CN114441122B - Vibration fatigue test device and test method for composite material fan blade - Google Patents
Vibration fatigue test device and test method for composite material fan blade Download PDFInfo
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- 238000003825 pressing Methods 0.000 claims abstract description 25
- 230000005284 excitation Effects 0.000 claims abstract description 23
- 238000004088 simulation Methods 0.000 claims description 27
- 238000012795 verification Methods 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 18
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- 229920005989 resin Polymers 0.000 description 2
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- 229920000049 Carbon (fiber) Polymers 0.000 description 1
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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
- 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
- G01—MEASURING; TESTING
- 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
- G01M7/025—Measuring arrangements
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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 of 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 pressing jacking block, the clamp body is provided with a clamping cavity for clamping and fixing a tenon of the test blade, and the upper pressing jacking block is arranged at the bottom of the clamping cavity and is used for pressing the tenon bottom of the test blade so that the side face of the clamping cavity is attached to working faces on two sides of the tenon of the test blade. According to the vibration fatigue test device, the clamp is designed according to the tenon shape of the test blade, the clamp is designed to be of an upper-top structure, so that the working face of the clamp is attached to and tightly pressed against the working faces 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, low noise and low maintenance cost are the continuous pursuit targets of commercial large-scale aircrafts, and reducing the weight of large-bypass-ratio turbofan engines of large-scale aircraft core components and improving the bypass ratio are one of the main ways of achieving the targets. The fan blade is a core part of the turbofan engine with a large bypass ratio, and the weight of the fan blade can be reduced, so that the iteration reduction of the weight of engine structures such as a fan casing, a transmission system and the like and aircraft structures such as aircraft wings and aircraft bodies can be realized; 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 use of larger and lighter fan blades has become a trend for large bypass ratio turbofan engines, while composite fan blades with low density, high specific strength, high specific stiffness, good anti-flutter performance, and strong damage tolerance have become an effective approach.
The problem of vibration of the blades is one of the problems puzzling the development and service of an aeroengine, and the composite material fan blades are no exception, and accidents of casualties caused by engine explosion due to fatigue fracture of the fan blades already exist in the civil aviation development history, so that a series of vibration fatigue tests, crosswind tests and the like are required to be carried out in order to effectively evaluate and improve the vibration resistance of the composite material fan blades and prolong the service time of the composite material fan blades. The vibration fatigue test is an effective means of verifying the vibration capability of the blade at the component level. The traditional vibration fatigue test method and system are mainly developed for isotropic metal blades, the traditional patch mode is difficult to obtain the complete strain of the blades due to the anisotropy of materials, and due to the sensitivity of the composite materials to temperature, the temperature needs to be monitored in real time and constant temperature measures are adopted in the test, the traditional excitation control method for the anisotropy of the high bending and sweeping shape and the strain of the blades cannot control the load level applied to the blades, the general vibration fatigue test clamp is inapplicable due to the structural characteristics of the composite materials blades, the accurate fatigue performance cannot be obtained due to the traditional S-N (stress-cycle) curve of the anisotropy of the composite materials blades, and in combination, the traditional vibration fatigue test device and method cannot be effectively applied to the vibration fatigue test of the composite materials of the fan blades, and new fatigue test methods and systems are required to be designed according to the characteristics of the composite materials of the fan blades.
Disclosure of Invention
The invention aims to provide a vibration fatigue test device and a test method for a composite material fan blade, which are suitable for the vibration fatigue test of the composite material fan blade.
The first aspect of the present invention provides a vibration fatigue test apparatus for a composite material fan blade, comprising:
the vibration table is used for providing an excitation source for vibration of the test blade; and
the fixture is arranged on the vibrating table and comprises a fixture body and an upper pressing jacking block, the fixture body is provided with a clamping cavity for clamping and fixing tenons of the test blades, and the upper pressing jacking block is arranged at the bottom of the clamping cavity and presses the bottoms of tenons of the test blades so that the side surfaces of the clamping cavity are attached to working surfaces on two sides of the tenons of the test blades.
