CN115493822A - Engine blade simulated load fatigue test device and method - Google Patents

Abstract

The application provides a simulated load fatigue test device and method for engine blades, which belong to the technical field of aero-engines. The device includes a horizontal installation datum, a movable and adjustable blade bracket is installed in the middle area of the installation datum, and blades are installed on the upper side of the blade bracket. There is also a movable support frame on the installation basis, the support frame is located on both sides of the blade support, and a multi-point mechanical measurement component is arranged in the support frame, and the end of the multi-point mechanical measurement component close to the blade support contacts the surface of the blade for force Applying, the end of the multi-point mechanical measurement component away from the blade support is connected to the air supply system, and the gas supply system is used to provide force to the multi-point mechanical measurement component; the engine blade simulated load fatigue test device also includes a CCD camera, which is used to obtain Deformation of the leaves. Through the processing scheme of the present application, the accuracy of the blade load fatigue test is improved, and the cost of the blade simulated load fatigue test is effectively reduced.

Description

An engine blade simulated load fatigue test device and method

technical field

The present application relates to the technical field of aero-engines, in particular to an engine blade simulation load fatigue test device and method.

Background technique

The blade is one of the core components of an aero-engine, and affects the performance level of an aero-engine to a great extent. Aeroengine blades are deformed by high aerodynamic loads during actual operation. Due to its complex operating conditions, it is difficult to obtain its deformation under different working conditions through common test methods, and the cost of the test is expensive. Therefore, it is urgent to improve the test technology capability of engine blades.

The existing engine blade test device is limited in the position and quantity of the applied force, and cannot accurately simulate the fatigue damage effect of the aerodynamic load on the blade, and cannot meet the requirements of the simulated load fatigue test of the engine blade.

Contents of the invention

In view of this, the embodiment of the present application provides a simulated load fatigue test device and method for engine blades, so as to achieve the purpose of improving the test accuracy of the fatigue resistance performance of engine blades under complex working conditions and reducing the cost of test verification. In the first aspect, the embodiment of the present application provides a simulated load fatigue test device for engine blades, which includes a horizontal installation reference, a movable and adjustable blade support is installed in the middle area of the installation reference, and blades are installed on the upper side of the blade support. ; The installation datum is also provided with a movable support frame, the support frame is located on both sides of the blade bracket, and a multi-point mechanical measurement assembly is arranged inside the support frame, and the multi-point mechanical measurement assembly is close to the One end of the blade support is in contact with the surface of the blade to apply force, and the end of the multi-point mechanical measurement assembly away from the blade support is connected to an air supply system, and the air supply system is used for the multi-point mechanical measurement Components provide force;

The engine blade simulated load fatigue test device also includes a CCD camera, and the CCD camera is used to obtain the deformation of the blade.

According to a specific implementation of the embodiment of the present application, a longitudinal precision guide rail, a horizontal precision guide rail, an angle adjustment disc, and a longitudinal coarse adjustment guide rail are sequentially provided between the blade bracket and the installation reference, and the longitudinal coarse adjustment guide rail is connected to the The installation reference is connected, and the longitudinal precision guide rail is connected with the bottom of the blade support.

According to a specific implementation manner of the embodiment of the present application, a horizontal coarse adjustment guide rail is provided between the support frame and the installation reference, and the support frame is moved and adjusted along the horizontal coarse adjustment guide rail.

According to a specific implementation of the embodiment of the present application, the multi-point mechanical measurement assembly includes a mechanical probe, a mechanical probe, and an actuating shaft connected in sequence, and the end of the actuating shaft far away from the mechanical probe is connected to the The gas supply system is connected, and the mechanical probes, the mechanical probes and the actuating shafts are respectively arranged in multiples in the support frame; the mechanical probes are used to apply force to the blade surface, and the The mechanical probe is used to constantly feed back the force acting on the surface of the blade.

