CN114441122A - Vibration fatigue test device and method for composite material fan blade - Google Patents
Vibration fatigue test device and method for composite material fan blade Download PDFInfo
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a vibration fatigue test device and a test method for a composite material fan blade. The vibration fatigue test device for the composite material fan blade comprises a vibrating table and a clamp, wherein the vibrating table is used for providing an excitation source for vibration of the test blade, the clamp is arranged on the vibrating table and comprises a clamp body and an upper pressure top block, the clamp body is provided with a clamping cavity for clamping and fixing a tenon of the test blade, and the upper pressure top block is arranged at the bottom of the clamping cavity and tightly presses the bottom of the tenon of the test blade so that the side surface of the clamping cavity is attached to the working surfaces of the two sides of the tenon of the test blade. The vibration fatigue test device provided by the invention designs the clamp according to the shape of the tenon of the test blade, the clamp is designed to be of an upper-jacking type structure, so that the working surface of the clamp is attached and pressed with the working surfaces on two sides of the tenon of the test blade, the frequency of the test blade is not changed any more by continuously increasing the pressing force, and the pressing force of the clamp in the test is determined, so that the test blade is fixed.
Description
Technical Field
The invention relates to the field of blade tests, in particular to a vibration fatigue test device and a test method for a composite material fan blade.
Background
High thrust-weight ratio, low fuel consumption rate, low noise and low maintenance cost are the targets continuously pursued by the commercial large-scale aircraft, and reducing the weight of the turbofan engine with the large bypass ratio of the core component of the large-scale aircraft and improving the bypass ratio thereof are one of the main ways for realizing the targets. The fan blades are core parts of the turbofan engine with a large bypass ratio, and the weight of the fan blades is reduced, so that the weight of engine structures such as a fan casing and a transmission system and the weight of airplane structures such as airplane wings and an airplane body can be reduced in an iterative manner; by increasing the size of the engine, the bypass ratio of the engine can be effectively improved, the thrust of the engine is increased, and the thrust-weight ratio is improved. Therefore, the trend of the turbofan engine is to adopt larger and lighter fan blades, and the composite material fan blades with low density, high specific strength, high specific rigidity, good flutter resistance and strong damage tolerance capability become an effective way.
The problem of blade vibration is one of the difficult problems which puzzles the development and the service of an aeroengine, the composite material fan blade is no exception, and accidents of casualties caused by engine explosion due to fatigue fracture of the fan blade already exist in the civil aviation development history, so a series of vibration fatigue tests, crosswind tests and the like are required to be carried out for effectively evaluating and improving the vibration resistance of the composite material fan blade and prolonging the service time of the composite material fan blade. The vibration fatigue test is an effective means for verifying the vibration capability of the blade at the component level. The traditional vibration fatigue test method and system are mainly developed aiming at isotropic metal blades, the complete strain of the blades is difficult to obtain by the traditional mounting mode of the composite material fan blades due to the anisotropy of materials, the temperature needs to be monitored in real time and constant temperature measures are taken in the test because of the sensitivity of the composite materials to the temperature, the load level applied to the blades cannot be controlled by the traditional excitation control method of the high bending sweepness and the anisotropy of the strain of the blades, the universal vibration fatigue test fixture is not suitable due to the structural characteristics of the composite material blades, the accurate fatigue performance cannot be obtained by the traditional S-N (stress-cycle) curve of the anisotropy of the stress of the composite material blades, and in sum, the traditional vibration fatigue test device and method cannot be effectively applied to the vibration fatigue test of the composite material fan blades, new fatigue test methods and systems need to be designed for the characteristics of composite fan blades.
Disclosure of Invention
The invention aims to provide a device and a method for testing the vibration fatigue of a composite material fan blade, which are suitable for the vibration fatigue test of the composite material fan blade.
The invention provides a vibration fatigue test device for a composite material fan blade, which comprises:
the vibration table is used for providing an excitation source for the vibration of the test blade; and
the fixture is arranged on the vibrating table and comprises a fixture body and an upper ejector pad, the fixture body is provided with a clamping cavity used for clamping and fixing the tenon of the test blade, and the upper ejector pad is arranged at the bottom of the clamping cavity and tightly presses the bottom of the tenon of the test blade so that the side surface of the clamping cavity is attached to the working surfaces of the two sides of the tenon of the test blade.