In some embodiments, the vibration fatigue testing device further comprises a suspension camera suspended above the tip of the test blade for capturing the amplitude of the tip, and a control device configured to receive the amplitude and control the vibration table action in accordance with 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 test device further comprises a strain gauge attached to the test blade and a strain monitoring device coupled with the strain gauge, wherein the attaching position of the strain gauge is adapted to the fiber trend of the test blade, and the strain monitoring device acquires the strain detected by the strain gauge.
In some embodiments, the vibration fatigue test apparatus further comprises a DIC device for acquiring full-field strain of the blade body of the test blade and interlayer strain at the dovetail of the test blade, the strain detected by the strain gauge acquired by the strain monitoring device being verified with the full-field strain and interlayer strain acquired by the DIC device.
In some embodiments, the vibration fatigue test apparatus further comprises a temperature monitoring device that monitors the temperature of the test blade in real time.
The second aspect of the invention provides a vibration fatigue test method for a composite fan blade, comprising the following steps:
designing a clamp according to the tenon shape of the test blade, arranging an upper pressing block at the bottom of a clamping cavity of the clamp, and pressing the upper pressing block with the tenon bottom of the test blade; and is also provided with
The fatigue performance of the test blade is evaluated by numerical simulation and mutual verification of the test.
In some embodiments, obtaining a fatigue performance curve for the test blade through numerical simulation and mutual verification of the test includes plotting tip amplitude versus cycle number for the test blade.
In some embodiments, obtaining the fatigue performance curve of the test blade through numerical simulation and mutual verification of the test includes:
acquiring the mode shape of the test blade through numerical simulation and mutual verification of the test, and determining the vibration frequency of a vibration fatigue test according to the mode shape;
carrying out harmonic response analysis on the test blade through numerical simulation and mutual verification of the test;
obtaining vibration stress distribution of the test blade according to the modal matrix harmonic response analysis of the blade, and determining the sticking position of the strain flower according to the vibration stress distribution;
and determining the load excitation level through numerical simulation and mutual verification of experiments, and performing formal vibration fatigue tests 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.
Based on the vibration fatigue test device and the test method of the composite material fan blade, the vibration fatigue test device of 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 pressing jacking block, the clamp body is provided with a clamping cavity for clamping and fixing a tenon of the test blade, and the upper pressing jacking block is arranged at the bottom of the clamping cavity and presses the bottom of the tenon of the test blade so that the side surfaces of the clamping cavity are attached to working surfaces on two sides of the tenon of the test blade. According to the vibration fatigue test device, the clamp is designed according to the tenon shape of the test blade, the structural characteristics of the resin-based composite material fan blade are considered, centrifugal load born by the blade in service is better simulated, and meanwhile, excessive shearing stress generated at the joint position of the tenon and the clamp is avoided.
Other features of the present invention and its advantages will become apparent from the following detailed description of exemplary embodiments of the invention, 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 embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:
FIG. 1 is a schematic diagram of a vibration fatigue test apparatus for a composite fan blade according to an embodiment of the present invention;
FIG. 2 is a schematic side elevational view of the mating of the test blade and clamp of FIG. 1;
FIG. 3 is a schematic view of a test blade according to an embodiment of the present invention;
FIG. 4 is a flow chart of a method of vibration fatigue testing of a composite fan blade according to an embodiment of the present invention.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the invention, its application, or uses. 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 relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the authorization specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative 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 in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways and the spatially relative descriptions used herein are construed accordingly.
Before describing embodiments of the present invention, the following related terms will be explained.
Resin-matrix fan blades (resin-matrix-composite based fan blade) resin-matrix composite refers to fiber reinforced materials with organic polymers as matrixes, glass fibers, carbon fibers, aramid fibers and the like are commonly used fiber reinforced materials, and fan blades which are designed and processed by adopting the resin-matrix composite according to a pneumatic blade profile are called resin-matrix composite fan blades.
Vibration fatigue test (vibration fatigue experiment) in which an alternating load is applied to a test subject by vibration excitation, and the fatigue performance is examined and the failure mode is studied.
