CN115493822B - 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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- CN115493822B CN115493822B CN202211042596.2A CN202211042596A CN115493822B CN 115493822 B CN115493822 B CN 115493822B CN 202211042596 A CN202211042596 A CN 202211042596A CN 115493822 B CN115493822 B CN 115493822B
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- 238000000034 method Methods 0.000 title claims abstract description 44
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- 125000004122 cyclic group Chemical group 0.000 claims description 4
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- 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
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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Abstract
The application provides an engine blade simulated load fatigue test device and method, which belong to the technical field of aeroengines, wherein the device comprises a horizontally arranged installation datum, a movable and adjustable blade bracket is arranged in the middle area of the installation datum, and blades are arranged on the upper side of the blade bracket; the mounting standard is also provided with a movable supporting frame, the supporting frame is positioned at two sides of the blade bracket, a multipoint mechanical measurement assembly is arranged in the supporting frame, one end of the multipoint mechanical measurement assembly, which is close to the blade bracket, is contacted with the surface of the blade to apply acting force, and one end of the multipoint mechanical measurement assembly, which is far away from the blade bracket, is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanical measurement assembly; the engine blade simulation load fatigue test device further comprises a CCD camera, and the CCD camera is used for acquiring the deformation condition of the blade. By the processing scheme, the accuracy of the blade load fatigue test is improved, and the cost of the blade load fatigue test simulation is effectively reduced.
Description
Technical Field
The application relates to the technical field of aeroengines, in particular to an engine blade simulated load fatigue test device and method.
Background
The blade is one of the core components of an aircraft engine and affects the performance level of the aircraft engine to a large extent. The aero-engine blades are deformed by high aerodynamic loads during actual operation. Because of the complex operation conditions, the deformation condition of the steel under different conditions is difficult to obtain by a common test method, and the test cost is high. Thus, there is a need to improve the test technology 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 cannot be accurately simulated, and the requirement of the engine blade simulated load fatigue test cannot be met.
Disclosure of Invention
In view of the above, the embodiment of the application provides a device and a method for simulating load fatigue test of an engine blade, so as to achieve the purposes of improving the test precision of the fatigue resistance of the engine blade under complex working conditions and reducing the test verification cost. In a first aspect, an embodiment of the present application provides an engine blade fatigue test apparatus, including a horizontally disposed mounting reference, a movably adjustable blade bracket being mounted in a middle area of the mounting reference, a blade being mounted on an upper side of the blade bracket; the installation standard is also provided with a movable supporting frame, the supporting frame is positioned at two sides of the blade support, a multipoint mechanical measurement assembly is arranged in the supporting frame, one end of the multipoint mechanical measurement assembly, which is close to the blade support, is in contact with the surface of the blade to apply acting force, one end of the multipoint mechanical measurement assembly, which is far away from the blade support, is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanical measurement 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 specific implementation manner of the embodiment of the application, a longitudinal precise guide rail, a transverse precise guide rail, an angle adjusting disc and a longitudinal rough adjustment guide rail are sequentially arranged between the blade support and the installation reference, the longitudinal rough adjustment guide rail is connected with the installation reference, and the longitudinal precise guide rail is connected with the bottom of the blade support.
According to a specific implementation manner of the embodiment of the application, a transverse rough adjusting guide rail is arranged between the supporting frame and the installation standard, and the supporting frame is movably adjusted along the transverse rough adjusting guide rail.
According to a specific implementation manner of the embodiment of the application, the multipoint mechanical measurement assembly comprises a mechanical probe, a mechanical probe and an actuating shaft which are sequentially connected, wherein one end of the actuating shaft, which is far away from the mechanical probe, is connected with the air supply system, and the mechanical probe, the mechanical probe and the actuating shaft are respectively arranged into a plurality of parts 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 acting force applied to the surface of the blade from time to time.
According to a specific implementation manner of the embodiment of the application, 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.