According to a specific implementation of the embodiment of the present application, the air supply system includes an air delivery pipe connected to the actuating shaft, a pressure regulating valve arranged on the air delivery pipe, and a The air source connected to one end of the actuating shaft is used to adjust the force of the actuating shaft by adjusting the pressure regulating valve.

In the second aspect, the embodiment of the present application also provides a simulated load fatigue test method for engine blades, using the engine blade simulated load fatigue test device as described in any embodiment of the first aspect above, the method comprising:

Using the CCD camera visual measurement method to obtain the aerodynamic deformation of the blade under the steady-state external flow field, it is used to analyze and calibrate the boundary parameters and mathematical models required for the simulation calculation of the steady-state aerodynamic flow field of the blade;

Split the operation process of blade unsteady aerodynamic flow field into several typical transient states;

Using the obtained boundary parameters and mathematical models, numerically simulate the aerodynamic external flow field of the blade under transient state;

Install the blade to the installation datum, and calibrate the spatial position of the blade;

Discretization of blade structure space grid to determine feature position;

Based on the characteristic position and flow field simulation data, calculate the load applied to the blade surface, act on the mechanical probe through the actuating shaft and apply the load to the actual blade;

Obtain the deformation of different characteristic positions of the blade through the CCD camera, and compare it with the simulation value of the deformation of different characteristic positions of the blade. If the deviation value meets the test requirements, record the magnitude and direction of the load under the transient state, otherwise the selection of the characteristic position will be adjusted;

Repeat the above process to determine the load data of the next transient external flow field aerodynamic simulation to form a load data record;

The recorded position and load data are formed into a load spectrum, which is applied to the blade to simulate the load fatigue performance of the blade under unsteady and cyclic loads;

The deformation of the blade is observed and recorded by the CCD camera to evaluate the fatigue resistance.

According to a specific implementation of the embodiment of the present application, the step of calculating and obtaining the load applied to the surface of the blade based on the characteristic position and flow field simulation data, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade includes: :

The coordinates of the simulation geometric model of the blade flow field are calibrated consistent with the spatial coordinates of the test device;

Based on the characteristic position and the simulation data of the external flow field of the blade, the local area integration of the simulation load based on the characteristic position is completed, and the normal component of the load along the surface is obtained;

Extract the normal component of the load along the feature position and transmit it to the actuating axis;

The characteristic position is one-to-one corresponding to the position of the measuring point where the mechanical probe is arranged. Based on the characteristic position and the normal load simulation data, the mechanical probe applies the normal component to the actual blade.

According to a specific implementation manner of the embodiment of the present application, in the step of discretizing the spatial grid of the blade structure and determining the characteristic position, the determining factors of the characteristic position include:

Discretization method of blade structural space grid;

The spatial resolution of mechanical probes and mechanical probes, the spatial resolution depends on the number and arrangement of mechanical probes and mechanical probes on the support frame;

Selection of location for blade structure study.

According to a specific implementation of the embodiment of the present application, in the step of applying a load to the blade by the mechanical probe, the load is applied to the pressure surface of the blade alone, or bidirectionally applied to the pressure surface and the suction surface of the blade.

According to a specific implementation of the embodiment of the present application, the number of selected characteristic positions is greater than or equal to 3, and the number of typical transient states split by the operating process of the unsteady aerodynamic flow field of the blade is greater than or equal to 2 .

Beneficial effect

The engine blade simulation load fatigue test device and method in the embodiment of the application can more accurately reflect the load conditions at different positions by setting up multi-point mechanical measurement components and adopting a multi-point contact method to accurately simulate the engine The fatigue loads of the blades under different aerodynamic loads provide testing methods for the optimization of the fatigue strength of the blades, and effectively reduce the cost of blade testing under different working conditions.

Description of drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the accompanying drawings that need to be used in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. Those of ordinary skill in the art can also obtain other drawings based on these drawings without any creative effort.

