CN115493822A - Engine blade simulated load fatigue test device and method - Google Patents
Engine blade simulated load fatigue test device and method Download PDFInfo
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- CN115493822A CN115493822A CN202211042596.2A CN202211042596A CN115493822A CN 115493822 A CN115493822 A CN 115493822A CN 202211042596 A CN202211042596 A CN 202211042596A CN 115493822 A CN115493822 A CN 115493822A
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 42
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- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
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Abstract
The device comprises a horizontally arranged installation reference, wherein a movably adjustable blade support is arranged in the middle area of the installation reference, and a blade is arranged on the upper side of the blade support; the mounting standard is also provided with a movable supporting frame, the supporting frame is positioned on two sides of the blade support, a multipoint mechanical measurement component is arranged in the supporting frame, one end, close to the blade support, of the multipoint mechanical measurement component is in contact with the surface of the blade to apply acting force, one end, far away from the blade support, of the multipoint mechanical measurement component is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanical measurement component; the engine blade simulated load fatigue test device further comprises a CCD camera, and the CCD camera is used for acquiring the deformation condition of the blade. According to the processing scheme, the accuracy of the blade load fatigue test is improved, and the cost of the blade simulation load fatigue test is effectively reduced.
Description
Technical Field
The application relates to the technical field of aero-engines, in particular to a fatigue test device and method for engine blade simulated loads.
Background
The blade is one of the core components of an aircraft engine and greatly affects the performance level of the aircraft engine. The aeroengine blade is subjected to high aerodynamic load during actual operation to deform. Due to the complex operation condition, the deformation condition under different working conditions is difficult to obtain by a common test method, and the test cost is expensive. Therefore, it is highly desirable to improve the experimental technical capabilities of engine blades.
The existing engine blade test device has the defects that the position and the number of applied acting force are limited, the fatigue damage effect of the pneumatic load on the blade can not be accurately simulated, and the requirement of the engine blade on the fatigue test of the simulated load can not be met.
Disclosure of Invention
In view of this, the embodiment of the application provides a device and a method for an engine blade fatigue simulation test, so as to achieve the purposes of improving the testing precision of the fatigue resistance of the engine blade under a complex working condition and reducing the test verification cost. In a first aspect, an embodiment of the application provides an engine blade simulated load fatigue test device, which comprises a horizontally arranged installation datum, wherein a movably adjustable blade support is installed in the middle area of the installation datum, and a blade is installed on the upper side of the blade support; the mounting datum is also provided with a movable supporting frame, the supporting frame is positioned on two sides of the blade support, a multipoint mechanics measuring assembly is arranged in the supporting frame, one end, close to the blade support, of the multipoint mechanics measuring assembly is in contact with the surface of the blade to apply acting force, one end, far away from the blade support, of the multipoint mechanics measuring assembly is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanics measuring assembly;
the engine blade simulated load fatigue test device further comprises a CCD camera, and the CCD camera is used for acquiring the deformation condition of the blade.
According to a concrete implementation mode of this application embodiment, the blade support with be equipped with vertical accurate guide rail, horizontal accurate guide rail, angle adjusting disk and vertical coarse adjusting guide rail between the installation benchmark in proper order, vertical coarse adjusting guide rail with the installation benchmark is connected, vertical accurate guide rail with the bottom of blade support is connected.
According to a specific implementation mode of the embodiment of the application, a transverse coarse adjustment guide rail is arranged between the support frame and the installation reference, and the support frame moves and adjusts along the transverse coarse adjustment guide rail.
According to a specific implementation manner of the embodiment of the application, the multipoint mechanics measurement assembly comprises a mechanics probe, a mechanics probe and an actuating shaft which are sequentially connected, wherein one end of the actuating shaft, which is far away from the mechanics probe, is connected with the gas supply system, and the mechanics probe, the mechanics probe and the actuating shaft are respectively arranged in the supporting frame in a plurality; the mechanical probe is used for applying force to the surface of the blade, and the mechanical probe is used for feeding back the force applied to the surface of the blade from time to time.