Full field strain (whole strain field) is the strain of the entire observation surface during deformation of a test object obtained by specific technical means such as digital image correlation techniques.
Blade tip amplitude (amplitude of blade tip) is the absolute value of the maximum displacement of the blade tip from the equilibrium position as the blade vibrates.
The interlayer strain (interlaminar strain) is that the layers in the laminated plate deform differently when the layers are stressed due to different elastic moduli, and the layers are mutually bonded, so that the deformation between the layers is mutually restricted and coordinated, and corresponding normal stress and shear stress are generated between the layers, namely interlayer stress.
High-speed imaging (high-speed photography) means that a moving image can be captured at an exposure of less than 1/1000 second or a frame rate exceeding 250 frames per second.
The fixture (fixture) is a device for fixing the test object in the process of manufacturing or testing, so as to occupy the correct position and complete the corresponding processing work.
The structure of the vibration fatigue test device for the composite material fan blade according to the embodiment of the invention and the method for performing the vibration fatigue test on the composite material fan blade by using the vibration fatigue test device are described in detail below.
As shown in fig. 1 and 2, the vibration fatigue test apparatus for a composite material fan blade of the present embodiment includes:
a vibration table 1 for providing an excitation source for vibration of the test blade 2; and
the fixture 3 is arranged on the vibrating table 1 and comprises a fixture body 31 and an upper pressing jacking block 32, wherein the fixture body 31 is provided with a clamping cavity for clamping and fixing tenons of the test blades, and the upper pressing jacking block 32 is arranged at the bottom of the clamping cavity and presses the bottoms of tenons of the test blades so that the side surfaces of the clamping cavity are attached to working surfaces on two sides of the tenons of the test blades.
According to the vibration fatigue test device, the clamp 3 is designed according to the tenon shape of the test blade, the structural characteristics of the resin matrix composite fan blade are considered, centrifugal load born by the blade in service is simulated better, meanwhile, excessive shearing stress generated at the joint position of the tenon and the clamp 3 is avoided, the clamp 3 of the embodiment is designed to be of an upper-top structure, the working face of the clamp 3 is tightly attached to the working faces on two sides of the tenon of the test blade 2, the frequency of the test blade 2 is not changed by increasing the pressing force continuously, and the pressing force of the clamp 3 in the test is determined, so that the test blade 2 is fixed.
Specifically, a bolt hole can be formed in the clamp body 31, a bolt is inserted into the bolt hole and is used for compressing the upper pressing block 32, and the tightening torque of the bolt is increased continuously to enable the upper pressing block 32 to move upwards, so that the compressing force is increased continuously. Or, a wedge block is arranged between the clamp body 31 and the upper pressing block 32, the pressing force of the upper pressing block 32 to the test blade 2 is continuously increased by continuously pressing the wedge block, and after the required pressing force is reached, the wedge block is locked by a pin and the like.
The fixture 3 of this embodiment is a structure for realizing stable connection between the test blade 2 and the vibration table 1, and when the fixture 3 is designed, the coupling vibration between the fixture 3 and the vibration table 1 is avoided, and the service state of the blade is simulated according to the fiber stress characteristics for the composite blade, and the fixture of this embodiment adopts an upper jacking type compacting structure, specifically, as shown in fig. 2, the fixture 3 of this embodiment includes a fixture body 31 and an upper jacking block 32, and the fixture body 31 is attached to the test blade 2 by compacting the upper jacking block 32 upwards, so that the test blade 2 is fixed.
The vibration table 1 of the present embodiment is a power source for the vibration fatigue test of the test blade, and supplies vibration energy at resonance frequencies of respective orders to the test blade 2, so that the test blade 2 completes the fatigue test at the resonance frequency. Because of 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, and the blade tip amplitude is adopted for evaluation, and the relationship between the blade tip amplitude and the cycle number, namely the A-N curve, is obtained for evaluating 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 photographing device 8 and a control device. The suspension type shooting device 8 is suspended above the tip of the test blade 2 and used for capturing the tip amplitude, and the control device is configured to receive the tip amplitude and control the action of the vibration table 1 according to the tip amplitude. Due to the material anisotropy of the composite blade, closed loop control of the vibration table 1 is required by controlling its load level through the tip amplitude. The test device of the embodiment obtains the blade tip amplitude of the composite blade through the suspension type shooting device 8 and feeds the blade tip amplitude back to the vibration table 1 as the input of closed-loop control, so that the test blade 2 can vibrate under constant amplitude.