In some embodiments, the vibration fatigue testing apparatus further comprises a suspension type shooting device and a control device, the suspension type shooting device is arranged above the blade tip of the test blade in a suspension mode and used for capturing the amplitude of the blade tip, and the control device is configured to receive the amplitude and control the action of the vibration table according to the amplitude.
In some embodiments, the control device is configured to plot the amplitude of the blade tip versus the number of cycles to evaluate the fatigue performance of the test blade.
In some embodiments, the vibration fatigue testing apparatus further includes a strain flower attached to the test blade and a strain monitoring device coupled to the strain flower, the attachment position of the strain flower is adapted to the fiber orientation of the test blade, and the strain monitoring device obtains the strain detected by the strain flower.
In some embodiments, the vibration fatigue testing apparatus further comprises a DIC device for acquiring a full field strain of the blade body of the test blade and an interlaminar strain at the tenon of the test blade, and the strain detected by the strain flowers acquired by the strain monitoring device is verified with the full field strain and the interlaminar strain acquired by the DIC device.
In some embodiments, the vibration fatigue testing apparatus further comprises a temperature monitoring device which monitors the temperature of the test blade in real time.
The invention provides a vibration fatigue test method of a composite material fan blade, which comprises the following steps:
designing a clamp according to the shape of the tenon of the test blade, arranging an upper ejector block at the bottom of a clamping cavity of the clamp, and enabling the upper ejector block to be tightly pressed with the bottom of the tenon of the test blade; and is
The fatigue performance of the test blade is evaluated through numerical simulation and mutual verification of tests.
In some embodiments, obtaining a fatigue performance curve for the test blade through numerical simulation and experimental mutual validation includes plotting the tip amplitude versus cycle number for the test blade.
In some embodiments, obtaining the fatigue performance curve of the test blade through mutual verification of numerical simulation and test comprises:
obtaining the modal vibration mode of the test blade through mutual verification of numerical simulation and test, and determining the vibration frequency of the vibration fatigue test according to the modal vibration mode;
carrying out harmonic response analysis on the test blade through numerical simulation and test mutual verification;
obtaining the vibration stress distribution of the test blade according to the modal array harmonic response analysis of the blade, and determining the sticking position of the strain rosette according to the vibration stress distribution;
and determining the load excitation level through mutual verification of numerical simulation and test, and performing formal vibration fatigue test under different load excitation levels to obtain test data under different load excitation levels.
In some embodiments, the test data includes full field strain, interlaminar strain, and tip amplitude of the blade, and the test method further includes plotting tip amplitude versus cycle number based on the tip amplitude to evaluate fatigue performance of the blade.
The vibration fatigue test device for the composite material fan blade comprises a vibration table and a clamp, wherein the vibration table is used for providing an excitation source for vibration of the test blade, the clamp is arranged on the vibration table and comprises a clamp body and an upper ejector block, the clamp body is provided with a clamping cavity used for clamping and fixing a tenon of the test blade, and the upper ejector block is arranged at the bottom of the clamping cavity and tightly presses the bottom of the tenon of the test blade so that the side surface of the clamping cavity is attached to working surfaces on two sides of the tenon of the test blade. The vibration fatigue test device provided by the invention designs the clamp according to the shape of the tenon of the test blade, and takes the structural characteristics of the fan blade made of the resin matrix composite material into consideration, so as to better simulate the centrifugal load borne by the blade in service and simultaneously avoid the excessive shear stress generated at the joint position of the tenon and the clamp.
Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the invention without limiting the invention. In the drawings:
FIG. 1 is a schematic structural diagram of a vibration fatigue testing device for a composite material fan blade according to an embodiment of the invention;
FIG. 2 is a schematic side view of the test blade and fixture of FIG. 1 in mating configuration;
FIG. 3 is a schematic structural view of a test blade according to an embodiment of the present invention;
FIG. 4 is a flow chart of a composite material fan blade vibration fatigue testing method according to an embodiment of the invention.
Detailed Description
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, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. 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 relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail, but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
Spatially relative terms, such as "above … …", "above … …", "above … …", "above", and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously positioned and the spatially relative descriptors used herein interpreted accordingly.
Before describing particular aspects of embodiments of the present invention, the following related terms are explained.
The fan blade is made of resin-based composite material (resin-matrix-composite fan blade), wherein the resin-based composite material refers to a fiber reinforced material taking an organic polymer as a matrix, commonly used fiber reinforced materials comprise glass fiber, carbon fiber, aramid fiber and the like, and the fan blade which is designed and processed and formed by adopting the resin-based composite material according to an aerodynamic blade profile is called the resin-based composite material fan blade.