According to a concrete implementation of this application embodiment, gas supply system include with actuating shaft connected gas-supply pipe, setting are in pressure regulating valve on the gas-supply pipe and with the gas-supply pipe is kept away from actuating shaft's the air supply that the one end is connected, through adjusting pressure regulating valve adjusts actuating shaft's effort size.
In a second aspect, an embodiment of the present application further provides an engine blade simulated load fatigue test method, where the engine blade simulated load fatigue test apparatus according to any of the embodiments of the first aspect is adopted, the method including:
acquiring the aerodynamic deformation condition of the blade in a steady-state external flow field by adopting a CCD camera vision measurement method, and analyzing and calibrating boundary parameters and mathematical models required by simulation calculation of the steady-state aerodynamic flow field of the blade;
splitting the operation process of the unsteady aerodynamic flow field of the blade into a plurality of typical transient states;
numerically simulating the aerodynamic external flow field of the blade under the transient state by using the obtained boundary parameters and the mathematical model;
mounting the blade to a mounting reference, and calibrating the spatial position of the blade;
discretizing a spatial grid of the blade structure, and determining a characteristic position;
based on the characteristic position and the flow field simulation data, calculating to obtain a load applied to the surface of the blade, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade;
obtaining the deformation of different characteristic positions of the blade through a CCD camera, comparing the deformation with the simulated values of the deformation of the different characteristic positions of the blade, recording the load size and the direction arrangement under the transient state if the deviation value meets the test requirement, and otherwise, adjusting the selection of the characteristic positions;
repeating the above processes, determining the next transient pneumatic simulation load data of the outflowing field, and forming a load data record;
forming a load spectrum by the recorded position and the load data, applying the load spectrum to the blade, and simulating the blade load fatigue performance under unsteady and cyclic loads;
and observing and recording the deformation condition of the blade through a CCD camera, and evaluating the fatigue resistance.
According to a specific implementation manner of the embodiment of the application, the step of calculating and obtaining the load applied to the surface of the blade based on the characteristic position and the flow field simulation data, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade includes:
calibrating the coordinates of the blade flow field simulation geometric model to be consistent with the spatial coordinates of the test device;
based on the characteristic position and simulation data of the flow field outside the blade, completing simulation load local surface integral based on the characteristic position, and acquiring a normal component of the load along the surface;
extracting a load normal component of the characteristic position along the surface, and transmitting the load normal component to the actuating shaft;
and corresponding the characteristic positions to measuring point positions where the mechanical probes are arranged one by one, and applying normal components to the actual blades by the mechanical probes based on the characteristic positions and normal load simulation data.
According to a specific implementation manner of the embodiment of the application, in the step of discretizing the spatial grid of the blade structure and determining the feature position, the determination factor of the feature position includes:
a discretization mode of a spatial grid of the blade structure;
the spatial resolution of the mechanical probes and the mechanical probes depends on the distribution quantity and arrangement mode of the mechanical probes and the mechanical probes on the supporting frame;
and (4) selecting a blade structure research position.
According to a specific implementation manner of the embodiment of the application, in the step of applying the load to the blade by using the mechanical probe, the load is applied to the pressure surface of the blade alone, or is applied to both the pressure surface and the suction surface of the blade in a bidirectional manner.
According to a specific implementation manner of the embodiment of the application, the number of the selected characteristic positions is greater than or equal to 3, and the number of typical transient states split in the operation process of the unsteady aerodynamic flow field of the blade is greater than or equal to 2.
