CN112179794A - Fatigue strength testing device for tenon root of composite material blade - Google Patents
Fatigue strength testing device for tenon root of composite material blade Download PDFInfo
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- CN112179794A CN112179794A CN202011033283.1A CN202011033283A CN112179794A CN 112179794 A CN112179794 A CN 112179794A CN 202011033283 A CN202011033283 A CN 202011033283A CN 112179794 A CN112179794 A CN 112179794A
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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 37
- 238000012544 monitoring process Methods 0.000 claims abstract description 14
- 238000009659 non-destructive testing Methods 0.000 claims description 9
- 230000032798 delamination Effects 0.000 claims description 3
- 230000003068 static effect Effects 0.000 abstract description 10
- 238000001514 detection method Methods 0.000 abstract description 9
- 238000000034 method Methods 0.000 abstract description 8
- 238000011160 research Methods 0.000 abstract description 5
- 230000002929 anti-fatigue Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001125 extrusion Methods 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
- 238000009864 tensile test Methods 0.000 description 1
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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
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- 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
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- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a composite material blade tenon root fatigue strength testing device, which comprises: the utility model provides a composite material tenon root structure, including tenon root fixed slot, surface strain monitoring unit, the axle is applyed to radial load, the piece is applyed to circumference load, radial force application frock, nondestructive test unit, the tenon root of the composite material blade that awaits measuring is placed in the tenon root fixed slot, the tenon root fixed slot is laminated with the tenon root size of the composite material blade that awaits measuring, the axle is applyed to radial load, the axle is applyed to circumference load applys the combined force load to the composite material blade tenon root through radial force application frock, develop the real-time internal layering and the damage detection of tenon root through the nondestructive test unit, the antifatigue strength of test blade tenon root, this scheme can adopt equivalent method to realize static loading research and load adjustment to the composite material tenon root structure, realize exerting alone and the combination including radial and circumference load, the static load that more accurate reflection tenon root.
Description
Technical Field
The invention belongs to the technical field of blade fatigue strength testing, and relates to a blade tenon root fatigue strength testing device, in particular to a composite material blade tenon root fatigue strength testing device, which realizes static loading research and load adjustment aiming at a composite material tenon root structure by adopting an equivalent method, realizes independent and combined application of radial and circumferential loads, and more accurately reflects the conditions of static load and alternating load borne by a tenon root.
Background
The composite material fan blade can greatly reduce the whole of an aircraft engine and is widely applied to engines with large bypass ratio, the tenon root of the composite material fan blade is often integrally manufactured and formed by composite materials, the pneumatic load of centrifugal load and aerodynamic force on the blade in the rotating process of the blade needs to be borne, the blade is a relatively weak position in the blade, and the strength needs to be tested; the traditional static mechanical testing device for the composite material fan blade can only simulate a simple unidirectional blade load loading process, but cannot accurately simulate real and complex loads under the working condition of the blade.
In the related art, a blade tensile testing machine is researched, which can conveniently center a blade test piece before the blade test piece is subjected to tensile loading, and can improve the detection precision of the tensile load of the blade, but the method can only simulate the influence of centrifugal force on 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 convert a torsion chuck through an arc-shaped guide rail to realize the test research of a small torsion angle of a blade, but the structure cannot comprehensively simulate the complex stress received by the tenon root of the composite material fan blade; in the related art, there is a blade fatigue performance testing machine capable of applying loads in three directions to a blade and adjusting the loads, and capable of simulating various loads such as static tension of centrifugal force, but the device cannot focus and accurately simulate a complex acting force applied to a tenon.
As the demand of power equipment for composite material fan blades is continuously increased, it is necessary to provide a device for testing the fatigue strength of the tenon root of the composite material fan blade.
Disclosure of Invention
In view of the above-mentioned drawbacks and problems of the prior art, the present invention is directed to a fatigue strength testing apparatus for a composite blade tenon root, the composite material blade is placed in the tenon root fixing groove, the tenon root fixing groove is in fit with the tenon root of the composite material blade in size, the radial load applying shaft and the circumferential load applying shaft apply combined force load to the tenon root of the composite material blade through the force application tool, the scheme can adopt an equivalent method to realize static loading research and load adjustment aiming at the structure of the composite material tenon root, realize single and combined application of radial and circumferential loads, and more accurately reflect the conditions of static load and alternating load borne by the tenon root, thereby at least partially solving one of the technical problems mentioned in the background technology.