In a second aspect, an embodiment of the present application further provides a method for testing fatigue of an engine blade under simulated load, where the apparatus for testing fatigue of an engine blade under simulated load according to any one of the embodiments of the first aspect is used, and the method includes:
The CCD camera vision measurement method is adopted to obtain the pneumatic deformation condition of the blade under the steady-state outflow field, and the pneumatic deformation condition is used for analyzing and calibrating boundary parameters and mathematical models required by the simulation calculation of the steady-state pneumatic flow field of the blade;
Splitting the operation process of the unsteady pneumatic flow field of the blade into a plurality of typical transient states;
adopting the obtained boundary parameters and mathematical model to numerically simulate the pneumatic external flow field of the blade in the transient state;
mounting the blade to a mounting reference, and calibrating the spatial position of the blade;
discretizing a space grid of the blade structure, and determining a characteristic position;
based on the characteristic position and the flow field simulation data, calculating to obtain the load applied to the surface of the blade, and applying the load to the actual blade by acting on the mechanical probe through the actuating shaft;
obtaining deformation of different characteristic positions of the blade through a CCD camera, comparing the deformation with simulation values of the deformation of the different characteristic positions of the blade, recording the load size and direction arrangement under the transient state if the deviation value meets the test requirement, otherwise, adjusting the selection of the characteristic positions;
Repeating the above processes, and carrying out the pneumatic simulation load data determination of the outflow field of the next transient state to form a load data record;
Forming a load spectrum by the recorded position and load data, applying the load spectrum to the blade, and simulating the fatigue performance of the blade under unsteady state and cyclic load;
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 present application, the step of calculating and obtaining the load applied to the surface of the blade based on the feature position and the flow field simulation data, acting on the mechanical probe through the actuation shaft, and applying the load to the actual blade includes:
calibrating the blade flow field simulation geometric model coordinate with the space coordinate of the test device;
based on the characteristic position and the simulation data of the external flow field of the blade, completing the local area integral of the simulation load based on the characteristic position, and obtaining the normal component of the load along the surface;
extracting a load along-plane normal component of the characteristic position and transmitting the load along-plane normal component to an actuating shaft;
The characteristic positions are in one-to-one correspondence with the measuring point positions where the mechanical probes are arranged, and the mechanical probes apply normal components to the actual blades based on the characteristic positions and normal load simulation data.
According to a specific implementation manner of the embodiment of the present application, in the step of determining the feature position in the discretization of the spatial grid of the blade structure, the determining factors of the feature position include:
A blade structure space grid discretization mode;
The spatial resolution of the mechanical probe and the mechanical probe depends on the distribution quantity and arrangement mode of the mechanical probe and the mechanical probe on the supporting frame;
and selecting a leaf structure research position.
According to a specific implementation manner of the embodiment of the present application, in the step of applying a load to the blade through the mechanical probe, the load is applied to the pressure surface of the blade separately or applied to the pressure surface and the suction surface of the blade in two directions.
According to a specific implementation manner of the embodiment of the application, the number of the selected characteristic positions is more than or equal to 3, and the number of typical transient states of the blade unsteady pneumatic flow field, which are split in the operation process, is more than or equal to 2.
Advantageous effects
According to the device and the method for testing the fatigue of the engine blade by simulating the load, disclosed by the embodiment of the application, the multi-point mechanical measurement assembly is arranged, the blade is tested in a multi-point contact mode, the load conditions of different positions can be reflected more accurately, the fatigue load conditions of the engine blade in the process of receiving different pneumatic loads can be simulated accurately, a testing means is provided for optimizing the fatigue resistance of the blade, and the testing cost of the blade 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 that are needed 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 that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
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 an engine blade simulated load fatigue test apparatus according to 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 illustrating operation 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 configuration according to an embodiment of the present disclosure;
FIG. 7 is a blade mounting 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 an engine blade simulated load fatigue test apparatus according to an embodiment of the present invention in operation and installation;
FIG. 9 is a test method of an engine blade simulated load fatigue test apparatus 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 on a blade of an engine blade simulated load fatigue test method according to an embodiment of the present invention;
FIG. 12 is a schematic illustration of an engine blade simulated load fatigue test apparatus mechanical probe applying a load to a blade in accordance with an embodiment of the present invention.
In the figure: 1. a blade; 1-1, a pressure surface; 1-2, a suction surface; 1-3, blade tips; 1-4, tenon root; 1-5, leading edge of leaf; 1-6, leaf trailing edge; 2. a mechanical probe; 3. a mechanical probe; 4. a driving shaft; 5. a support frame; 6. a gas pipe; 7. a pressure regulating valve; 8. a gas source; 9. installing a reference; 10. a blade support; 11. a longitudinal precision guide rail; 12. a transverse precision guide rail; 13. an angle adjusting plate; 14. a longitudinal coarse adjustment guide rail; 15. a transverse rough adjustment guide rail; 16. a CCD camera; 17. feature location.