Advantageous effects
According to the engine blade simulated load fatigue test device and method in the embodiment of the application, the multipoint mechanical measurement assembly is arranged, the blade is tested in a multipoint contact mode, the load conditions of different positions can be reflected more accurately, the fatigue load conditions of the engine blade in different pneumatic load processes can be simulated accurately, a test means is provided for optimizing the fatigue resistance of the blade, and the blade test cost under different working conditions is effectively reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a side view of an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention;
FIG. 2 is a top view of an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention;
FIG. 3 is a side view of the engine blade simulated load fatigue test apparatus in accordance with an embodiment of the present invention;
FIG. 4 is a top plan view of an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention;
FIG. 5 is a schematic diagram of an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention;
FIG. 6 is a schematic view of an engine blade according to an embodiment of the present invention;
FIG. 7 is a blade mounting view of an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention;
FIG. 8 is a schematic illustration of an operational installation of a simulated load fatigue test apparatus for an engine blade according to an embodiment of the present invention;
FIG. 9 is a method of testing an engine blade simulated load fatigue test apparatus according to an embodiment of the present disclosure;
FIG. 10 is a blade grid diagram of a method for engine blade simulated load fatigue testing in accordance with an embodiment of the present invention;
FIG. 11 is a schematic view of a blade loading simulation of a method for a simulated loading fatigue test of an engine blade according to an embodiment of the invention;
FIG. 12 is a schematic diagram of a mechanical probe of a fatigue testing device for simulating load of an engine blade applying load to the blade according to an embodiment of the invention.
In the figure: 1. a blade; 1-1, pressure surface; 1-2, a suction surface; 1-3, leaf apex; 1-4, tenon root; 1-5, leading edge of leaf; 1-6, trailing edge of blade; 2. a mechanical probe; 3. a mechanical probe; 4. an actuating shaft; 5. a support frame; 6. a gas delivery pipe; 7. a pressure regulating valve; 8. a gas source; 9. installing a reference; 10. a blade holder; 11. a longitudinal precision guide rail; 12. a transverse precision guide rail; 13. an angle adjusting disk; 14. longitudinally coarsely adjusting the guide rail; 15. transversely coarsely adjusting the guide rail; 16. a CCD camera; 17. the feature location.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It should be apparent that the described embodiments are only a few embodiments of the present application, and not all embodiments. The application is capable of other and different embodiments and its several details are capable of modifications and various changes in detail without departing from the spirit of the application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. 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 application.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
The applicant researches and discovers that the prior art at present discloses a pneumatic-thermal combined test system and a test method, wherein two sides of a test chamber are respectively connected with an arc heater and a wind tunnel auxiliary device, so that the pneumatic environment can be simulated and the strength examination can be carried out as truly as possible, and the self-interference of the test device is small. However, the device has high difficulty and high cost in realizing the fatigue performance test of the blade under the complex working condition.
The device completes the simulation of the bending load by adopting an electric push rod to complete the load application on the turbine rotor blade. Yet another prior art discloses an aircraft engine blade test apparatus, and the orientation of the supporting portion of at least one supporting member is automatically adjusted along with the deformation of the blade sample, thereby avoiding the introduction of additional load due to the inconsistent supporting position and orientation, and improving the accuracy of applied load and the accuracy of test. However, the above patents cannot accurately simulate the complex and coupled aerodynamic force applied to the blade in the actual operation process, and the position and the number of applied force are limited.
The low-frequency load loading module is driven by servo hydraulic pressure, the high-frequency load loading module is driven by electromagnetic resonance, and in-situ monitoring can be completed and is used for realizing high-resolution visual dynamic monitoring of the fatigue crack initiation, expansion and fracture processes of the sample. However, the number of the nodes applied by the device is limited, so that intensive acting force application cannot be realized, and the fatigue damage effect of the pneumatic load on the blade cannot be accurately simulated.
In order to solve the problems in the prior art, through diligent experimental research, an engine blade simulated load fatigue test apparatus and method are developed, and are described in detail below with reference to fig. 1 to 12.
In a first aspect, an embodiment of the present application provides an engine blade simulated load fatigue test device, referring to fig. 1 and fig. 2, including a horizontally arranged installation datum 9, a movably adjustable blade support 10 is installed in a middle area of the installation datum 9, and a blade 1 is installed on an upper side of the blade support 10; the mounting datum 9 is also provided with a movable supporting frame 5, the supporting frame 5 is positioned on two sides of the blade support 10, a multipoint mechanics measuring assembly is arranged in the supporting frame 5, one end, close to the blade support 10, of the multipoint mechanics measuring assembly is in contact with the surface of the blade 1 to apply acting force, one end, far away from the blade support 10, of the multipoint mechanics measuring assembly is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanics measuring assembly; the engine blade simulated load fatigue test device further comprises a CCD camera 16 (charge coupled device), and the CCD camera 16 is used for acquiring the deformation condition of the blade 1.