Because the composite fan blade is highly curved and sweeped, the traditional laser displacement equipment cannot capture the blade tip amplitude of the blade, and therefore the suspension type shooting device 8 adopted in the embodiment is a high-speed camera, so as 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 suspension imaging device 8 captures the tip amplitude and transmits the tip amplitude to the amplitude processing system.
The control device of the present embodiment is configured to draw a curve of the amplitude of the blade tip versus the number of cycles to evaluate the fatigue performance of the blade. For composite blades, the test apparatus of this embodiment evaluates the fatigue performance of the blade using the relationship between the tip amplitude and the number of cycles, i.e., the a-N curve.
As shown in fig. 3, the vibration fatigue test 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 adhesion position of the strain gauge 9 is adapted to the fiber trend X of the test blade 2, and the strain monitoring device 5 acquires the strain detected by the strain gauge 9. The strain monitoring device acquires the strain at the patch location of the strain gage 9, including the blade surface strain along the fiber direction and the interlaminar strain at the dovetail location.
The patch of the strain gage 9 of this embodiment is required to include at least 1.5 unit cells.
The vibration fatigue test device of the embodiment further comprises a DIC device 7, wherein the DIC device 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 device.
The vibration fatigue test device of the embodiment further comprises a temperature monitoring device 6, and the temperature monitoring device 6 monitors the temperature of the test blade 2 in real time. In particular, in the present embodiment, the temperature monitoring device 6 is disposed on the vibration table 1 and is a non-contact infrared thermal imager. The non-contact infrared thermal imager is used for realizing real-time monitoring of the temperature of the test blade 2, and avoiding the temperature rise of the blade caused by long-time vibration fatigue test and affecting the fatigue performance of the blade.
In order to realize real-time constant temperature control of the temperature between tests 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 thermostatic control device 4 is placed on one side of the vibrating table 4. The constant temperature control device 4 is a constant temperature air conditioning unit.
The vibration fatigue test method of the composite material fan blade of the embodiment comprises the following steps:
designing a clamp 3 according to the tenon shape of the test blade 2, arranging an upper jacking block 32 at the bottom of a clamping cavity of the clamp 3, and enabling the upper jacking block 32 to be tightly pressed with the tenon bottom of the test blade 2; and is also provided with
The fatigue performance of the test blade 2 was evaluated by numerical simulation and mutual verification of the test.
Specifically, the vibration fatigue test method of the present embodiment obtains the fatigue performance curve of the test blade 2 by numerical simulation and mutual verification of the test, including drawing the curve of the tip amplitude of the test blade 2 with the number of cycles. Because of 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, and the blade tip amplitude is adopted for evaluation, and the relationship between the blade tip amplitude and the cycle number, namely the A-N curve, is obtained for evaluating the fatigue performance of the blade.
The obtaining the fatigue performance curve of the test blade through numerical simulation and mutual verification of the test in the embodiment comprises the following steps:
the mode shape of the test blade 2 is obtained through numerical simulation and mutual verification of the test, and the vibration frequency of the vibration fatigue test is determined according to the mode shape;
carrying out harmonic response analysis on the test blade through numerical simulation and mutual verification of the test;
obtaining vibration stress distribution of the test blade according to the modal matrix harmonic response analysis of the blade, and determining the sticking position of the strain flower according to the vibration stress distribution;
and determining the load excitation level through numerical simulation and mutual verification of experiments, and performing formal vibration fatigue tests under different load excitation levels to obtain test data under different load excitation levels.
The flow of the vibration fatigue test method of the composite fan blade is shown in fig. 4.