Fig. 1 is a side view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 2 is a top view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 3 is a working side view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 4 is a working top view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 5 is a working schematic diagram of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 6 is a schematic structural diagram of an engine blade according to an embodiment of the present invention;

Fig. 7 is a blade installation diagram of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 8 is a schematic diagram of working and installation of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 9 is a test method of an engine blade simulated load fatigue test device according to an embodiment of the present invention;

Fig. 10 is a blade grid diagram of an engine blade simulated load fatigue test method according to an embodiment of the present invention;

Fig. 11 is a schematic diagram of a simulated load simulation method for a blade of an engine blade according to an embodiment of the present invention;

Fig. 12 is a schematic diagram of a mechanical probe applying a load to a blade of an engine blade simulated load fatigue test device according to an embodiment of the present invention.

In the figure: 1, blade; 1-1, pressure surface; 1-2, suction surface; 1-3, blade tip; 1-4, tenon root; 1-5, leaf leading edge; 1-6, leaf trailing edge ;2. Mechanical probe; 3. Mechanical probe; 4. Actuating shaft; 5. Support frame; 6. Air pipe; 7. Pressure regulating valve; 8. Air source; 1. Longitudinal precision guide rail; 12. Horizontal precision guide rail; 13. Angle adjustment disc; 14. Longitudinal coarse adjustment guide rail; 15. Horizontal coarse adjustment guide rail; 16. CCD camera; 17. Characteristic position.

detailed description

Embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.

Embodiments of the present application are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of this application, not all of them. The present application can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.

It is noted that the following describes various aspects of the embodiments that are 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 illustrative only. Based on the present application one skilled in the art should appreciate that an 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, any number of the aspects set forth herein can be used to implement an apparatus and/or practice a method. In addition, such an apparatus may be implemented and/or such a method practiced using other structure and/or functionality than one or more of the aspects set forth herein.

It should also be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic idea of the application, and only the components related to the application are shown in the drawings rather than the number, shape and number of components in actual implementation. Dimensional drawing, the type, quantity and proportion of each component can be changed arbitrarily during actual implementation, and the component layout type may also be more complicated.

Additionally, in the following description, specific details are provided to facilitate a thorough understanding of examples. However, it will be understood by those skilled in the art that the described aspects may be practiced without these specific details.

The applicant's research found that the current prior art discloses an aerodynamic-thermal joint test system and test method. The two sides of the test chamber are respectively connected with the arc heater and the auxiliary equipment of the wind tunnel, which can simulate the aerodynamic environment as realistically as possible. And carry out strength assessment, the test equipment itself has little interference. However, it is difficult and expensive for this equipment to realize the fatigue performance test of blades under complex working conditions.

Another technology related to the bending stiffness test device of the turbine rotor blade of the aero-engine, the device completes the load application on the turbine rotor blade by using the electric push rod to complete the simulation of the bending load. And another prior art discloses an aeroengine blade test device, and the orientation of the support part of at least one support member can be automatically adjusted along with the deformation of the blade sample, thereby avoiding additional damage caused by uncoordinated support position and orientation. The introduction of the load improves the accuracy of the applied load and the accuracy of the test. However, the above patents cannot accurately simulate the complex and coupled aerodynamic forces experienced by the blades during actual operation, and the position and amount of force applied are limited.

Another technology related to the in-situ test device and method for the high-low cycle composite fatigue performance of materials. The low-frequency load loading module is driven by servo hydraulics, and the high-frequency load loading module is driven by electromagnetic resonance, and in-situ monitoring can be completed to realize the test High-resolution visual dynamic monitoring of sample fatigue crack initiation, growth and fracture process. However, the number of nodes applied by this device is limited, and intensive force application cannot be realized, and the accurate simulation of the fatigue damage effect of aerodynamic load on the blade cannot be satisfied.

In order to solve the above-mentioned problems in the prior art, the applicant has developed an engine blade simulated load fatigue test device and method through diligent testing and research, which will be described in detail below with reference to FIGS. 1 to 12 .