Detailed Description
Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present application will become apparent to those skilled in the art from the following disclosure, which describes the embodiments of the present application with reference to specific examples. It will be apparent that the described embodiments are only some, but not all, embodiments of the application. The application may be practiced or carried out in other embodiments that depart from the specific details, and the details of the present description may be modified or varied from the spirit and scope of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that various aspects of the embodiments are described below within the scope of the following 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 disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, 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. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concept of the present application by way of illustration, and only the components related to the present application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide 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 find that the prior art discloses a pneumatic and thermal combined test system and a test method, wherein two sides of the test cabin are respectively connected with an arc heater and wind tunnel auxiliary equipment, so that the pneumatic environment can be simulated as truly as possible, the strength assessment can be carried out, and the test equipment has small interference. However, the device has the advantages of high difficulty and high cost in fatigue performance test of the blade under the complex working condition.
Another technique relates to an aero-engine turbine rotor blade bending stiffness test apparatus that performs load application to turbine rotor blades by employing an electric pushrod to perform simulation of bending loads. And another prior art discloses an aeroengine blade test device, and the position of the supporting part of at least one support piece can be automatically adjusted along with the deformation of a blade sample, thereby avoiding the introduction of additional load caused by inconsistent supporting position and position, and improving the accuracy of load application and test. However, the above patent cannot accurately simulate the complex and coupled aerodynamic forces to which the blade is subjected in the actual running process, and the position and the number of the applied forces are limited.
The other technology related to the material high-low cycle composite fatigue performance in-situ test device and method is that the low-frequency load loading module is driven by servo hydraulic pressure, the high-frequency load loading module is driven by electromagnetic resonance, in-situ monitoring can be completed, and the device and the method are used for realizing high-resolution visual dynamic monitoring of the specimen fatigue crack initiation, propagation and fracture process. However, the device has limited number of applied nodes, can not realize dense acting force application, and can not meet the effect of accurately simulating fatigue damage of pneumatic load to the blade.
The applicant has developed an engine blade simulated load fatigue test apparatus and method, which are described in detail below with reference to fig. 1 to 12, through an effort test study in order to solve the problems of the prior art.
In a first aspect, an embodiment of the present application provides an engine blade fatigue test apparatus, referring to fig. 1 and 2, including a horizontally arranged mounting reference 9, a movably adjustable blade bracket 10 being mounted in a middle area of the mounting reference 9, and a blade 1 being mounted on an upper side of the blade bracket 10; the mounting standard 9 is also provided with a movable supporting frame 5, the supporting frame 5 is positioned at two sides of the blade bracket 10, the supporting frame 5 is internally provided with a multipoint mechanical measurement assembly, one end of the multipoint mechanical measurement assembly, which is close to the blade bracket 10, is contacted with the surface of the blade 1 to apply acting force, and one end of the multipoint mechanical measurement assembly, which is far away from the blade bracket 10, is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanical measurement assembly; the engine blade simulated load fatigue test device further comprises a CCD camera 16 (charge coupled device, a charge coupled device), wherein the CCD camera 16 is used for acquiring the deformation condition of the blade 1.
In one embodiment, the multipoint mechanical measurement assembly comprises a mechanical probe 2, a mechanical probe 3 and an actuating shaft 4 which are sequentially connected, one end, far away from the mechanical probe 3, of the actuating shaft 4 is connected with an air supply system, the mechanical probe 2, the mechanical probe 3 and the actuating shaft 4 are respectively arranged into a plurality of parts in a supporting frame 5, each group of the mechanical probe 2, the mechanical probe 3 and the actuating shaft 4 can be independently adjusted, the mechanical probe 3 is used for applying acting force to the surface of the blade, and the mechanical probe 2 is used for feeding back the acting force applied to the surface of the blade from time to time. When the engine blade 1 is installed on the blade bracket 10, the accurate positioning of the structure is realized, 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 engine blade is derived 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 guide rail 14 are sequentially arranged between the blade bracket 10 and the mounting standard 9, the longitudinal rough guide rail 14 is connected with the mounting standard 9, and the longitudinal precise guide rail 11 is connected with the bottom of the blade bracket 10. In the process of detecting 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 the actual load is equivalent to a specific extrusion load applied by the mechanical probe 2, the actual deformation condition of the blade 1 in the specific load is checked, and the actual deformation condition is compared and calibrated with a numerical simulation calculation result, so that a set of mature calculation and simulation methods are finally formed, and technical conditions are finally provided for checking 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, and the spatial position of the blade 1 is accurately adjusted by adjusting the transverse precise guide rail 12, the longitudinal precise guide rail 11, the angle adjusting disc 13 and the longitudinal rough adjustment guide rail 14.