In one embodiment, the multipoint mechanics measuring assembly comprises a mechanics probe 2, a mechanics probe 3 and an actuating shaft 4 which are connected in sequence, one end, far away from the mechanics probe 3, of the actuating shaft 4 is connected with a gas supply system, the mechanics probe 2, the mechanics probe 3 and the actuating shaft 4 are respectively arranged in a plurality of support frames 5, each group of the mechanics probe 2, the mechanics probe 3 and the actuating shaft 4 can be independently adjusted, the mechanics probe 3 is used for acting an acting force on the surface of a blade, and the mechanics probe 2 is used for feeding back the acting force acting on the surface of the blade from time to time. During installation, the engine blade 1 is installed on the blade support 10 to achieve accurate positioning of the structure, the mechanical probe 2 and the mechanical probe 3 are integrated together, the actuating shaft 4 acts on the mechanical probe 2 through the mechanical probe 3 and is used for applying acting force to the pressure surface 1-1 and the suction surface 1-2 of the engine blade 1, and the actuating capacity of the actuating shaft comes from an air supply system.
In one embodiment, a longitudinal precise guide rail 11, a transverse precise guide rail 12, an angle adjusting disc 13 and a longitudinal rough adjusting guide rail 14 are sequentially arranged between the blade support 10 and the mounting datum 9, the longitudinal rough adjusting guide rail 14 is connected with the mounting datum 9, and the longitudinal precise guide rail 11 is connected with the bottom of the blade support 10. In the detection process of the engine blade 1, the relative positions of the blade 1, the mechanical probe 2 and the mechanical probe 3 need to be accurately adjusted, aerodynamic force borne by the blade 1 in actual load is equivalent to specific extrusion load applied by the mechanical probe 2, the actual deformation condition of the blade 1 in the specific load is detected, and the actual deformation condition is compared and calibrated with a numerical simulation calculation result, so that a set of mature calculation and simulation method is finally formed, and technical conditions are finally provided for detecting the deformation condition of the blade 1 under different operation conditions. The relative position is adjusted mainly by adjusting the spatial position of the blade 1 itself, and by adjusting the transverse precision guide rail 12, the longitudinal precision guide rail 11, the angle adjusting disc 13 and the longitudinal coarse adjusting guide rail 14, the spatial position of the blade 1 is accurately adjusted.
Furthermore, a transverse coarse adjustment guide rail 15 is arranged between the support frame 5 and the installation reference 9, the support frame 5 moves and adjusts along the transverse coarse adjustment guide rail 15, and the large-amplitude adjustment of the space distance between the support frame 5 and the blade 1 is realized through the transverse coarse adjustment guide rail 15. Through the adjusting mechanism, the coordinate of the blade flow field simulation geometric model can be guaranteed to be consistent with the calibration of the testing space coordinate of the testing device, the normal component of the partial surface integral theory of the characteristic position obtained through the blade flow field simulation can be accurately acted on the actual surface position of the blade, the numerical simulation working condition and the testing working condition of the blade 1 are kept consistent, and the testing accuracy of the simulated load fatigue testing device is improved.
In one embodiment, the air supply system comprises an air pipe 6 connected with the actuating shaft 4, a pressure regulating valve 7 arranged on the air pipe 6 and an air source 8 connected with one end of the air pipe 6 far away from the actuating shaft 4, and the acting force of the mechanical probe 3 is regulated by regulating the pressure regulating valve 7.
