby more accurately reflecting the static load and alternating load conditions born by a tenon root.
Background
The composite material fan blade can greatly reduce the whole body of an aeroengine, is widely applied to a large bypass ratio engine, the tenon of the composite material fan blade is also often manufactured and formed integrally by composite materials, the centrifugal load and the aerodynamic force in the rotation process of the blade are required to bear the aerodynamic load of the blade, the blade is a relatively weak position in the blade, the strength test is required, however, the integral blade profile of the composite material blade (particularly the wide chord composite material large blade) is highly distorted in space, the loading of the load on the blade body cannot be realized in the actual static test, therefore, the general test method mainly comprises the steps of installing the blade in a rotating device, observing whether the tenon is damaged or broken through high-speed rotation, and the high-speed rotation test has high cost, and the integral test has dangerousness and cannot realize the real-time test of the tenon strength; the traditional composite material fan blade static mechanical testing device can only simulate a simple one-way load loading process of the blade, but can not accurately simulate real and complex loads under the working condition of the blade.
In the related art, a blade tensile testing machine is studied, which can conveniently center a blade test piece before the blade test piece is subjected to tension loading, and can improve the detection precision of the tension loading of the blade, but the method can only simulate the influence of centrifugal force applied to the blade in the high-speed running process on the radial direction of a tenon root, but cannot simulate the comprehensive extrusion effect in other directions; in the related art, a blade torsion test device can realize test research of a small torsion angle of a blade by converting a torsion chuck through an arc-shaped guide rail, but the structure cannot comprehensively simulate complex stress received by a tenon root of a composite material fan blade; in the related art, there is a blade fatigue performance testing machine, which can apply loads in three directions to a blade and adjust the loads, and can simulate various loads such as static tension of centrifugal force, but the device cannot focus and accurately simulate complex acting force applied to a tenon.
As the demand for composite fan blades by power equipment continues to rise, it is necessary to provide a device for testing the dovetail fatigue strength of composite blades.
Disclosure of Invention
In view of the above-mentioned shortcomings and problems of the prior art, the present invention aims to provide a device for testing fatigue strength of a dovetail root of a composite blade, wherein the device is used for testing fatigue strength of a dovetail root of a composite blade by placing a composite blade in a dovetail root fixing groove, the dovetail root fixing groove is attached to the size of the dovetail root of the composite blade, a radial load applying shaft and a circumferential load applying shaft apply combined force load to the dovetail root of the composite blade through a force applying tool, real-time internal layering and damage detection of the dovetail root are performed through a nondestructive detection system, and the fatigue strength of the dovetail root of the blade is tested.
The invention adopts the technical proposal for solving the technical problems that:
a fatigue strength testing device for a composite blade dovetail, comprising: the tenon root fixing groove, the radial load applying shaft, the circumferential load applying block, the radial force applying tool and the surface strain monitoring unit are characterized in that,
the dovetail mounting groove comprises a bottom wall and a side wall fixedly disposed or integrally formed on the bottom wall, wherein,
the bottom wall is provided with a recess matched with the bottom of the radial force application tool, the radial force application tool is arranged in the recess, the bottom of the recess is provided with a through hole extending along the vertical direction, and the radial load application shaft is movably arranged in the through hole along the vertical direction and the top of the radial load application shaft is propped against the bottom of the radial force application tool;
the side wall is positioned at one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon of the composite material blade to be tested;
the other side of the recess is provided with the circumferential load applying block on the bottom wall, and the inner wall of the circumferential load applying block is matched with the other side face of the tenon of the composite material blade to be tested;
the tenon fixing groove, the circumferential load applying block and the radial force applying tool are mutually matched to form a tenon groove, the tenon of the to-be-tested composite material blade is fixedly arranged in the tenon groove, and the circumferential load applying block and the radial load applying shaft are used for respectively applying circumferential load and radial load to the tenon of the to-be-tested composite material blade;
the surface strain monitoring unit is arranged in the tenon root fixing groove and/or the circumferential load applying block and is in contact with the tenon root surface of the to-be-tested composite material blade, so as to detect the deformation condition of the tenon root surface of the to-be-tested composite material blade in real time.
Optionally, the device further comprises a nondestructive testing unit, the nondestructive testing unit is in communication connection with the surface strain monitoring unit, real-time internal layering and damage detection of the tenon root are carried out through the nondestructive testing system, and fatigue strength of the tenon root of the blade is tested.
When the device for testing the fatigue strength of the tenon of the composite material blade is used, the tenon of the composite material blade to be tested is placed in the tenon fixing groove, the tenon fixing groove is attached to the shape and the size of the tenon of the composite material blade to be tested, the radial load applying shaft and the circumferential load applying block apply combined force load to the tenon of the composite material blade to be tested so as to simulate the application condition of actual load, the deformation condition of the surface of the tenon of the composite material blade to be tested is detected in real time through the surface strain monitoring unit, the real-time internal layering and damage detection of the tenon are carried out through the nondestructive detection unit, and the fatigue strength of the tenon of the blade is tested.