Firstly, in step 101, the design of the clamp 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 fan blade, centrifugal load born by the blade in service is better simulated, meanwhile, excessive shear stress generated at the joint position of the tenon and the clamp 3 is avoided, the clamp 3 is designed to be of an upper-top structure, the working face of the clamp 3 is tightly attached to the working faces on two sides of the tenon of the test blade 2, the frequency of the blade is not changed by continuously increasing the compression force, and the compression force of the clamp in the test is determined to fix the test blade 2.
In step 102, the test blade 2 is connected with the clamp 3 in a matching way, the mode simulation of the test blade 2 in the working state is completed under the simulation condition, the coupling of the clamp 3 and the blade mode shape is avoided, meanwhile, the natural mode of the blade is obtained through the frequency sweep of the vibration table 1 under the test condition, the simulation and the test result are verified mutually, and finally the vibration frequency of the vibration fatigue test is determined.
In step 103, the harmonic response analysis of the blade in the working state is completed under the simulation condition, meanwhile, the response of the blade under smaller 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 and the simulation result are consistent through adjusting the setting of the simulation damping condition and the like.
In step 104, under the simulation condition, according to the material-level fatigue failure data of the composite blade, the maximum excitation which can be born 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 predicted value of the formal fatigue test. Meanwhile, vibration stress distribution of the blade is obtained through a mode characteristic test of a harmonic response analysis combined test, and the determination of the position of the strain flower is completed.
In step 105, according to the characteristics of the resin-based composite material blade, a monitoring method different from the traditional metal blade is needed, specifically, a suspension type high-speed camera is adopted to capture the blade tip amplitude, the blade tip amplitude value is obtained through software processing and is used as a control signal, the vibration table is subjected to closed-loop control, and the amplitude in the fatigue test is unchanged; taking the anisotropism of the composite blade into consideration, acquiring the full-field strain of the blade body through the joint monitoring of the strain relief of the blade body and DIC equipment, and simultaneously acquiring the interlayer strain of the blade tenon position through the strain relief of the tenon end part stuck according to the fiber running direction. The resin matrix composite is sensitive to temperature, and in order to avoid the influence of temperature change on blade performance in fatigue test, a non-contact infrared thermal imager is adopted to monitor the blade temperature in real time and realize the constant temperature of the environmental temperature through a constant temperature air conditioning unit.
In step 106, the devices are jointly debugged 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, interlayer strain, tip amplitude and the like of the blade under different load levels are obtained.
In step 108, the test data is analyzed, and the conventional stress-based evaluation method for the metal blade is not suitable for the composite blade due to the material anisotropy of the composite blade, but the blade tip amplitude is adopted for evaluation, so that an A-N curve of the fatigue performance of the blade is obtained.
In summary, the embodiment of the invention provides a vibration fatigue test device and a test method for a composite material fan blade, which are characterized in that the excitation level is determined through numerical simulation and mutual verification of tests, the effective connection of the blade and a vibration table is realized through a fixture with special design, the vibration amplitude of the blade tip is monitored through a high-speed camera to realize the control of the excitation level of the blade, the vibration stress monitoring of the anisotropic composite material fan blade is realized through the combination of a strain gauge and a strain pattern and DIC full-field strain monitoring, the real-time monitoring of the temperature of the blade is realized through a non-contact infrared thermal imager, the constant-temperature control of the ambient temperature is realized through a constant-temperature air conditioning unit, and the evaluation of the fatigue performance of the blade is realized through drawing the relation between the vibration amplitude and the circulation number of the blade, namely an A-N curve.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same; while the invention has been described in detail with reference to the preferred embodiments, those skilled in the art will appreciate that: modifications may be made to the specific embodiments of the present invention or equivalents may be substituted for part of the technical features thereof; without departing from the spirit of the invention, it is intended to cover the scope of the invention as claimed.