Referring to fig. 3 to 5, in actual operation, the mechanical probe 3 in the support frame 5 acts on the surface of the blade 1 according to the designed position and acting force, and the mechanical probe 2 at the front edge of the mechanical probe 3 feeds back the acting force acting on the surface of the blade from time to time. The positions of the blade support 10, the transverse coarse adjusting guide rail 15 and other structures relative to the blade 1 are adjusted to simulate the acting direction of the simulated pneumatic load in actual operation, so that the pneumatic acting force of the blade 1 in the actual process can be accurately simulated. When the simulated pneumatic load is applied, the load conditions of different positions can be reflected more accurately by adopting a multi-point contact mode. The loading process may be applied to the pressure surface of the blade 1 alone, or may be applied to both the pressure surface and the suction surface of the blade 1. The positions of the contact points (characteristic positions 17) on each side of the blade 1 during the application of the load are not less than 3. The range of force applied by the mechanical probe 3 during actual loading may cover all features of the blade 1.
Referring to fig. 6, which is a schematic diagram of a structure of a blade 1, the blade includes a pressure surface 1-1, a suction surface 1-2, a blade tip 1-3, a tenon root 1-4, a blade leading edge 1-5, and a blade trailing edge 1-6. The positions of mainly applied load are a pressure surface 1-1 and a suction surface 1-2 of the blade 1, and the tenon root 1-4 of the blade 1 is mainly used for realizing the accurate positioning of the space position of the blade 1.
Referring to fig. 7 and 8, the blade mount 10 is configured to mate with the dovetail 1-4 structure of the blade 1 and to be secured in a test system. The transverse precision guide rail 12 and the longitudinal precision guide rail 11 are combined and used for precisely and slightly adjusting the space coordinate position of the blade 1 in a plane, and the angle adjusting disc 13 is used for adjusting the space included angle between the blade 1 and the mechanical probe 3 in the plane. The longitudinal coarse adjustment guide rail 14 is used for adjusting the spatial coordinate position of the blade 1 in a plane to a large extent. Therefore, the testing system mainly realizes the primary positioning of the blade 1 through the coarse adjustment of the transverse coarse adjustment guide rail 15 and the longitudinal coarse adjustment guide rail 14, realizes the precise positioning of the blade 1 through the transverse precise guide rail 12 and the longitudinal precise guide rail 11, and realizes the spatial included angle positioning of the blade 1 relative to the mechanical probe 3 through the angle adjusting disc 13.
In a second aspect, an embodiment of the present application further provides an engine blade simulated load fatigue test method, where an engine blade simulated load fatigue test apparatus according to any embodiment of the first aspect is used, and with reference to fig. 9, the method includes:
And 2, splitting the operation process of the unsteady aerodynamic flow field of the blade into a plurality of typical transient states.
And 3, numerically simulating the aerodynamic external flow field of the blade under the transient state by using the obtained boundary parameters and the mathematical model.
And 4, mounting the blade 1 to a mounting reference 9, and calibrating the spatial position of the blade 1.
And 5, discretizing the spatial grid of the blade structure, and determining the characteristic position 17.
And 6, calculating to obtain the load applied to the surface of the blade 1 based on the characteristic position 17 and the flow field simulation data, acting on the mechanical probe 2 through the actuating shaft 4, and applying the load to the actual blade 1.
The method specifically comprises the following steps:
step 61, completing the consistent calibration of the blade flow field simulation geometric model coordinates and the test device space coordinates;
step 62, completing simulation load local surface integral based on the characteristic position 17 and simulation data of the blade outer flow field, and acquiring a normal component of the load along the surface;
step 63, extracting a load component of the characteristic position 17 along the surface normal direction, and transmitting the load component to the actuating shaft 4;
and step 64, corresponding the characteristic positions 17 to measuring point positions where the mechanical probes 2 are arranged one by one, and applying normal components to the actual blades 1 by the mechanical probes 2 based on the characteristic positions 17 and normal load simulation data.
And 7, obtaining the deformation of different characteristic positions 17 of the blade 1 through the CCD camera 16, comparing the deformation with simulation values of the deformation of the different characteristic positions 17 of the blade 1, recording the load size and the direction arrangement under the transient state if the deviation value meets the test requirement, and otherwise, adjusting the selection of the characteristic positions 17.
And 8, repeating the processes, determining the next transient pneumatic simulation load data of the outflowing field, and forming a load data record.
And 9, forming a load spectrum by the recorded position and the load data, applying the load spectrum to the blade 1, and simulating the blade load fatigue performance under unsteady state and cyclic load.