Optionally, the surface strain monitoring unit is used for detecting the deformation condition of the tenon root of the composite material blade at the joint of the tenon root fixing groove in real time.
Optionally, the radial load applying shaft and the circumferential load applying block apply load in a hydraulic or motor driving mode, and the magnitude and frequency of the applied load are adjustable.
Optionally, the circumferential load applying block is rotatable, thereby enabling adjustment of the direction of the applied force.
Optionally, the radial load applying shaft and the circumferential load applying shaft are combined to simulate the application of an actual load.
Optionally, the top surface of the radial force application tool is a plane or a complex curved surface so as to simulate different actual working conditions.
Optionally, the testing device comprises a nondestructive testing unit to observe internal layering and damage of the tenon root in real time.
Optionally, the inner wall of the circumferential load applying block is set to be a convex array, a free curved surface or a plane structure, so as to simulate different wall conditions possibly faced by the tenon root of the to-be-tested composite material blade in the mortise, and study the influence of the different wall conditions on the tenon root fatigue resistance of the to-be-tested composite material blade. Compared with the prior art, the invention has the beneficial effects that:
1-realizing a static loading test aiming at a composite material tenon root structure so as to be compared with a complex loading condition during high-speed movement, and realizing low-cost simulation of complex running load;
2-can realize the adjustable of tenon root portion load, realize including radial and circumference load is exerted alone and the combination, more accurately reflect the dead load, the alternating load condition that receive of tenon root department to accomplish accurate combined material blade tenon root fatigue strength test.
Drawings
FIG. 1 is a schematic diagram of a composite blade dovetail fatigue strength testing device according to the present invention;
FIG. 2 is a side view of a composite blade dovetail fatigue strength testing device of the present invention;
FIG. 3 is a cross-sectional view A-A of the composite blade dovetail fatigue strength testing device of the present invention;
FIG. 4 is a schematic representation of a composite blade dovetail force load;
FIG. 5 is a schematic representation of composite blade dovetail force load synthesis;
FIG. 6 is a schematic view of a circumferential load applying block structure;
FIG. 7 is a schematic illustration of circumferential load applying block position adjustment;
in the figure, a tenon fixing groove 1, a tenon 2 of a composite material blade to be tested, a surface strain monitoring unit 3, a radial load applying shaft 4, a circumferential load applying block 5, a radial force applying tool 6 and a nondestructive detection unit 7.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. The following describes the structure and technical scheme of the present invention in detail with reference to the accompanying drawings, and an embodiment of the present invention is given.
As shown in figures 1 and 2, the device for testing the fatigue strength of the tenons of the composite material blade comprises a tenon fixing groove 1, tenons 2 of the composite material blade to be tested, a surface strain monitoring unit 3, a radial load applying shaft 4, a circumferential load applying block 5, a radial force applying tool 6 and a nondestructive testing unit 7. The tenon fixing groove 1 comprises a bottom wall and a side wall fixedly arranged or integrally formed on the bottom wall, a recess matched with the bottom of the radial force application tool 6 is formed in the bottom wall, the radial force application tool 6 is arranged in the recess, a through hole extending along the vertical direction is formed in the bottom of the recess, and the radial load application shaft 4 is movably arranged in the through hole along the vertical direction and the top of the radial load application shaft abuts against the bottom of the radial force application tool 6. The side wall is positioned at one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon 2 of the composite material blade to be tested; on the other side of the recess, a circumferential load applying block 5 is arranged on the bottom wall, and the inner wall of the circumferential load applying block 5 is matched with the other side face of the tenon 2 of the composite material blade to be tested. The tenon fixing groove 1, the circumferential load applying block 5 and the radial force applying tool 6 are mutually matched to form a tenon groove, the tenon 2 of the to-be-tested composite material blade is fixedly arranged in the tenon groove, and the circumferential load applying block 5 and the radial load applying shaft 4 are used for respectively applying circumferential load and radial load to the tenon 2 of the to-be-tested composite material blade. The surface strain monitoring unit 3 is arranged in the tenon root fixing groove 1 and/or the circumferential load applying block 5, is contacted with the surface of the tenon root 2 of the to-be-tested composite material blade, and is used for detecting the deformation condition of the tenon root surface of the to-be-tested composite material blade in real time.
