CN112577686A - High-temperature vibration characteristic test system for composite material aircraft engine flame tube - Google Patents
High-temperature vibration characteristic test system for composite material aircraft engine flame tube Download PDFInfo
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Abstract
The invention discloses a high-temperature vibration characteristic test system of a composite material aeroengine flame tube, which comprises a first electromagnetic type vibration table; a composite material engine flame tube is fixedly arranged above the first electromagnetic type vibration table; a quartz lamp radiation heater bracket is fixedly arranged right above the flame tube; a hollow cylindrical reflecting plate is arranged on the bottom surface of the quartz lamp radiation heater bracket; a plurality of quartz lamps are arranged on the peripheral side wall inside the cylindrical reflecting plate; the flame tube is positioned in the inner cavity of the cylindrical reflecting plate; the surface of the flame tube is bonded with a high-temperature strain gauge and a measuring temperature sensor; the high-temperature strain gauge is connected with a data recorder; the measuring temperature sensor is connected with the data recorder; a laser vibration meter is fixedly arranged right above the flame tube; the laser vibration meter is connected with the data recorder. The method can simulate the high-temperature working environment of the flame tube, and obtain the vibration response acceleration data and the vibration strain data of the flame tube under a certain order of resonance frequency in the high-temperature environment.
Description
Technical Field
The invention relates to the technical field of mechanical environment tests of composite material aeroengine flame tubes, in particular to a high-temperature vibration characteristic test system of a composite material aeroengine flame tube.
Background
The aero-engine flame tube is a key part of an aero-engine, is a part for combustion of fuel gas of the aero-engine and is in a high-temperature environment in the running process of the aero-engine. In order to improve the thrust-weight ratio and the thermal efficiency of the engine, reduce the weight and reduce the noise level, the composite material is adopted to replace an alloy material, and the development direction of the flame tube of the aero-engine is provided.
At present, as the composite material is still in the development stage for the design of the flame tube, relatively less data can be referred to. In order to verify whether the structural design of the composite material aero-engine flame tube meets the requirements of the use working condition or not so as to support the improvement and optimization of the design, the vibration characteristics (including vibration response acceleration and vibration stress) of the flame tube under a certain order (such as first order, second order or third order) of resonance frequency need to be acquired under a high-temperature environment.
However, there is no technology that can obtain vibration characteristics (including vibration response acceleration and vibration stress) of a certain order (for example, first order, second order or third order) of resonance frequency of the flame tube in a high-temperature environment.
Disclosure of Invention
The invention aims to provide a high-temperature vibration characteristic test system of a composite material aeroengine flame tube, aiming at the technical defects in the prior art.
Therefore, the invention provides a high-temperature vibration characteristic test system of a composite material aeroengine flame tube, which comprises a first electromagnetic type vibration table;
the movable coil at the top of the first electromagnetic type vibration table is fixedly provided with a water cooling plate through a bolt;
the top of the water cooling plate is fixedly provided with a heat insulation plate through a bolt;
a high-temperature adapter plate is fixedly arranged at the top of the heat insulation plate through bolts;
the composite material engine flame tube is fixedly arranged at the top of the high-temperature adapter plate through bolts;
the first electromagnetic vibration table is used as a vibration exciting device and is used for providing exciting force for a vibration characteristic test of the composite material engine flame tube;
wherein, an annular quartz lamp radiation heater bracket is fixedly arranged right above the composite material engine flame tube;
a hollow cylindrical reflecting plate is arranged on the bottom surface of the quartz lamp radiation heater bracket;
a plurality of quartz lamps are arranged on the peripheral side wall inside the cylindrical reflecting plate;
the composite material engine flame tube is positioned in the inner cavity of the cylindrical reflecting plate;
wherein, the surface of the composite material engine flame tube is bonded with a high-temperature strain gauge and a measuring temperature sensor;
the high-temperature strain gauge is connected with the data recorder and is used for collecting the vibration stress of the composite material engine flame tube and then sending the vibration stress to the data recorder;
the measuring temperature sensor is connected with the data recorder and is used for collecting the temperature of the surface of the composite material engine flame tube at a preset temperature measuring point and then sending the temperature to the data recorder;
wherein, a laser vibration meter is fixedly arranged right above the composite material engine flame tube;
the laser vibration meter is positioned right above the central through hole of the quartz lamp radiation heater bracket;
the laser vibration meter is connected with the data recorder and is used for collecting the vibration response acceleration of the specified part on the composite material engine flame tube and then sending the vibration response acceleration to the data recorder;
and the data recorder is used for receiving and recording the vibration response acceleration of the designated part on the composite material engine flame tube sent by the laser vibration meter, the vibration stress of the composite material engine flame tube sent by the high-temperature strain gauge and the temperature of the preset temperature measuring point on the surface of the composite material engine flame tube sent by the temperature sensor.