And step 10, observing and recording the deformation condition of the blade 1 through a CCD camera 16, and evaluating the fatigue resistance.
The method of the above embodiment is described in detail below.
Referring to fig. 10, the blade 1 is discretized in simulation software to form individual feature positions 17 in space, and the spatial position of each feature position 17 can be precisely located. Thus, the determination factors of the characteristic position 17 include:
the spatial grid discretization mode of the blade structure is that the arrangement of the discretized points can meet the space realizable requirement of the mechanical probe 3;
the spatial resolution of the mechanical probes 2 and the mechanical probes 3 depends on the distribution number and arrangement mode of the mechanical probes 2 and the mechanical probes 3 on the support frame 5;
the selection of the research positions of the blade structure, the positions of different blades 1 for fatigue load investigation are inconsistent, and different numbers of characteristic positions 17 need to be arranged at the positions of a pressure surface 1-1, a suction surface 1-2, a blade tip 1-3, a tenon root 1-4, a blade front edge 1-5 and a blade rear edge 1-6 according to actual conditions.
Referring to fig. 11, the blade 1 completes the mechanical simulation in the simulation software. The blade 1 mainly bears the pneumatic loads at the pressure surface 1-1 and the suction surface 1-2 in the actual working condition, but the pneumatic loads have different values at different positions of the blade 1, and the loading of different force values at each position is difficult to realize in the actual test. Therefore, in the present embodiment, the multi-point loading of the force at a specific point (characteristic position 17) of the blade 1 is mainly realized, so that the changing aerodynamic load applied to the blade 1 is simulated with high precision, and the fatigue strength test of the blade 1 under the aerodynamic load is further completed.
Referring to fig. 12, which is a schematic view of a mechanical probe 2 applying a load to a blade 1, before numerical simulation of a pneumatic flow field of the blade 1 is performed, a test of the blade 1 under a typical steady-state operation condition is performed, a CCD camera 16 obtains a deformation condition of the blade 1 in the state by using a DIC (Digital Image Correlation ) non-contact modern optical measurement experiment technology, and compares the deformation condition with a result of the numerical simulation of the pneumatic flow field of the blade 1, and continuously adjusts a mathematical model and parameter setting of the numerical simulation of the pneumatic flow field, so that a deviation between the result of the numerical simulation of the pneumatic flow field and an experiment value obtained by the CCD camera 16 by using the DIC method is kept within an allowable error range, and a result of the numerical simulation of the pneumatic flow field can reflect a real deformation condition of the blade 1.
The method comprises the steps of obtaining a pneumatic flow field of a blade 1 in operation in a simulation mode, and splitting an unstable operation process into a plurality of typical transient states, wherein the number N of the split transient states is more than or equal to 2. Determining the key assessment test part of the blade 1 by combining the specific characteristics of the pressure surface 1-1, the suction surface 1-2, the blade tip 1-3 and the like of the structure of the blade 1; the density of positions, which can be realized by the measuring point mechanical probe 2 and can be researched and arranged by the blade 1, is determined by combining the spatial resolution and arrangement of the mechanical probe 2 and the mechanical probe 3 of the test device; and determining the discretization mode of the structural space grid of the blade 1, so that the arranged characteristic positions 17 (positions which can be realized by the mechanical probe 2) correspond to the surface characteristic positions 17 after the discretization of the structural space grid of the blade 1 one by one. The mechanical probe 3 can realize the application of force at a specific position 17 of the blade 1 through the mechanical probe 2, and the applied position and the applied size are consistent with the simulation of the blade 1.
Before an actual test, the coordinate of the blade 1 and the spatial coordinate of a test device need to be calibrated in a consistent manner, the spatial position and the posture of the blade 1 in a test system are adjusted by adjusting the transverse precise guide rail 12, the longitudinal precise guide rail 11, the transverse coarse adjustment guide rail 15, the longitudinal coarse adjustment guide rail 14 and the angle adjusting disc 13, and the spatial position and the posture of the blade 1 in the test system can also be adjusted by designing a specific structure of the blade support 10.