The technical scheme adopted by the invention for solving the technical problem is as follows:
a fatigue strength testing device for a composite material blade tenon root comprises: a tenon root fixing groove, a radial load applying shaft, a circumferential load applying block, a radial force applying tool and a surface strain monitoring unit,
-said tongue-and-groove comprises a bottom wall and a side wall fixedly arranged or integrally formed on said bottom wall, wherein,
a recess matched with the bottom of the radial force application tool is formed in the bottom wall, the radial force application tool is arranged in the recess, a through hole extending along the vertical direction is formed in the bottom of the recess, 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 abuts against the bottom of the radial force application tool;
the side wall is positioned on one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon root of the composite material blade to be detected;
the circumferential load applying block is arranged on the bottom wall of the other side of the recess, and the inner wall of the circumferential load applying block is matched with the other side face of the tenon root of the composite material blade to be tested;
the tenon root fixing groove, the circumferential load applying block and the radial force applying tool are matched with each other to form a tenon groove, the tenon root of the composite material blade to be tested is fixedly arranged in the tenon groove, and the circumferential load applying block and the radial load applying shaft are used for applying circumferential load and radial load to the tenon root of the composite material blade to be tested respectively;
the surface strain monitoring unit is disposed in the tenon root fixing groove and/or the circumferential load applying block, and is in contact with the tenon root surface of the composite material blade to be detected, so as to detect the deformation of the tenon root surface of the composite material blade to be detected 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, and the nondestructive testing system is used for carrying out real-time internal delamination and damage detection on the tenon root and testing the fatigue strength of the blade tenon root.
When the fatigue strength testing device for the tenon root of the composite material blade is used, the tenon root of the composite material blade to be tested is placed in the tenon root fixing groove, the shape and the size of the tenon root fixing groove are fitted with those of the tenon root of the composite material blade to be tested, the radial load applying shaft and the circumferential load applying block apply combined force loads to the tenon root of the composite material blade to be tested so as to simulate the application condition of an actual load, the deformation condition of the surface of the tenon root of the composite material blade to be tested is detected in real time through the surface strain monitoring unit, and the real-time internal layering and damage detection of the tenon root is carried out through the nondestructive detection unit so as to test the fatigue strength of the tenon root of the.
Optionally, the surface strain monitoring unit is used for detecting the tenon root deformation condition of the composite material blade attached to the tenon root fixing groove in real time.
Optionally, the radial load applying shaft and the circumferential load applying block apply a load in a hydraulic or motor driving manner, 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 application axis and the circumferential load application axis 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 to simulate different practical conditions.
Optionally, the testing device comprises a nondestructive testing unit to observe internal delamination and damage conditions of the tenon root in real time.
Optionally, the inner wall of the circumferential load applying block is arranged to be a convex array, a free-form surface or a planar structure so as to simulate different wall conditions that the tenon root of the composite material blade to be tested may face in the mortise and study the influence of the different wall conditions on the fatigue resistance of the tenon root of the composite material blade to be tested. Compared with the prior art, the invention has the beneficial effects that:
1-realizing a static loading test aiming at a tenon root structure of a composite material to compare with a complex loading condition of the tenon root structure in high-speed motion and realize low-cost simulation of complex operation load;
2, the load of the tenon root can be adjusted, the radial load and the circumferential load are applied independently and in combination, and the static load and alternating load conditions borne by the tenon root are reflected more accurately, so that the fatigue strength test of the tenon root of the composite material blade is completed accurately.