In the first aspect, the embodiment of the present application provides a simulated load fatigue test device for engine blades, referring to Fig. 1 and Fig. 2, including a horizontally arranged installation datum 9, a movable and adjustable blade bracket 10 is installed in the middle area of the installation datum 9, The blade 1 is installed on the upper side of the blade support 10; the installation datum 9 is also provided with a movable support frame 5, the support frame 5 is located on both sides of the blade support 10, and a multi-point mechanical measurement component is arranged in the support frame 5, and the multi-point mechanical measurement One end of the assembly close to the blade support 10 is in contact with the surface of the blade 1 to apply force, and the end of the multi-point mechanical measurement assembly away from the blade support 10 is connected to the air supply system, and the air supply system is used to provide force to the multi-point mechanical measurement assembly; The blade simulated load fatigue test device also includes a CCD camera 16 (charge coupled device, charge coupled device), and the CCD camera 16 is used to obtain the deformation of the blade 1 .

In one embodiment, the multi-point mechanical measurement assembly includes a mechanical probe 2, a mechanical probe 3 and an actuating shaft 4 connected in sequence, the end of the actuating shaft 4 away from the mechanical probe 3 is connected to the gas supply system, the mechanical probe 2, The mechanical probes 3 and the actuating shafts 4 are respectively arranged in multiples in the support frame 5, each group of the mechanical probes 2, the mechanical probes 3 and the actuating shafts 4 can be adjusted independently, and the mechanical probes 3 are used to apply the force On the surface of the blade, the mechanical probe 2 is used to constantly feed back the force acting on the surface of the blade. During installation, the engine blade 1 is installed on the blade bracket 10 to realize the precise positioning of the structure, the mechanical probe 2 and the mechanical probe 3 are integrated together, and the actuating shaft 4 acts on the mechanical probe 2 through the mechanical probe 3 to control the engine. The pressure surface 1-1 and the suction surface 1-2 of the blade 1 apply force, and their actuation ability comes from the air supply system.

In one embodiment, between the blade support 10 and the installation reference 9, there are longitudinal precision guide rails 11, horizontal precision guide rails 12, angle adjustment discs 13 and longitudinal coarse adjustment guide rails 14, and the longitudinal coarse adjustment guide rails 14 are connected to the installation reference 9. The longitudinal precision guide rail 11 is connected with the bottom of the blade support 10 . In the detection process of the engine blade 1, it is necessary to accurately adjust the relative position of the blade 1, the mechanical probe 2 and the mechanical probe 3, and the aerodynamic force received by the blade 1 in the actual load is equivalent to the specific squeeze exerted by the mechanical probe 2. Compressive load, and check the actual deformation of the blade 1 in a specific load, and compare and calibrate it with the numerical simulation calculation results to finally form a set of mature calculation and simulation methods, and finally to test the blade 1 under different operating conditions The deformation situation provides technical conditions. Adjusting the relative position is mainly by adjusting the spatial position of the blade 1 itself, and by adjusting the horizontal precision guide rail 12, the longitudinal precision guide rail 11, the angle adjustment disc 13, and the longitudinal rough adjustment guide rail 14 to realize the precise adjustment of the spatial position of the blade 1.

Further, a horizontal coarse adjustment guide rail 15 is provided between the support frame 5 and the installation reference 9, and the support frame 5 moves and adjusts along the horizontal coarse adjustment guide rail 15, and the large spatial distance between the support frame 5 and the blade 1 is realized through the horizontal coarse adjustment guide rail 15. Adjustment. Through the above adjustment mechanism, it is possible to ensure that the coordinates of the simulation geometric model of the blade flow field are consistent with the calibration of the test space coordinates of the test device, so that the theoretical normal component of the local area integral of the characteristic position obtained through the simulation of the blade flow field can accurately act on the actual blade surface position , so that the numerical simulation working condition of the blade 1 is consistent with the experimental test working condition, and the test accuracy of the simulated load fatigue test device is improved.