The magnitude of the load of the mechanical probe 2 and the mechanical probe 3 on the surface of the blade 1 is obtained through simulation, based on the determined characteristic position 17, a discrete area is reasonably divided by taking the characteristic position 17 as the center, and surface integration is carried out, so that a load value of an area taking the point as the center is obtained. Because the arc of the mechanical probe 2 is tangent to the surface arc of the blade 1, the acting force is mainly transmitted along the normal direction of the contact point, mainly is a normal component F along the surface, the normal component value F is extracted in the simulation software and transmitted to the actuating shaft 4, and the acting force is applied to the actual blade 1 as the force output. And in the practical action, the tangential friction load f of the mechanical probe 2 on the surface of the blade 1 is also included, and the tangential friction load f of the mechanical probe 2 on the surface of the blade is an additionally introduced interference quantity in the measurement mode. Since the surfaces of the mechanical probe 2 and the blade 1 are smooth, and the component of the input load of the mechanical probe 2 in the direction is small, the magnitude of the friction load f is small and can be ignored. The deformation conditions of different characteristic positions 17 of the blade 1 are obtained through the CCD camera 16 and are compared with deformation simulation values of the different characteristic positions 17 of the blade 1, and if the deviation value meets the test requirement, the load size and direction arrangement under the transient state (transient state 1) can be recorded for the later fatigue test. And if the deviation value does not meet the requirement, adjusting the selection of the characteristic position 17 to finally obtain the position condition meeting the deviation requirement. In the actual selection process, the number of the feature positions 17 is greater than or equal to 3.
After the load record of the pneumatic simulation (transient 1) of the outflowing field of the blade 1 is finished, the processes are repeated, the load data determination of the pneumatic simulation (transient 2) of the outflowing field of the blade 1 is carried out, a set of load data records is finally formed, and the number of transient states is more than or equal to 2. And forming a load spectrum by the recorded position and the load data, applying the load spectrum to the blade 1, simulating the load fatigue performance of the blade 1 under unsteady and cyclic loads, observing and recording the deformation condition of the blade 1 through the CCD camera 16, and evaluating the fatigue resistance performance of the blade 1.
The utility model provides an engine blade simulation load fatigue test device, can the accurate relative position of adjusting blade and mechanics probe in order to realize the accurate positioning of structure, the power shaft is acted on blade pressure surface and suction surface through the mechanics probe of integration on the mechanics probe and is exerted the effort, the aerodynamic force that receives the blade in actual load is equivalent for the specific extrusion load that the mechanics probe was applyed, and the actual deformation condition of inspection blade in specific load, and compare the calibration with numerical simulation calculation result, with the final one set of ripe calculation and simulation method that forms, finally provide technical condition for the deformation condition of inspection blade under the operating condition of difference.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. The engine blade simulated load fatigue test device is characterized by comprising a horizontally arranged installation reference, wherein a movably adjustable blade support is installed in the middle area of the installation reference, and a blade is installed on the upper side of the blade support; the mounting datum is also provided with a movable supporting frame, the supporting frame is positioned on two sides of the blade support, a multipoint mechanics measuring assembly is arranged in the supporting frame, one end, close to the blade support, of the multipoint mechanics measuring assembly is in contact with the surface of the blade to apply acting force, one end, far away from the blade support, of the multipoint mechanics measuring assembly is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanics measuring assembly;
the engine blade simulated load fatigue test device further comprises a CCD camera, and the CCD camera is used for acquiring the deformation condition of the blade.
2. The engine blade simulated load fatigue test device of claim 1, wherein a longitudinal precision guide rail, a transverse precision guide rail, an angle adjusting disc and a longitudinal rough adjusting guide rail are sequentially arranged between the blade support and the mounting datum, the longitudinal rough adjusting guide rail is connected with the mounting datum, and the longitudinal precision guide rail is connected with the bottom of the blade support.
3. The engine blade simulated load fatigue test device of claim 2, wherein a lateral coarse adjustment guide rail is arranged between the support frame and the mounting datum, and the support frame is adjusted in a moving mode along the lateral coarse adjustment guide rail.