Further, a transverse rough adjusting guide rail 15 is arranged between the supporting frame 5 and the mounting standard 9, the supporting frame 5 is movably adjusted along the transverse rough adjusting guide rail 15, and the space distance between the supporting frame 5 and the blade 1 is greatly adjusted through the transverse rough adjusting guide rail 15. Through the adjusting mechanism, the coordinate of the blade flow field simulation geometric model can be ensured to be consistent with the test space coordinate of the test device, so that the local area integral theoretical normal component of the characteristic position obtained through the blade flow field simulation can precisely act on the actual blade surface position, the numerical simulation working condition and the test working condition of the blade 1 are kept consistent, and the test accuracy of the simulated load fatigue test 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 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 structures such as the blade bracket 10, the transverse rough adjusting guide rail 15 and the like relative to the blade 1 are adjusted to simulate the action direction of the simulated aerodynamic load in actual operation, so that the aerodynamic acting force of the blade 1 in the actual process is accurately simulated. When the simulated pneumatic load is applied, the load conditions of different positions can be reflected more accurately by adopting a multipoint contact mode. The load may be applied to the pressure surface of the blade 1 alone or in both directions on the pressure and suction surfaces of the blade 1. The positions of the contact points (characteristic positions 17) of each face of the blade 1 are not less than 3 during the load application. The range of application of the force by the mechanical probe 3 may cover all features of the blade 1 during actual application of the load.
Referring to FIG. 6, a schematic view of a blade 1 configuration is shown, the blade comprising a pressure side 1-1, a suction side 1-2, a blade tip 1-3, a dovetail 1-4, a blade leading edge 1-5, and a blade trailing edge 1-6. The positions of the main applied loads are a pressure surface 1-1 and a suction surface 1-2 of the blade 1, and the tenons 1-4 of the blade 1 are mainly used for realizing accurate positioning of the spatial positions of the blade 1.
Referring to fig. 7 and 8, the blade mount 10 is adapted to be structurally mated with the dovetail 1-4 of the blade 1 and secured in a test system. The transverse precise guide rail 12 and the longitudinal precise guide rail 11 are combined and used for precisely and slightly adjusting the space coordinate position of the blade 1 in the 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 tuning guide 14 is used to substantially adjust the spatial coordinate position of the blade 1 in the plane. Therefore, the testing system mainly realizes the preliminary positioning of the blade 1 through the rough adjustment of the transverse rough adjustment guide rail 15 and the longitudinal rough adjustment guide rail 14, realizes the accurate positioning of the blade 1 through the transverse precise guide rail 12 and the longitudinal precise guide rail 11, and realizes the positioning of the spatial included angle of the blade 1 relative to the mechanical probe 3 through the angle adjusting disk 13.
In a second aspect, an embodiment of the present application further provides a method for testing fatigue of an engine blade under simulated load, using the apparatus for testing fatigue of an engine blade under simulated load according to any embodiment of the first aspect, referring to fig. 9, the method includes:
And step 1, obtaining the pneumatic deformation condition of the blade under the steady-state outflow field by adopting a CCD camera 16 vision measurement method, and analyzing and calibrating boundary parameters and mathematical models required by the simulation calculation of the steady-state pneumatic flow field of the blade.
And 2, splitting the operation process of the unsteady pneumatic flow field of the blade into a plurality of typical transient states.
And 3, adopting the obtained boundary parameters and mathematical model to numerically simulate the pneumatic external flow field of the blade in the transient state.
And 4, installing the blade 1 to the installation standard 9, and calibrating the spatial position of the blade 1.
And 5, discretizing the space grid of the blade structure, and determining the characteristic position 17.
And 6, calculating and obtaining the load applied to the surface of the blade 1 based on the characteristic position 17 and the flow field simulation data, and applying the load to the actual blade 1 by acting the actuating shaft 4 on the mechanical probe 2.