In one embodiment, the air supply system includes an air delivery pipe 6 connected to the actuation shaft 4, a pressure regulating valve 7 arranged on the air delivery pipe 6, and an air source 8 connected to the end of the air delivery pipe 6 away from the actuation shaft 4, The force of the mechanical probe 3 is adjusted by adjusting the pressure regulating valve 7 .

Referring to Figures 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 force, and the mechanical probe 2 at the leading edge of the mechanical probe 3 acts on the feedback from time to time. force on the blade surface. By adjusting the position of the blade support 10, the transverse coarse guide rail 15 and other structures relative to the blade 1 to simulate the acting direction of the simulated aerodynamic load in actual operation, the aerodynamic force on the blade 1 in the actual process can be accurately simulated. When applying the simulated aerodynamic load, the multi-point contact method can be used to more accurately reflect the load conditions at different positions. The load application process can be applied solely on the pressure surface of the blade 1, or can be applied bidirectionally on the pressure surface and the suction surface of the blade 1. During the load application process, there are no less than three contact points (characteristic positions 17) on each surface of the blade 1 . During the actual load application process, the application force range of the mechanical probe 3 can cover all the features of the blade 1 .

Referring to Figure 6, it is a schematic diagram of the structure of the 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 where the main load is applied are the pressure surface 1-1 and the suction surface 1-2 of the blade 1, and the tenon root 1-4 of the blade 1 is mainly used to realize the precise positioning of the spatial position of the blade 1.

Referring to Fig. 7 and Fig. 8, the blade bracket 10 is used to cooperate with the structure of the tenon 1-4 of the blade 1, and is fixed in the testing system. The horizontal precision guide rail 12 and the longitudinal precision guide rail 11 are combined and used to precisely and slightly adjust the spatial coordinate position of the blade 1 in the plane, and the angle adjustment disc 13 is used to adjust the spatial angle between the blade 1 and the mechanical probe 3 in the plane. The longitudinal coarse adjustment guide rail 14 is used for largely adjusting the spatial coordinate position of the blade 1 in the plane. Therefore, the test system mainly realizes the preliminary positioning of the blade 1 through the rough adjustment of the horizontal coarse adjustment guide rail 15 and the longitudinal coarse adjustment guide rail 14, realizes the precise positioning of the blade 1 through the horizontal precision guide rail 12 and the longitudinal precision guide rail 11, and realizes the precise positioning of the blade 1 through the angle adjustment disc 13. The space angle positioning of the blade 1 relative to the mechanical probe 3 is realized.

In the second aspect, the embodiment of the present application also provides a simulated load fatigue test method for engine blades, using the engine blade simulated load fatigue test device as in any embodiment of the first aspect, referring to FIG. 9 , the method includes:

Step 1. Using the CCD camera 16 visual measurement method to obtain the aerodynamic deformation of the blade under the steady-state external flow field, which is used to analyze and calibrate the boundary parameters and mathematical models required for the simulation calculation of the steady-state aerodynamic flow field of the blade.

Step 2, splitting the operation process of the unsteady aerodynamic flow field of the blade into several typical transient states.

Step 3. Using the obtained boundary parameters and mathematical model, numerically simulate the aerodynamic external flow field of the blade under transient state.

Step 4, install the blade 1 to the installation datum 9, and calibrate the spatial position of the blade 1.

Step 5, discretize the spatial grid of the blade structure, and determine the characteristic position 17 .

Step 6. Based on the characteristic position 17 and the flow field simulation data, calculate and obtain the load applied to the surface of the blade 1 , act on the mechanical probe 2 through the actuating shaft 4 and apply the load to the actual blade 1 .