Vibration fatigue test (vibration fatigue experiment) in which an alternating load is applied to a test subject by vibration excitation, the fatigue performance is examined, and the failure mode is studied.
Full field strain (whole field) strain of the entire observed surface during deformation of a test object, obtained by specific technical means, such as digital image correlation techniques.
The tip amplitude (amplitude of blade tip) refers to the absolute value of the maximum displacement of the blade tip from the equilibrium position when the blade vibrates.
The interlaminar strain (interlaminar strain) is characterized in that each layer in the laminated plate deforms differently under stress due to different elastic modulus, and the deformation of the layers is restricted and coordinated due to the mutual adhesion of the layers, so that corresponding normal stress and shear stress are generated between the layers, namely the interlaminar stress.
High-speed photography (high-speed photography) means that a moving image can be captured with an exposure of less than 1/1000 seconds or at a frame rate of more than 250 frames per second.
The fixture (fixture) is used for fixing the test object in the process of manufacturing or testing, so that the test object occupies the correct position and completes the corresponding processing work.
The following describes in detail the structure of the vibration fatigue test apparatus for a composite material fan blade according to the embodiment of the present invention and a method for performing a vibration fatigue test on a composite material fan blade by using the vibration fatigue test apparatus.
As shown in fig. 1 and 2, the vibration fatigue test apparatus for the composite material fan blade of the present embodiment includes:
the vibration table 1 is used for providing an excitation source for the vibration of the test blade 2; and
anchor clamps 3 sets up on shaking table 1 and includes anchor clamps body 31 and last kicking block 32, and anchor clamps body 31 has the centre gripping chamber that is used for the tenon of centre gripping fixed test blade, goes up kicking block 32 and sets up in the bottom in centre gripping chamber and compresses tightly the tenon bottom of test blade so that the side in centre gripping chamber and the working face laminating of the tenon both sides of test blade.
The vibration fatigue test device of this embodiment designs anchor clamps 3 according to test blade's tenon shape, consider the structural feature of resin matrix combined material fan blade, centrifugal load for bearing in the better simulation blade service, avoid tenon and 3 binding site of anchor clamps to produce too big shear stress simultaneously, anchor clamps 3 of this embodiment design is top formula structure, make the working face of anchor clamps 3 and the laminating of the tenon both sides working face of test blade 2 compress tightly, make the frequency of test blade 2 no longer change through constantly increasing the packing force, confirm the packing force of anchor clamps 3 in the experiment, thereby it is fixed with test blade 2.
Specifically, a bolt hole may be formed in the clamp body 31, a bolt may be inserted into the bolt hole, and the upper ejector pad 32 may be compressed by the bolt, so that the tightening torque of the bolt may be increased to move the upper ejector pad 32 upward, thereby increasing the pressing force. Or, a wedge-shaped block is arranged between the clamp body 31 and the upper ejection block 32, the pressing force of the upper ejection block 32 on the test blade 2 is continuously increased by continuously pressing the wedge-shaped block, and the wedge-shaped block is locked by a pin or the like after the required pressing force is reached.
The anchor clamps 3 of this embodiment are the structure of realizing experimental blade 2 and 1 stable connections of shaking table, will avoid the coupling vibration of anchor clamps 3 and shaking table 1 when designing anchor clamps 3, will be according to fibre atress characteristics to the combined material blade, the simulation blade state of being in service, the anchor clamps of this embodiment adopt the compact structure of top formula, specifically, as shown in fig. 2, the anchor clamps 3 of this embodiment include anchor clamps body 31 and last top pressing block 32, make anchor clamps body 31 and experimental blade 2 laminating through upwards compressing tightly top pressing block 32, thereby it is fixed with experimental blade 2.
The vibration table 1 of the embodiment is a power source for the vibration fatigue test of the test blade, and provides vibration energy at each order of resonance frequency to the test blade 2, so that the test blade 2 completes the fatigue test at the resonance frequency. Due to the material anisotropy of the composite material blade, the traditional stress-based evaluation method of the metal blade is not suitable for the composite material blade, the blade tip amplitude is adopted for evaluation, and the relation between the blade tip amplitude and the cycle number, namely an A-N curve, is obtained to evaluate the fatigue performance of the blade.