The method specifically comprises the following steps:
Step 61, completing the unified calibration of the blade flow field simulation geometric model coordinate and the test device space coordinate;
step 62, based on the characteristic position 17 and the blade outflow field simulation data, completing the simulation load local area integral based on the characteristic position, and obtaining the load along-plane normal component;
Step 63, extracting a load of the characteristic position 17 along the normal component of the surface, and transmitting the load to the actuating shaft 4;
And 64, the characteristic positions 17 are in one-to-one correspondence with the measuring point positions where the mechanical probe 2 is arranged, and the mechanical probe 2 applies a normal component to the actual blade 1 based on the characteristic positions 17 and normal load simulation data.
And 7, obtaining deformation of different characteristic positions 17 of the blade 1 through the CCD camera 16, comparing the deformation with deformation simulation values of different characteristic positions 17 of the blade 1, recording the load size and direction arrangement under the transient state if the deviation values meet the test requirements, and otherwise, adjusting the selection of the characteristic positions 17.
And 8, repeating the process, and carrying out the next transient outflow field pneumatic simulation load data determination to form a load data record.
And 9, forming a load spectrum by using the recorded position and load data, applying the load spectrum to the blade 1, and simulating the fatigue performance of the blade under unsteady state and cyclic load.
And 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 performs a discretization operation in simulation software, forming respective feature positions 17 of a space, and the spatial position of each feature position 17 can be precisely located. Thus, the determining factors of the feature position 17 include:
The space grid discretization mode of the blade structure, and the arrangement of the discrete points can meet the requirement of the mechanical probe 3 that the space can be realized;
the spatial resolution of the mechanical probe 2 and the mechanical probe 3 depends on the distribution quantity and arrangement mode of the mechanical probe 2 and the mechanical probe 3 on the supporting frame 5;
The selection of the research positions of the blade structure is that the positions of different blades 1 for fatigue load investigation are inconsistent, and different numbers of characteristic positions 17 are required 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 leading edge 1-5 and a blade trailing edge 1-6 according to actual conditions.
Referring to fig. 11, the blade 1 completes the mechanical simulation in simulation software. The blade 1 is mainly subjected to pneumatic loads at the pressure surface 1-1 and the suction surface 1-2 in actual working conditions, but the pneumatic loads are different values at different positions of the blade 1, and different force loading at each point position is difficult to realize in actual test. Therefore, in the present embodiment, the fatigue strength of the blade 1 under the aerodynamic load is tested by simulating the aerodynamic load of the blade 1, which is constantly changing, with high accuracy mainly by realizing the force multipoint loading at a specific point (characteristic position 17) of the blade 1.
Referring to fig. 12, a schematic diagram of a mechanical probe 2 applying a load to a blade 1 is shown, before a 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 non-contact modern optical measurement experimental technique of DIC (DIGITAL IMAGE coreaction) is adopted by a CCD camera 16 to obtain a deformation condition of the blade 1 under the condition, and the deformation condition is compared with a numerical simulation result of the pneumatic flow field of the blade 1, and a mathematical model and a parameter setting of the numerical simulation of the pneumatic flow field are continuously adjusted, so that a deviation between the numerical simulation result of the pneumatic flow field and an experimental value obtained by the CCD camera 16 by adopting the DIC method is kept within an allowable error range, and the numerical simulation result of the pneumatic flow field can reflect a real deformation condition of the blade 1.
The pneumatic flow field of the blade 1 in operation is obtained in a simulation mode, and the unsteady operation process is split into a plurality of typical transient states, wherein the number N of the split transient states is more than or equal to 2. The key assessment test part of the blade 1 is determined by combining specific characteristics of a pressure surface 1-1, a suction surface 1-2, a blade tip 1-3 and the like of the structure of the blade 1; the spatial resolution and arrangement of the mechanical probe 2 and the mechanical probe 3 of the test device are combined to determine the density of the positions which can be realized by the mechanical probe 2 of the measuring point and which can be researched and arranged by the blade 1; the discretization mode of the structural space grid of the blade 1 is determined, so that the arranged characteristic positions 17 (the positions which can be realized by the mechanical probe 2) are in one-to-one correspondence with the surface characteristic positions 17 after discretization of the structural space grid of the blade 1. So that the force probe 3 can achieve the application of force at a specific position 17 of the blade 1 by the mechanical probe 2 and the position and the size of the application are consistent with the simulation of the blade 1.