This step specifically includes:

Step 61, complete the consistent calibration of the coordinates of the simulation geometric model of the blade flow field and the spatial coordinates of the test device;

Step 62, based on the characteristic position 17 and the simulation data of the blade external flow field, complete the local area integration of the simulation load based on the characteristic position, and obtain the normal component of the load along the surface;

Step 63, extracting the normal component of the load at the characteristic position 17, and transmitting it to the actuating axis 4;

Step 64: Corresponding the characteristic position 17 with the measuring point position where the mechanical probe 2 is arranged, and based on the characteristic position 17 and the normal load simulation data, the mechanical probe 2 applies a normal component to the actual blade 1 .

Step 7. Obtain the deformation of the different characteristic positions 17 of the blade 1 through the CCD camera 16, and compare it with the simulation value of the deformation of the different characteristic positions 17 of the blade 1. If the deviation value meets the test requirements, record the magnitude and direction of the load in the transient state, otherwise The selection of feature location 17 will be adjusted.

Step 8. Repeat the above process to determine the load data of the next transient external flow field aerodynamic simulation to form a load data record.

Step 9, forming a load spectrum from the recorded position and load data, and applying it to the blade 1 to simulate the load fatigue performance of the blade under unsteady and cyclic loads.

Step 10, observe and record the deformation of the blade 1 through the CCD camera 16, and evaluate the anti-fatigue performance.

The method in the above embodiment will be described in detail below.

Referring to FIG. 10 , the discretization operation of the blade 1 is completed in the simulation software to form various characteristic positions 17 in space, and the spatial position of each characteristic position 17 can be precisely positioned. Therefore, the determining factors of feature location 17 include:

Discretization of blade structure space grid, the arrangement of discretized points should be able to meet the spatially achievable requirements of mechanical probe 3;

The spatial resolution of the mechanical probe 2 and the mechanical probe 3 depends on the distribution quantity and arrangement of the mechanical probe 2 and the mechanical probe 3 on the support frame 5;

The selection of the research location of the blade structure, different blades 1 have inconsistent locations for fatigue load investigation, and it is necessary to select the pressure surface 1-1, suction surface 1-2, blade tip 1-3, mortise root 1-4, blade Different numbers of characteristic positions 17 are arranged at the leading edge 1-5 and the leaf trailing edge 1-6.

Referring to Fig. 11, the mechanical simulation of the blade 1 is completed in the simulation software. In the actual working condition, the blade 1 is mainly subjected to the aerodynamic load at the pressure surface 1-1 and the suction surface 1-2, but the aerodynamic load has different values at different positions of the blade 1, and it is difficult to realize the aerodynamic load at each point in the actual test. Positions are loaded with different force values. Therefore, in this embodiment, the multi-point loading of force is mainly realized at the specific point (characteristic position 17) of the blade 1, and the constantly changing aerodynamic load suffered by the blade 1 is simulated with high precision, and then the aerodynamic load under the aerodynamic load is completed. Test of fatigue strength of blade 1.

Referring to FIG. 12 , it is a schematic diagram of the mechanical probe 2 applying a load to the blade 1. Before carrying out the numerical simulation of the aerodynamic flow field of the blade 1, the experimental test of the blade 1 under a typical steady-state operating condition is first carried out, and the CCD camera 16 adopts the DIC ( Digital Image Correlation (Digital Image Correlation) non-contact modern optical measurement experiment technology to obtain the deformation of the blade 1 in this state, and compare it with the numerical simulation results of the aerodynamic flow field of the blade 1, and constantly adjust the mathematics of the numerical simulation of the aerodynamic flow field The model and parameters are set so that the deviation between the numerical simulation results of the aerodynamic flow field and the experimental value obtained by the CCD camera 16 using the DIC method is kept within the allowable error range, so that the numerical simulation results of the aerodynamic flow field can reflect the real deformation of the blade 1 .