Drawings
FIG. 1 is a schematic structural view of a composite material blade tenon root fatigue strength testing device of the present invention;
FIG. 2 is a side view of the composite blade dovetail fatigue strength testing apparatus of the present invention;
FIG. 3 is a sectional view A-A of the composite blade dovetail fatigue strength testing apparatus of the present invention;
FIG. 4 is a schematic illustration of a composite blade dovetail force load;
FIG. 5 is a composite blade dovetail force loading diagram;
FIG. 6 is a schematic view of a circumferential load applying block configuration;
FIG. 7 is a schematic view of circumferential load application block position adjustment;
in the figure, a tenon root fixing groove 1, a tenon root 2 of a composite material blade to be detected, 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 are arranged.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, 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 only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. 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. The structure and technical scheme of the present invention are further described in detail with reference to the accompanying drawings, and an embodiment of the present invention is provided.
As shown in fig. 1 and 2, the composite material blade tenon root fatigue strength testing device comprises a tenon root fixing groove 1, a tenon root 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 application tool 6 and a nondestructive testing unit 7. The tenon root fixing groove 1 comprises a bottom wall and a side wall fixedly arranged on the bottom wall 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 in the vertical direction is formed in the bottom of the recess, the radial load application shaft 4 is movably arranged in the through hole in 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 on one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon root 2 of the composite material blade to be tested; and a circumferential load applying block 5 is arranged on the bottom wall of the other side of the recess, and the inner wall of the circumferential load applying block 5 is matched with the other side surface of the tenon root 2 of the composite material blade to be tested. The tenon root fixing groove 1, the circumferential load applying block 5 and the radial force application tool 6 are matched with each other to form a tenon groove, the tenon root 2 of the composite material blade to be tested is fixedly arranged in the tenon groove, and the circumferential load applying block 5 and the radial load applying shaft 4 are used for applying circumferential load and radial load to the tenon root 2 of the composite material blade to be tested respectively. The surface strain monitoring unit 3 is arranged in the tenon root fixing groove 1 and/or the circumferential load applying block 5, is in contact with the surface of the tenon root 2 of the composite material blade to be detected, and is used for detecting the deformation condition of the tenon root surface of the composite material blade to be detected in real time.
When the composite material blade tenon root fatigue strength testing device is used, the tenon root 2 of a composite material blade to be tested is placed in the tenon root fixing groove 1, the tenon root 2 of the composite material blade to be tested is tightly fixed through adjusting the radial load applying shaft 4 and the circumferential load applying block 5 through the radial force application tool 6, different combination internal effects are formed through combining the radial load applying shaft 4 and the circumferential load applying block 5, and the combined radial load applying shaft and the circumferential load applying block are applied to the tenon root 2 of the composite material blade to be tested and used for simulating circumferential and radial centrifugal loads and pneumatic loads applied to the tenon root in the actual operation process of the composite material blade. The integral structure formed by the tenon root fixing groove 1, the tenon root 2 of the composite material blade to be tested, the surface strain monitoring unit 3, the radial load applying shaft 4, the circumferential load applying block 5 and the radial force application tool 6 is fixed on a detection platform of the nondestructive detection unit 7 through screws, and the fatigue strength and the real-time internal state of the tenon root of the composite material blade are tested by the real-time internal layering and damage detection of the tenon root unfolded by the nondestructive detection unit 7. The radial load applying shaft 4 and the circumferential load applying block 5 can be driven by hydraulic pressure or a motor, and 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 application 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 complicated actual condition can be simulated by adjusting the structure of the contact position of the radial force application tool 6 and the composite material blade 2.
As shown in fig. 2 and 3, the tenon root 2 of the composite material blade to be tested is fixed in a tenon groove formed by a tenon root fixing groove 1, a radial load applying shaft 4, a circumferential load applying block 5 and a radial force applying tool 6, the force applying load angle of the circumferential load applying block 5 can be adjusted, and the surface strain monitoring unit 3 is installed in the tenon root fixing groove 1 and the circumferential load applying block 5 and is used for detecting the deformation condition of the surface of the tenon root 2 of the composite material blade in contact with the surface of the tenon groove in real time.