Claims (6)
1. A vibration fatigue test device for a composite fan blade, comprising:
a vibration table (1) for providing an excitation source for the vibration of the test blade (2); and
the fixture (3) is arranged on the vibrating table (1) and comprises a fixture body (31) and an upper pressing top block (32), the fixture body (31) is provided with a clamping cavity for clamping and fixing the tenons of the test blades (2), and the upper pressing top block (32) is arranged at the bottom of the clamping cavity and presses the bottoms of the tenons of the test blades (2) so that the side surfaces of the clamping cavity are attached to working surfaces on two sides of the tenons of the test blades (2);
the vibration fatigue test device further comprises a strain flower (9) attached to the test blade (1) and a strain monitoring device (5) coupled with the strain flower, wherein the attaching position of the strain flower (9) is matched with the trend of the fiber of the test blade (2), and the strain monitoring device (5) acquires the strain detected by the strain flower (9);
the vibration fatigue test device further comprises a suspension type shooting device (8) and a control device, wherein the suspension type shooting device (8) is suspended above the blade tip of the test blade (2) and used for capturing the vibration amplitude of the blade tip, the control device is configured to receive the vibration amplitude and feed the vibration amplitude back to the vibration table (1) as input of closed-loop control so as to control the vibration table (1) to act according to the vibration amplitude, and the control device is configured to draw a relation curve of the vibration amplitude of the blade tip and the number of cycles so as to evaluate the fatigue performance of the test blade (1).
2. The vibration fatigue test device of a composite material fan blade according to claim 1, further comprising a DIC device (7), the DIC device (7) being adapted to obtain a full-field strain of the blade body of the test blade (2) and an interlayer strain at the tenon of the test blade (2), the strain detected by the strain-gauge (9) obtained by the strain-monitoring device (5) being verified with the full-field strain and the interlayer strain obtained by the DIC device (7).
3. The vibration fatigue test device of a composite material fan blade according to claim 1, further comprising a temperature monitoring device (6), the temperature monitoring device (6) monitoring the temperature of the test blade (2) in real time.
4. A method of vibration fatigue testing a composite material fan blade based on the vibration fatigue testing apparatus of claim 1, comprising the steps of:
designing a clamp (3) according to the tenon shape of the test blade (2), arranging an upper jacking block (32) at the bottom of a clamping cavity of the clamp (3) and enabling the upper jacking block (32) to be tightly pressed with the tenon bottom of the test blade (2); and is also provided with
The fatigue performance of the test blade (2) is evaluated through numerical simulation and mutual verification of the test, and the fatigue performance curve of the test blade (2) is obtained through the numerical simulation and the mutual verification of the test, which comprises the step of drawing the curve of the blade tip amplitude and the cycle number of the test blade (2).
5. The method of vibration fatigue testing a composite material fan blade according to claim 4, wherein obtaining the fatigue performance curve of the test blade (2) by numerical simulation and mutual verification of the test comprises:
acquiring the mode shape of the test blade (2) through numerical simulation and mutual verification of the test, and determining the vibration frequency of a vibration fatigue test according to the mode shape;
carrying out harmonic response analysis on the test blade (2) through numerical simulation and mutual verification of tests;
according to the modal array shape of the blade and the harmonic response analysis, vibration stress distribution of the test blade (2) is obtained, and the sticking position of the strain flower is determined according to the vibration stress distribution;
and determining the load excitation level through numerical simulation and mutual verification of experiments, and performing formal vibration fatigue tests under different load excitation levels to obtain test data under different load excitation levels.