Before an actual test, the coordinate of the blade 1 and the spatial coordinate of the test device are required to be calibrated in a unified manner, the spatial position and the posture of the blade 1 in the test system are realized by adjusting the transverse precise guide rail 12, the longitudinal precise guide rail 11, the transverse rough guide rail 15, the longitudinal rough guide rail 14 and the angle adjusting disk 13, and the spatial position and the posture of the blade 1 in the test system can be adjusted by designing the specific structure of the blade bracket 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 the area integration is performed to obtain a load value taking the point as the center area. Because the arc of the mechanical probe 2 is in tangential relation with the arc of the surface of the blade 1, the acting force is mainly transmitted along the normal direction of the contact point, mainly along the normal component F of the surface, and the normal component F is extracted in simulation software and transmitted to the actuating shaft 4 to act as force output to apply acting force to the actual blade 1. In practice, 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 the interference quantity additionally introduced by the measurement mode. The mechanical probe 2 and the blade 1 have smooth surfaces, and the component of the input load of the mechanical probe 2 in the direction is smaller, so that the magnitude of the friction load f is smaller and can be ignored. The deformation conditions of different characteristic positions 17 of the blade 1 are obtained through the CCD camera 16, and compared with deformation simulation values of different characteristic positions 17 of the blade 1, if the deviation values meet test requirements, the load size and direction arrangement under the transient state (transient state 1) can be recorded for later fatigue tests. If the deviation value does not meet the requirement, the selection of the characteristic position 17 is adjusted, and finally the position condition meeting the deviation requirement is obtained. In the actual selection process, the selection number of the characteristic positions 17 is more than or equal to 3.
After the load record of the blade 1 external flow field pneumatic simulation (transient 1) is completed, repeating the above processes, and carrying out load data determination of the blade 1 external flow field pneumatic simulation (transient 2), so that a set of load data record is finally formed, and the number of transient states is more than or equal to 2. The recorded position and load data are applied to the blade 1 to form a load spectrum, the load fatigue performance of the blade 1 under unsteady state and cyclic load is simulated, the deformation condition of the blade 1 is observed and recorded through the CCD camera 16, and the fatigue resistance performance of the blade 1 is evaluated.
The engine blade simulation load fatigue test device can accurately adjust the relative positions of the blade, the mechanical probe and the mechanical probe to realize the accurate positioning of the structure, the actuating shaft acts on the pressure surface and the suction surface of the blade through the mechanical probe integrated on the mechanical probe to apply acting force, aerodynamic force born by the blade in actual load is equivalent to specific extrusion load applied by the mechanical probe, the actual deformation condition of the blade in the specific load is checked, and the comparison and calibration are carried out with the numerical simulation calculation result, so that a set of mature calculation and simulation method is finally formed, and technical conditions are finally provided for checking the deformation condition of the blade under different operation working conditions.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the application is subject to the protection scope of the claims.
Claims (9)
1. The engine blade simulated load fatigue test device is characterized by comprising a horizontally arranged installation datum, wherein a movable and adjustable blade bracket is arranged in the middle area of the installation datum, and a blade is arranged on the upper side of the blade bracket; the installation standard is also provided with a movable supporting frame, the supporting frame is positioned at two sides of the blade support, a multipoint mechanical measurement assembly is arranged in the supporting frame, one end of the multipoint mechanical measurement assembly, which is close to the blade support, is in contact with the surface of the blade to apply acting force, one end of the multipoint mechanical measurement assembly, which is far away from the blade support, is connected with an air supply system, and the air supply system is used for providing acting force for the multipoint mechanical measurement assembly; the multipoint mechanical measurement assembly comprises a mechanical probe, a mechanical probe and an actuating shaft which are sequentially connected, one end of the actuating shaft, which is far away from the mechanical probe, is connected with the air supply system, and the mechanical probe, the mechanical probe and the actuating shaft are respectively arranged into a plurality of parts 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;
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 according to claim 1, wherein a longitudinal precise guide rail, a transverse precise guide rail, an angle adjusting disc and a longitudinal rough adjustment guide rail are sequentially arranged between the blade support and the installation reference, the longitudinal rough adjustment guide rail is connected with the installation reference, and the longitudinal precise 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 provided between the support frame and the mounting datum, the support frame being movable along the lateral coarse adjustment guide rail.
4. The engine blade simulated load fatigue test device of claim 1, 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 away from the actuating shaft, and the acting force of the actuating shaft is regulated by regulating the pressure regulating valve.