When the device for testing the fatigue strength of the tenons of the composite material blades is used, the tenons 2 of the composite material blades to be tested are placed in the tenon fixing grooves 1, the tenons 2 of the composite material blades to be tested are tightly fixed through the radial force application tool 6 by adjusting the radial load application shaft 4 and the circumferential load application block 5, different combined inner effects are formed by combining the radial load application shaft 4 and the circumferential load application block 5, and the device is applied to the tenons 2 of the composite material blades to be tested and is used for simulating the circumferential and radial centrifugal loads and the pneumatic loads suffered by the tenons of the composite material blades in the actual running process. The integrated structure formed by the tenon fixing groove 1, the tenon 2 of the to-be-tested composite material blade, the surface strain monitoring unit 3, the radial load applying shaft 4, the circumferential load applying block 5 and the radial force applying tool 6 is fixed on a detection platform of the nondestructive detection unit 7 through screws, and the real-time internal layering and damage detection of the tenon is performed through the development of the nondestructive detection unit 7, so that the fatigue strength and the real-time internal state of the tenon of the composite material blade are tested. The radial load applying shaft 4 and the circumferential load applying block 5 can be driven by hydraulic pressure or by a motor, so that the frequency and the magnitude of the applied force can be controlled. The radial load applying shaft 4 does not directly act on the composite material blade 2, but indirectly acts on the tenon root 2 of the composite material blade to be tested through the middle radial force applying tool 6, so that the simulated centrifugal load borne by the tenon root 2 of the composite material blade to be tested is closer to the actual condition, and the more complex actual working condition can be simulated by adjusting the structure of the contact position of the radial force applying tool 6 and the composite material blade 2.
As shown in fig. 2 and 3, the tenon 2 of the to-be-tested composite blade is fixed in a tenon groove formed by a tenon fixing groove 1, a radial load applying shaft 4, a circumferential load applying block 5 and a radial force applying tool 6, the applied force load angle of the circumferential load applying block 5 can be adjusted, and a surface strain monitoring unit 3 is installed in the tenon fixing groove 1 and the circumferential load applying block 5 and is used for detecting the deformation condition of the surface of the tenon 2 of the composite blade in contact with the surface of the tenon groove in real time.
As shown in fig. 4 and 5, the dovetail root 2 of the to-be-tested composite blade is fixed in a dovetail root fixing groove 1, a radial load applying shaft 4, a circumferential load applying block 5 and a force applying tool 6, and the radial load applying shaft 4 applies a radial force load F2 simulating centrifugal load to the dovetail root 2 of the to-be-tested composite blade through the radial force applying tool 6. The circumferential load applying block 5 applies circumferential force loads F1 simulating other loads to the tenon root 2 of the composite material blade to be tested, different loads F0 can be simulated by adjusting the frequency and the magnitude of the applied loads of the radial load applying shaft 4 and the circumferential load applying block 5 and adjusting the acting direction of the circumferential load applying block 5, and the fatigue strength of the tenon root 2 of the composite material blade can be tested more realistically. Wherein F2 is the force load applied by the radial load applying shaft, F1 is the force load applied by the circumferential load applying shaft, F0 is the comprehensive force load applied by the blade tenon root, and as F1 and F2, various alternating loads applied by the composite blade in a practical complex running environment can be simulated by adjusting angles, directions and the magnitudes and frequencies of the forces, and the fatigue strength of the composite blade tenon root is tested based on the states.
As shown in fig. 6, the surface of the circumferential load applying block 5 contacting the dovetail root 2 of the composite material blade to be tested may be designed into different structures, including but not limited to, a convex array, a free-form surface, and a plane, so as to simulate different wall conditions that the dovetail root 2 of the composite material blade to be tested may face in the dovetail groove, and study the influence of the different wall conditions on the fatigue resistance of the dovetail root 2 of the composite material blade to be tested.
As shown in fig. 7, the circumferential load applying block 5 can be used for simulating radial force loads in different directions by adjusting the relative angle with the dovetail fixing groove 1, so that the accurate study on the stress performance of the dovetail 2 of the composite blade is realized.
The object of the present invention is fully effectively achieved by the above-described embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, those illustrated in the drawings and described in the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the scope of the appended claims.