As shown in fig. 1, in order to monitor the tip amplitude of the test blade 2, the vibration fatigue test apparatus of the present embodiment further includes a suspension type camera 8 and a control device. The suspended shooting device 8 is arranged above the tip of the test blade 2 in a suspended mode and used for capturing the tip amplitude, and the control device is configured to receive the tip amplitude and control the vibrating table 1 to act according to the tip amplitude. Due to the material anisotropy of the composite material blade, the load level of the composite material blade needs to be controlled through the amplitude of the blade tip to realize closed-loop control on the vibration table 1. The test device of this embodiment obtains the apex amplitude through suspension type camera 8 to compound material blade to feed back to shaking table 1 as closed loop control's input, thereby make test blade 2 can vibrate under invariable amplitude.
Because the composite material fan blade is highly bent, twisted and swept, and the blade tip amplitude of the blade cannot be captured by the traditional laser displacement equipment, the suspended type shooting device 8 adopted by the embodiment is a high-speed camera to capture the blade tip amplitude. The number of frames of the high speed camera is greater than the test natural frequency of the test blade 2.
Specifically, the control device includes an amplitude processing system, and the boom camera 8 captures the blade tip amplitude and sends the blade tip amplitude to the amplitude processing system.
The control apparatus of the present embodiment is configured to plot the amplitude of the blade tip versus the number of cycles to evaluate the fatigue performance of the blade. For a composite blade, the testing device of the embodiment adopts the relation between the blade tip amplitude and the cycle number, namely an A-N curve, to evaluate the fatigue performance of the blade.
As shown in fig. 3, the vibration fatigue testing apparatus of the present embodiment further includes a strain gauge 9 attached to the test blade 2, and a strain monitoring device 5 coupled to the strain gauge 9. The sticking position of the strain rosette 9 is adapted to the fiber direction X of the test blade 2, and the strain monitoring device 5 acquires the strain detected by the strain rosette 9. The strain monitoring device acquires the strain at the patch position of the strain rosette 9, including the blade body surface strain along the fiber direction and the interlaminar strain at the tenon position.
The patch of the strain flower 9 of this embodiment is required to include at least 1.5 unit cells.
The vibration fatigue test device of the embodiment further comprises DIC equipment 7, wherein the DIC equipment is used for obtaining the full-field strain of the blade body of the test blade 2 and the interlayer strain at the tenon of the test blade 2, and the strain detected by the strain gauge 9 obtained by the strain monitoring device is verified with the full-field strain and the interlayer strain obtained by the DIC equipment.
The vibration fatigue test device of this embodiment further includes a temperature monitoring device 6, and the temperature monitoring device 6 monitors the temperature of the test blade 2 in real time. In this embodiment, the temperature monitoring device 6 is disposed on the vibration table 1 and is a non-contact thermal infrared imager. The non-contact infrared thermal imager can be used for monitoring the temperature of the test blade 2 in real time, and the problem that the fatigue performance of the blade is influenced due to temperature rise of the blade caused by long-time vibration fatigue test is avoided.
In order to realize real-time constant temperature control of the temperature in the test room and avoid the change of the fatigue mechanical property of the composite material blade caused by the temperature change, the vibration fatigue test device of the embodiment further comprises a constant temperature control device 4. The thermostat control device 4 is placed on one side of the vibration table 4. The thermostatic control device 4 is a thermostatic air conditioning unit.
The vibration fatigue test method of the composite material fan blade comprises the following steps:
designing a clamp 3 according to the shape of the tenon of the test blade 2, arranging an upper ejector block 32 at the bottom of a clamping cavity of the clamp 3, and enabling the upper ejector block 32 to be tightly pressed with the bottom of the tenon of the test blade 2; and is
The fatigue performance of the test blade 2 was evaluated by mutual verification of numerical simulation and test.
Specifically, the method for testing the vibration fatigue according to the embodiment obtains the fatigue performance curve of the test blade 2 through the mutual verification of the numerical simulation and the test, and includes the step of drawing the curve of the blade tip amplitude and the cycle number of the test blade 2. Due to the material anisotropy of the composite material blade, the traditional stress-based evaluation method of the metal blade is not suitable for the composite material blade, the blade tip amplitude is adopted for evaluation, and the relation between the blade tip amplitude and the cycle number, namely an A-N curve, is obtained to evaluate the fatigue performance of the blade.