4. The engine blade simulated load fatigue test device as claimed in claim 1, wherein the multipoint mechanics measurement assembly comprises a mechanics probe, a mechanics probe and an actuating shaft which are connected in sequence, one end of the actuating shaft, which is far away from the mechanics probe, is connected with the gas supply system, and the mechanics probe, the mechanics probe and the actuating shaft are respectively arranged in a plurality in the supporting frame; the mechanical probe is used for applying force to the surface of the blade, and the mechanical probe is used for feeding back the force applied to the surface of the blade from time to time.
5. The engine blade simulation load fatigue test device of claim 4, wherein the air supply system comprises an air pipe connected with the actuating shaft, a pressure regulating valve arranged on the air pipe and an air source connected with one end of the air pipe far away from the actuating shaft, and the acting force of the actuating shaft is regulated by regulating the pressure regulating valve.
6. An engine blade simulated load fatigue test method, characterized in that the engine blade simulated load fatigue test device according to any one of claims 1-5 is adopted, and the method comprises the following steps:
acquiring the aerodynamic deformation condition of the blade in a steady-state external flow field by adopting a CCD camera vision measurement method, and analyzing and calibrating boundary parameters and mathematical models required by simulation calculation of the steady-state aerodynamic flow field of the blade;
splitting the operation process of the unsteady aerodynamic flow field of the blade into a plurality of typical transient states;
numerically simulating the aerodynamic external flow field of the blade under the transient state by using the obtained boundary parameters and the mathematical model;
mounting the blade to a mounting reference, and calibrating the spatial position of the blade;
discretizing a spatial grid of the blade structure, and determining a characteristic position;
based on the characteristic position and the flow field simulation data, calculating to obtain a load applied to the surface of the blade, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade;
obtaining the deformation of different characteristic positions of the blade through a CCD camera, comparing the deformation with the deformation simulation values of the different characteristic positions of the blade, recording the load size and the direction arrangement under the transient state if the deviation value meets the test requirement, and otherwise, adjusting the selection of the characteristic positions;
repeating the above processes, and determining the next transient state pneumatic simulation load data of the outflowing field to form a load data record;
forming a load spectrum by the recorded position and the load data, applying the load spectrum to the blade, and simulating the blade load fatigue performance under unsteady and cyclic loads;
and observing and recording the deformation condition of the blade through a CCD camera, and evaluating the fatigue resistance.
7. The method for the fatigue test of the engine blade under the simulated load according to claim 6, wherein the step of calculating the load applied to the surface of the blade based on the characteristic position and the flow field simulation data, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade comprises the steps of:
calibrating the coordinates of the blade flow field simulation geometric model to be consistent with the spatial coordinates of the test device;
based on the characteristic position and simulation data of the blade external flow field, completing simulation load local surface integral based on the characteristic position, and acquiring normal component of the load along the surface;
extracting a load normal component of the characteristic position along the surface, and transmitting the load normal component to the actuating shaft;
and corresponding the characteristic positions to measuring point positions where the mechanical probes are arranged one by one, and applying normal components to the actual blades by the mechanical probes based on the characteristic positions and normal load simulation data.
8. The method for engine blade simulated load fatigue test according to claim 6, wherein in the step of discretizing the spatial grid of the blade structure and determining the characteristic position, the determination factor of the characteristic position comprises:
a discretization mode of a spatial grid of the blade structure;
the spatial resolution of the mechanical probes and the mechanical probes depends on the distribution quantity and arrangement mode of the mechanical probes and the mechanical probes on the supporting frame;
and (4) selecting a research position of the blade structure.
9. The method for testing fatigue of engine blades under simulated load according to claim 6, wherein in the step of applying load to the blades by the mechanical probe, the load is applied to the pressure surface of the blades alone or applied to both the pressure surface and the suction surface of the blades.
10. The engine blade simulation load fatigue test method according to claim 6, wherein the selected number of the characteristic positions is greater than or equal to 3, and the number of typical transient states split during the operation of the blade unsteady aerodynamic flow field is greater than or equal to 2.
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