5. A method for testing simulated load fatigue of an engine blade, characterized in that the apparatus for testing simulated load fatigue of an engine blade according to any one of claims 1-4 is used, the method comprising:
The CCD camera vision measurement method is adopted to obtain the pneumatic deformation condition of the blade under the steady-state outflow field, and the pneumatic deformation condition is used for analyzing and calibrating boundary parameters and mathematical models required by the simulation calculation of the steady-state pneumatic flow field of the blade;
Splitting the operation process of the unsteady pneumatic flow field of the blade into a plurality of typical transient states;
adopting the obtained boundary parameters and mathematical model to numerically simulate the pneumatic external flow field of the blade in the transient state;
mounting the blade to a mounting reference, and calibrating the spatial position of the blade;
discretizing a space grid of the blade structure, and determining a characteristic position;
based on the characteristic position and the flow field simulation data, calculating to obtain the load applied to the surface of the blade, and applying the load to the actual blade by acting on the mechanical probe through the actuating shaft;
obtaining deformation of different characteristic positions of the blade through a CCD camera, comparing the deformation with simulation values of the deformation of the different characteristic positions of the blade, recording the load size and direction arrangement under the transient state if the deviation value meets the test requirement, otherwise, adjusting the selection of the characteristic positions;
Repeating the above processes, and carrying out the pneumatic simulation load data determination of the outflow field of the next transient state to form a load data record;
Forming a load spectrum by the recorded position and load data, applying the load spectrum to the blade, and simulating the fatigue performance of the blade under unsteady state and cyclic load;
And observing and recording the deformation condition of the blade through a CCD camera, and evaluating the fatigue resistance.
6. The method for simulating load fatigue test of engine blade according to claim 5, wherein the step of calculating the load applied to the surface of the blade based on the feature position and the flow field simulation data, acting on the mechanical probe through the actuation shaft and applying the load to the actual blade comprises:
calibrating the blade flow field simulation geometric model coordinate with the space coordinate of the test device;
based on the characteristic position and the simulation data of the external flow field of the blade, completing the local area integral of the simulation load based on the characteristic position, and obtaining the normal component of the load along the surface;
extracting a load along-plane normal component of the characteristic position and transmitting the load along-plane normal component to an actuating shaft;
The characteristic positions are in one-to-one correspondence with the measuring point positions where the mechanical probes are arranged, and the mechanical probes apply normal components to the actual blades based on the characteristic positions and normal load simulation data.
7. The engine blade simulated load fatigue test method of claim 5, wherein in the step of determining a characteristic position in the discretization of the blade structure space grid, the determining factor of the characteristic position comprises:
A blade structure space grid discretization mode;
The spatial resolution of the mechanical probe and the mechanical probe depends on the distribution quantity and arrangement mode of the mechanical probe and the mechanical probe on the supporting frame;
and selecting a leaf structure research position.
8. The method for simulating load fatigue test of an engine blade according to claim 5, wherein in the step of applying load to the blade by the mechanical probe, the load is applied to the pressure surface of the blade alone or to both the pressure surface and the suction surface of the blade.
9. The method for testing the simulated load fatigue of the engine blade according to claim 5, wherein the number of the selected characteristic positions is more than or equal to 3, and the number of typical transient states of the unstable aerodynamic flow field of the blade during the operation is more than or equal to 2.
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| CN112179794A (en) * | 2020-09-27 | 2021-01-05 | 中国科学院工程热物理研究所 | Fatigue strength testing device for tenon root of composite material blade |
| CN214668311U (en) * | 2021-04-25 | 2021-11-09 | 苏州泰斯特测控科技有限公司 | Aeroengine blade high-low cycle composite fatigue life testing device |
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| GB0906342D0 (en) * | 2009-04-15 | 2009-05-20 | Rolls Royce Plc | Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture |
| CN215865760U (en) * | 2021-05-24 | 2022-02-18 | 中国飞机强度研究所 | Blade fatigue test device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112179794A (en) * | 2020-09-27 | 2021-01-05 | 中国科学院工程热物理研究所 | Fatigue strength testing device for tenon root of composite material blade |
| CN214668311U (en) * | 2021-04-25 | 2021-11-09 | 苏州泰斯特测控科技有限公司 | Aeroengine blade high-low cycle composite fatigue life testing device |
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