The obtaining of the fatigue performance curve of the test blade through the mutual verification of the numerical simulation and the test of the embodiment includes:
obtaining the modal vibration mode of the test blade 2 through numerical simulation and test mutual verification, and determining the vibration frequency of the vibration fatigue test according to the modal vibration mode;
carrying out harmonic response analysis on the test blade through numerical simulation and test mutual verification;
obtaining the vibration stress distribution of the test blade according to the modal array harmonic response analysis of the blade, and determining the sticking position of the strain rosette according to the vibration stress distribution;
and determining the load excitation level through mutual verification of numerical simulation and test, and performing formal vibration fatigue test under different load excitation levels to obtain test data under different load excitation levels.
The flow of the composite material fan blade vibration fatigue test method of the embodiment of the invention is shown in FIG. 4.
Firstly, in step 101, the design of the fixture 3 is completed according to the tenon shape of the test blade 2, and in consideration of the structural characteristics of the resin-based composite material fan blade, in order to better simulate the centrifugal load borne by the blade in service and simultaneously avoid the excessive shear stress generated at the joint position of the tenon and the fixture 3, the fixture 3 is designed to be of an upper-jacking type structure, so that the working surface of the fixture 3 is attached and compressed with the working surfaces at two sides of the tenon of the test blade 2, the frequency of the blade is not changed any more by continuously increasing the pressing force, and the pressing force of the fixture in the test is determined so as to fix the test blade 2.
In step 102, the test blade 2 is in transfer connection with the fixture 3, modal simulation of the test blade 2 in a working state is completed under a simulation condition, coupling of the fixture 3 and a modal vibration mode of the blade is avoided, meanwhile, a natural mode of the blade is obtained through frequency sweeping of the vibration table 1 under the test condition, simulation and test results are verified mutually, and finally vibration frequency of a vibration fatigue test is determined.
In step 103, harmonic response analysis under the working state of the blade is completed under the simulation condition, meanwhile, the response of the blade under small excitation is obtained through the test of the vibration table 1 under the test condition, the test and the simulation result are compared, and the test is consistent with the simulation result through adjusting the settings of the simulation damping condition and the like.
In step 104, under the simulation condition, according to the composite material blade material-level fatigue failure data, the maximum excitation which can be borne by the blade is estimated, different load excitation levels are divided according to the fatigue test requirements, and the load excitation levels are used as the estimated values of the formal fatigue test. Meanwhile, the vibration stress distribution of the blade is obtained by combining harmonic response analysis and modal characteristic test of a test, and the position of the strain rosette is determined.
In step 105, according to the characteristics of the resin-based composite material blade, a monitoring method different from the traditional metal blade needs to be adopted, specifically comprising the steps of adopting a suspension type high-speed camera to capture the amplitude of the blade tip, obtaining the amplitude value of the blade tip through software processing, using the amplitude value as a control signal, and carrying out closed-loop control on a vibration table to realize the constant amplitude in a fatigue test; and in consideration of anisotropy of the composite material blade, acquiring the full-field strain of the blade body through joint monitoring of the blade body strain rosette and DIC equipment, and acquiring the interlayer strain of the blade tenon position through the strain rosette stuck at the tenon end part according to the fiber walking direction. The resin-based composite material is sensitive to temperature, and in order to avoid the influence of temperature change in a fatigue test on the performance of the blade, a non-contact infrared thermal imager is adopted to monitor the temperature of the blade in real time and realize the constant temperature of the ambient temperature through a constant temperature air conditioning unit.
In step 106, joint debugging is performed on each device through pre-test, and the load excitation level division in step 104 is verified.
In step 107, a formal fatigue test is started, and test data such as full-field strain, interlaminar strain, blade tip amplitude and the like of the blade at different load levels are acquired.
In step 108, the test data is analyzed, and due to the material anisotropy of the composite material blade, the traditional stress-based evaluation method for the metal blade is not suitable for the composite material blade, and the blade tip amplitude is adopted for evaluation to obtain an A-N curve of the fatigue performance of the blade.