6. The method of claim 5, wherein the test data includes full field strain, interlaminar strain and tip amplitude of the blade, and wherein the test method further comprises plotting tip amplitude versus cycle number based on the tip amplitude to evaluate fatigue performance of the blade.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101688824A (en) * | 2007-05-30 | 2010-03-31 | 维斯塔斯风力系统集团公司 | A fatigue testing device for wind turbine blade testing, a method of testing wind turbine blades and a control system for a blade testing actuator |
| JP2013140185A (en) * | 2013-04-19 | 2013-07-18 | National Institute For Materials Science | Cryogenic temperature ultrasonic fatigue nondestructive test evaluation apparatus |
| WO2015140945A1 (en) * | 2014-03-19 | 2015-09-24 | 株式会社日立製作所 | Fatigue tester |
| CN105319039A (en) * | 2014-07-02 | 2016-02-10 | 西安航空动力股份有限公司 | Vibration fatigue testing method for large-bypass-ratio engine fan blade with shoulder |
| CN106226015A (en) * | 2016-07-01 | 2016-12-14 | 西北工业大学 | A kind of assay device of turbine disk coupled vibrations |
| CN108195537A (en) * | 2018-02-06 | 2018-06-22 | 东南大学 | A kind of blade of aviation engine vibration fatigue test method based on amplitude controlling |
| CN108519225A (en) * | 2018-03-19 | 2018-09-11 | 江苏大学 | A kind of detection device and method of blade of aviation engine high-temperature vibrating fatigue properties |
| CN109238718A (en) * | 2017-08-31 | 2019-01-18 | 中国航空制造技术研究院 | A kind of engine blower blade high cycle fatigue performance test methods |
| CN110595709A (en) * | 2019-08-14 | 2019-12-20 | 南京航空航天大学 | Method for determining allowable amplitude of turbine engine blade |
| CN110631789A (en) * | 2018-06-21 | 2019-12-31 | 中国航发商用航空发动机有限责任公司 | Jig, test device, and test method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2993359B1 (en) * | 2012-07-16 | 2014-08-29 | Snecma | METHOD FOR PERFORMING A VIBRATORY FATIGUE TEST OF A MECHANICAL PART |
| ES2717122T3 (en) * | 2014-12-23 | 2019-06-19 | Ore Catapult Development Services Ltd | Fatigue tests |
| GB201510408D0 (en) * | 2015-06-15 | 2015-07-29 | Rolls Royce Plc | Vibration fatigue testing |
-
2020
- 2020-11-06 CN CN202011231488.0A patent/CN114441122B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101688824A (en) * | 2007-05-30 | 2010-03-31 | 维斯塔斯风力系统集团公司 | A fatigue testing device for wind turbine blade testing, a method of testing wind turbine blades and a control system for a blade testing actuator |
| JP2013140185A (en) * | 2013-04-19 | 2013-07-18 | National Institute For Materials Science | Cryogenic temperature ultrasonic fatigue nondestructive test evaluation apparatus |
| WO2015140945A1 (en) * | 2014-03-19 | 2015-09-24 | 株式会社日立製作所 | Fatigue tester |
| CN105319039A (en) * | 2014-07-02 | 2016-02-10 | 西安航空动力股份有限公司 | Vibration fatigue testing method for large-bypass-ratio engine fan blade with shoulder |
| CN106226015A (en) * | 2016-07-01 | 2016-12-14 | 西北工业大学 | A kind of assay device of turbine disk coupled vibrations |
| CN109238718A (en) * | 2017-08-31 | 2019-01-18 | 中国航空制造技术研究院 | A kind of engine blower blade high cycle fatigue performance test methods |
| CN108195537A (en) * | 2018-02-06 | 2018-06-22 | 东南大学 | A kind of blade of aviation engine vibration fatigue test method based on amplitude controlling |
| CN108519225A (en) * | 2018-03-19 | 2018-09-11 | 江苏大学 | A kind of detection device and method of blade of aviation engine high-temperature vibrating fatigue properties |
| CN110631789A (en) * | 2018-06-21 | 2019-12-31 | 中国航发商用航空发动机有限责任公司 | Jig, test device, and test method |
| CN110595709A (en) * | 2019-08-14 | 2019-12-20 | 南京航空航天大学 | Method for determining allowable amplitude of turbine engine blade |
Non-Patent Citations (4)
| Title |
|---|
| Research on Design and Simulation of Biaxial Tensile-Bending Complex Mechanical Performance Test Apparatus;Hailian Li et al;Micromachines (Basel);20171012;1-3 * |
| 放大工装在整体叶轮叶片振动疲劳试验中的应用;姚春斌等;环境试验;第11-16页 * |
| 王家广等.空心风扇叶片高循环疲劳异常失效分析.航空制造技术.2017,(第12期),第84-93页. * |
| 空心风扇叶片高循环疲劳异常失效分析;王家广等;航空制造技术(第12期);第84-93页 * |
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