As shown in fig. 4 and 5, the tenon root 2 of the composite material blade to be tested is fixed in a tenon groove formed by the tenon root fixing groove 1, the radial load applying shaft 4, the circumferential load applying block 5 and the force applying tool 6, and the radial load applying shaft 4 applies a radial force load F2 simulating a centrifugal load to the tenon root 2 of the composite material blade to be tested through the radial force applying tool 6. The circumferential load applying block 5 applies circumferential force load 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 size of the force loads applied by 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 vividly. The F2 is the force load applied by the radial load applying shaft, the F1 is the force load applied by the circumferential load applying shaft, the F0 is the comprehensive force load applied by the blade tenon root, and along with the F1 and the F2, various alternating loads applied to the composite material blade in an actual complex operation environment can be simulated by adjusting the angle, the direction, the force magnitude and the frequency, and the fatigue strength of the composite material blade tenon root is tested based on the state.
As shown in fig. 6, different structures can be designed on the surface of the circumferential load applying block 5, which is in contact with the tenon root 2 of the composite material blade to be tested, wherein the structures include, but are not limited to, a protrusion array, a free-form surface and a plane, so as to simulate different wall conditions that the tenon root 2 of the composite material blade to be tested may face in a mortise, and study the influence of the different wall conditions on the fatigue resistance of the tenon 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 a relative angle with the tenon root fixing groove 1, so as to realize accurate research on the force bearing performance of the composite material blade tenon root 2.
The object of the present invention is fully effectively achieved by the above embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and 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 to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications within the spirit and scope of the appended claims.
Claims (6)
1. A fatigue strength testing device for a composite material blade tenon root comprises: a tenon root fixing groove, a radial load applying shaft, a circumferential load applying block, a radial force applying tool and a surface strain monitoring unit,
-said tongue-and-groove comprises a bottom wall and a side wall fixedly arranged or integrally formed on said bottom wall, wherein,
a recess matched with the bottom of the radial force application tool is formed in the bottom wall, the radial force application tool is arranged in the recess, a through hole extending along the vertical direction is formed in the bottom of the recess, 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 abuts against the bottom of the radial force application tool;
the side wall is positioned on one side of the recess, and the inner wall of the side wall is matched with one side surface of the tenon root of the composite material blade to be detected;
the circumferential load applying block is arranged on the bottom wall of the other side of the recess, and the inner wall of the circumferential load applying block is matched with the other side face of the tenon root of the composite material blade to be tested;
the tenon root fixing groove, the circumferential load applying block and the radial force applying tool are matched with each other to form a tenon groove, the tenon root of the composite material blade to be tested is fixedly arranged in the tenon groove, and the circumferential load applying block and the radial load applying shaft are used for applying circumferential load and radial load to the tenon root of the composite material blade to be tested respectively;
the surface strain monitoring unit is disposed in the tenon root fixing groove and/or the circumferential load applying block, and is in contact with the tenon root surface of the composite material blade to be detected, so as to detect the deformation of the tenon root surface of the composite material blade to be detected in real time.
2. The apparatus for testing fatigue strength of a blade tenon root of composite material as claimed in the preceding claim, further comprising a nondestructive testing unit communicatively connected to the surface strain monitoring unit, wherein the nondestructive testing unit is configured to perform real-time internal delamination and damage testing of the tenon root by the nondestructive testing system, thereby testing the fatigue strength of the blade tenon root.
3. The device for testing the fatigue strength of the composite material blade tenon root according to the previous claim, wherein the radial load applying shaft and the circumferential load applying block apply loads in a hydraulic or motor-driven manner, and the magnitude and the frequency of the applied loads are adjustable.
4. A fatigue strength testing device for a composite material blade dovetail according to the previous claim, wherein said circumferential load applying block is rotatable, thereby enabling adjustment of the direction of the applied force.
5. The composite material blade tenon root fatigue strength testing device of the preceding claim, wherein the top surface of the radial force application tool is a plane or a complex curved surface to simulate different practical conditions.
6. The device for testing the fatigue strength of the tenon root of the composite material blade as claimed in the preceding claim, wherein the inner wall of the circumferential load applying block is configured to be a convex array, a free-form surface or a planar structure so as to simulate different wall conditions which the tenon root of the composite material blade to be tested may face in the mortise and study the influence of the different wall conditions on the fatigue resistance of the tenon root of the composite material blade to be tested.
Priority Applications (1)
| 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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| 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 true CN112179794A (en) | 2021-01-05 |
| CN112179794B 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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| CN112179794B (en) | 2023-11-21 |
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