Claims (4)
1. A fatigue strength testing device for a composite blade dovetail, comprising: the tenon root fixing groove, the radial load applying shaft, the circumferential load applying block, the radial force applying tool and the surface strain monitoring unit are characterized in that,
the tenon fixing groove comprises a bottom wall and a side wall fixedly arranged or integrally formed on the bottom wall, wherein,
the bottom wall is provided with a recess matched with the bottom of the radial force application tool, the radial force application tool is arranged in the recess, the bottom of the recess is provided with a through hole extending along the vertical direction, and the radial load application shaft is movably arranged in the through hole along the vertical direction and the top of the radial load application shaft is propped against the bottom of the radial force application tool;
the side wall is positioned at one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon of the to-be-tested composite material blade;
the other side of the recess is provided with the circumferential load applying block, the inner wall of the circumferential load applying block is matched with the other side face of the tenon root of the to-be-tested composite material blade, the circumferential load applying block is rotatable, so that the direction of applied force can be adjusted, the inner wall of the circumferential load applying block is provided with a convex array, a free curved surface or a plane structure, different wall conditions possibly faced by the tenon root of the to-be-tested composite material blade in a tenon groove are simulated, and the influence of the different wall conditions on the tenon root fatigue resistance of the to-be-tested composite material blade is studied;
the tenon fixing groove, the circumferential load applying block and the radial force applying tool are mutually matched to form a tenon groove, the tenon of the to-be-tested composite material blade is fixedly arranged in the tenon groove, and the circumferential load applying block and the radial load applying shaft are used for respectively applying circumferential load and radial load to the tenon of the to-be-tested composite material blade;
the surface strain monitoring unit is arranged in the tenon root fixing groove and/or the circumferential load applying block, is contacted with the tenon root surface of the to-be-tested composite material blade, and is used for detecting the deformation condition of the tenon root surface of the to-be-tested composite material blade in real time;
when the fatigue strength testing device is used, the tenon root of the to-be-tested composite material blade is placed in the tenon root fixing groove, the tenon root fixing groove is attached to the tenon root of the to-be-tested composite material blade in shape and size, and the radial load applying shaft and the circumferential load applying block apply combined force load to the tenon root of the to-be-tested composite material blade so as to simulate the application condition of actual load.
2. The device for testing the fatigue strength of the tenon root of the composite material blade according to claim 1, wherein the device further comprises a nondestructive testing unit, the nondestructive testing unit is in communication connection with the surface strain monitoring unit, and real-time internal delamination and damage detection of the tenon root are carried out through the nondestructive testing unit, so that the fatigue strength of the tenon root of the blade is tested.
3. The device for testing the fatigue strength of the tenon root of the composite blade according to claim 1, wherein the radial load applying shaft and the circumferential load applying block apply load in a hydraulic or motor driving mode, and the magnitude and the frequency of the applied load are adjustable.
4. The device for testing the fatigue strength of the tenon of the composite blade according to claim 1, wherein the top surface of the radial force application tool is set to be a plane or a complex curved surface so as to simulate different actual working conditions.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202011033283.1A CN112179794B (en) | 2020-09-27 | 2020-09-27 | Device for testing fatigue strength of tenon root of composite material blade |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011033283.1A CN112179794B (en) | 2020-09-27 | 2020-09-27 | Device for testing fatigue strength of tenon root of composite material blade |
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| CN112179794A CN112179794A (en) | 2021-01-05 |
| CN112179794B true CN112179794B (en) | 2023-11-21 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6250166B1 (en) * | 1999-06-04 | 2001-06-26 | General Electric Company | Simulated dovetail testing |
| GB2472193A (en) * | 2009-07-27 | 2011-02-02 | Rolls Royce Plc | Rotor blade test specimen |
| CN106768755A (en) * | 2016-11-28 | 2017-05-31 | 中航动力股份有限公司 | A kind of fixture integrated and test method for swallow-tail form tenon turbine blade vibration fatigue test |
| CN208614623U (en) * | 2018-08-02 | 2019-03-19 | 成都工贸职业技术学院 | High-pressure compressor blade dovetail tenon clamping fixture |
| CN110389024A (en) * | 2019-06-17 | 2019-10-29 | 浙江大学 | A kind of all composite fatigue experimental rigs of turbine engine rotor mortise structure height and method |
| FR3084161A1 (en) * | 2018-07-23 | 2020-01-24 | Safran Aircraft Engines | ASSEMBLY OF TEST, AND TEST MACHINE IN FATIGUE VIBRATORY. |
-
2020
- 2020-09-27 CN CN202011033283.1A patent/CN112179794B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6250166B1 (en) * | 1999-06-04 | 2001-06-26 | General Electric Company | Simulated dovetail testing |
| GB2472193A (en) * | 2009-07-27 | 2011-02-02 | Rolls Royce Plc | Rotor blade test specimen |
| CN106768755A (en) * | 2016-11-28 | 2017-05-31 | 中航动力股份有限公司 | A kind of fixture integrated and test method for swallow-tail form tenon turbine blade vibration fatigue test |
| FR3084161A1 (en) * | 2018-07-23 | 2020-01-24 | Safran Aircraft Engines | ASSEMBLY OF TEST, AND TEST MACHINE IN FATIGUE VIBRATORY. |
| CN208614623U (en) * | 2018-08-02 | 2019-03-19 | 成都工贸职业技术学院 | High-pressure compressor blade dovetail tenon clamping fixture |
| CN110389024A (en) * | 2019-06-17 | 2019-10-29 | 浙江大学 | A kind of all composite fatigue experimental rigs of turbine engine rotor mortise structure height and method |
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