To sum up, the embodiment of the invention provides a vibration fatigue test device and a test method for a composite material fan blade, wherein an excitation level is determined through mutual verification of numerical simulation and test, effective connection between the blade and a vibration table is realized through a specially designed clamp, the blade tip amplitude of the blade is monitored through a high-speed camera to realize control of the excitation level of the blade, vibration stress monitoring of the anisotropic composite material fan blade is realized through a strain gauge and a strain rosette in combination with DIC full-field strain monitoring, the blade temperature is monitored in real time through a non-contact infrared thermal imager, constant temperature control of the environment temperature is realized through a constant temperature air conditioning unit, and the fatigue performance of the blade is evaluated through drawing a relation between the blade tip amplitude and the cycle number, namely an A-N curve.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention and not to limit it; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications of the embodiments of the invention or equivalent substitutions for parts of the technical features are possible; without departing from the spirit of the invention, it is intended to cover all modifications within the scope of the invention as claimed.
Claims (10)
1. A vibration fatigue test device of a composite material fan blade is characterized by comprising:
the vibration table (1) is used for providing an excitation source for the vibration of the test blade (2); and
anchor clamps (3), set up in just including anchor clamps body (31) and last top pressing block (32) on shaking table (1), anchor clamps body (31) have and are used for the centre gripping to fix the centre gripping chamber of the tenon of test blade (2), go up top pressing block (32) set up in the bottom in centre gripping chamber and compress tightly the tenon bottom of test blade (2) is so that the side in centre gripping chamber with the working face laminating of the tenon both sides of test blade (2).
2. The vibration fatigue test device for a composite fan blade according to claim 1, further comprising a hanging camera (8) and a control device, wherein the hanging camera (8) is hung above the blade tip of the test blade (2) for capturing the amplitude of the blade tip, and the control device is configured to receive the amplitude and control the vibration table (1) to act according to the amplitude.
3. The device for testing the vibratory fatigue of a composite fan blade as claimed in claim 2, characterized in that said control device is configured to plot the amplitude of the blade tip versus the number of cycles in order to evaluate the fatigue performance of a test blade (1).
4. The vibration fatigue test device for the composite fan blade is characterized by further comprising a strain flower (9) attached to the test blade (1) and a strain monitoring device (5) coupled with the strain flower, wherein the attachment position of the strain flower (9) is adaptive to the fiber trend of the test blade (2), and the strain monitoring device (5) acquires the strain detected by the strain flower (9).
5. The vibration fatigue test device for the composite fan blade according to claim 4, further comprising DIC equipment (7), wherein the DIC equipment (7) is used for acquiring the full field strain of the blade body of the test blade (2) and the interlaminar strain at the tenon of the test blade (2), and the strain detected by the strain rosette (9) acquired by the strain monitoring device (5) is verified with the full field strain and the interlaminar strain acquired by the DIC equipment (7).
6. The vibration fatigue test device of the composite material fan blade of claim 1, further comprising a temperature monitoring device (6), wherein the temperature monitoring device (6) monitors the temperature of the test blade (2) in real time.
7. A vibration fatigue test method for a composite material fan blade is characterized by comprising the following steps:
designing a clamp (3) according to the shape of the tenon of the test blade (2), arranging an upper ejector block (32) at the bottom of a clamping cavity of the clamp (3) and enabling the upper ejector block (32) to be tightly pressed with the bottom of the tenon of the test blade (2); and is
The fatigue performance of the test blade (2) is evaluated by mutual verification of numerical simulation and test.
8. The method for testing the vibratory fatigue of a composite fan blade as set forth in claim 7, wherein obtaining a fatigue performance curve of a test blade (2) by mutual verification of numerical simulation and testing comprises plotting the tip amplitude versus cycle number of the test blade (2).
9. The method for testing the vibration fatigue of the composite material fan blade according to claim 7, wherein the step of obtaining the fatigue performance curve of the test blade (2) through the mutual verification of numerical simulation and test comprises the following steps:
obtaining the modal vibration mode of the test blade (2) through numerical simulation and test mutual verification, and determining the vibration frequency of the vibration fatigue test according to the modal vibration mode;
carrying out harmonic response analysis on the test blade (2) through numerical simulation and test mutual verification;
analyzing and acquiring the vibration stress distribution of the test blade (2) according to the modal array of the blade and the harmonic response, and determining the sticking position of the strain rosette according to the vibration stress distribution;
and determining the load excitation level through mutual verification of numerical simulation and test, and performing formal vibration fatigue test under different load excitation levels to obtain test data under different load excitation levels.
10. The method of claim 9 wherein the test data includes full field strain, interlaminar strain, and tip amplitude of the blade, and wherein the method further comprises plotting tip amplitude versus cycle number based on the tip amplitude to assess fatigue performance of the blade.
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