The aerodynamic flow field of the blade 1 in operation is obtained through simulation, and the unsteady operation process is split into several typical transient states, and the number of split transient states is N≥2. Combining the specific characteristics of the pressure surface 1-1, suction surface 1-2, and blade tip 1-3 of the blade 1 structure to determine the key assessment and test parts of the blade 1; combining the spatial resolution and arrangement of the mechanical probe 2 and mechanical probe 3 of the test device To clarify the location density of the measuring point that can be studied and arranged by the blade 1 and the position that the mechanical probe 2 can achieve; determine the discretization method of the structural space grid of the blade 1, so that the characteristic position 17 of the arrangement (the position that the mechanical probe 2 can achieve) is the same as that of the blade 1 The surface feature positions 17 after the discretization of the structural space grid correspond to each other. This enables the mechanical probe 3 to apply force at a specific position 17 of the blade 1 through the mechanical probe 2 , and the applied position and magnitude are consistent with the simulation of the blade 1 .

Before the actual test, the coordinates of the blade 1 and the space coordinates of the test device need to be calibrated uniformly by adjusting the horizontal precision guide rail 12, the longitudinal precision guide rail 11, the horizontal coarse adjustment guide rail 15, the longitudinal coarse adjustment guide rail 14 and the angle adjustment disc 13. The spatial position and attitude adjustment of the blade 1 in the test system can also be supplemented by designing the specific structure of the blade support 10 to adjust the spatial position and attitude of the blade 1 in the test system.

The magnitude of the load on the surface of the blade 1 by the mechanical probe 2 and the mechanical probe 3 is obtained through simulation. Based on the determined characteristic position 17, with the characteristic position 17 as the center, the discrete area is reasonably divided, and the area integration is performed to obtain the The point is the load value of the central region. Since the arc of the mechanical probe 2 is tangent to the arc of the surface of the blade 1, its force is mainly transmitted along the normal direction of the contact point, mainly the normal component F along the surface, and the value of the normal component F in Extracted from the simulation software, and transmitted to the actuating shaft 4, as the force output to exert force on the actual blade 1. However, the actual effect also includes the tangential friction load f of the mechanical probe 2 on the surface of the blade 1, and the tangential friction load f of the mechanical probe 2 on the blade surface is an additional interference introduced by this measurement method. Since the surface of the mechanical probe 2 and the blade 1 is smooth, and the component of the input load of the mechanical probe 2 in this direction is also small, the magnitude of the friction load f is small and can be ignored. Obtain the deformation situation of different characteristic positions 17 of blade 1 by CCD camera 16, and compare with the deformation simulation value of different characteristic positions 17 of blade 1, if the deviation value meets the test requirements, the deformation under the transient state (transient state 1) can be obtained. Load magnitude and direction arrangement are recorded for later fatigue test. If the deviation value does not meet the requirements, then adjust the selection of the characteristic position 17, and finally obtain the position situation that meets the deviation requirements. In the actual selection process, the number of selected feature positions 17 is ≥ 3.

After completing the load records of the aerodynamic simulation (transient 1) of the outer flow field of blade 1, repeat the above process, carry out the determination of the load data of the aerodynamic simulation of the outer flow field of blade 1 (transient 2), and finally form a set of load data records, and The number of transient states ≥ 2. Apply the recorded position and load data to form a load spectrum on the blade 1 to simulate the load fatigue performance of the blade 1 under unsteady and cyclic loads, and observe and record the deformation of the blade 1 through the CCD camera 16 to evaluate the fatigue resistance of the blade 1 performance.

The engine blade simulation load fatigue test device of the present application can accurately adjust the relative position of the blade, the mechanical probe and the mechanical probe to realize the precise positioning of the structure, and the actuating shaft acts on the pressure surface of the blade through the mechanical probe integrated on the mechanical probe and the suction surface to apply force, the aerodynamic force of the blade in the actual load is equivalent to the specific extrusion load applied by the mechanical probe, and the actual deformation of the blade in the specific load is checked, and compared with the numerical simulation calculation results Compare and calibrate to finally form a set of mature calculation and simulation methods, and finally provide technical conditions for testing the deformation of blades under different operating conditions.

The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the application. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be based on 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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