Preferably, the device further comprises water cooling equipment;
the water cooling equipment is connected with the water cooling plate, the first electromagnetic type vibration table and the cylindrical reflecting plate through water pipe pipelines and used for cooling the water cooling plate, the first electromagnetic type vibration table and the cylindrical reflecting plate.
Preferably, a control temperature sensor is further included;
the control temperature sensor is a K-shaped armored high-temperature thermocouple sensor and is adhered to a temperature measuring point specified on the surface of a composite material cylinder body of the composite material engine flame tube through special high-temperature glue;
the control temperature sensor is connected with the quartz lamp radiation heater control system through a cable to form a temperature closed-loop control system.
Preferably, a vibration control system is also included;
the vibration control system is a closed-loop control system and comprises a first vibration controller, a first power amplifier and a high-temperature acceleration sensor;
the high-temperature acceleration sensor is arranged at the top of the high-temperature adapter plate;
the first vibration controller is used for outputting a vibration signal to the first power amplifier according to specified excitation test conditions;
the first power amplifier is connected with the first vibration controller and used for amplifying the vibration signal transmitted by the first vibration controller and then outputting the amplified vibration signal to the first electromagnetic vibration table to drive the first electromagnetic vibration table to vibrate;
the high-temperature acceleration sensor is used for measuring an acceleration signal output by the first electromagnetic type vibration table and feeding back the acceleration signal to the first vibration controller;
and the first vibration controller is respectively connected with the first power amplifier and the high-temperature acceleration sensor and used for correcting the vibration signal finally output by the first vibration controller according to the acceleration signal fed back by the high-temperature acceleration sensor and by comparing the acceleration signal fed back by the high-temperature acceleration sensor with the vibration signal of a test spectrum set in the first vibration controller until the vibration signal generated by the first electromagnetic vibration table meets the tolerance requirement of a vibration excitation test condition, wherein the vibration signal output by the first vibration controller is the vibration signal generated by the first electromagnetic vibration table.
Compared with the prior art, the high-temperature vibration characteristic test system for the composite material aero-engine flame tube can simulate the high-temperature working environment of the flame tube, acquire vibration response acceleration data and vibration strain data of the flame tube under a certain order (such as first order, second order or third order) resonance frequency in the high-temperature environment, be used for exploring the vibration characteristic of the composite material aero-engine flame tube in the high-temperature environment, and provide support for technical research and development and structural optimization of the composite material flame tube.
Drawings
FIG. 1 is a schematic overall structure diagram of a high-temperature vibration characteristic test system for a composite material aircraft engine flame tube provided by the invention;
FIG. 2 is a schematic structural diagram of a test system for normal-temperature modal analysis test in the present invention;
FIG. 3 is a schematic structural diagram of a test system for a normal temperature sinusoidal vibration test in the present invention;
in the figure, 1 is a first electromagnetic type vibration table, 2 is water cooling equipment, 3 is a water cooling plate, 4 is a heat insulation plate, and 5 is a high temperature adapter plate;
6 is a high-temperature strain gauge, 7 is a data recorder, 8 is a measurement temperature sensor, 9 is a control temperature sensor, and 10 is a composite material engine flame tube;
the device comprises a laser vibration meter 11, a quartz lamp radiation heater fixing support 12, a quartz lamp 13, a cylindrical reflecting plate 14 and a quartz lamp radiation heater control system 15, wherein the quartz lamp radiation heater fixing support is arranged on the quartz lamp radiation heater fixing support;
16 is a high-temperature acceleration sensor, 17 is a first vibration controller, and 18 is a first power amplifier;
21 is a second electromagnetic type vibration table, 22 is a water cooling cabinet, 23 is a switching tool, 24 is a normal temperature strain gauge and 25-data acquisition instrument;
a normal temperature measurement acceleration sensor 27, a normal temperature control acceleration sensor 28, a second vibration controller 29, and a second power amplifier 30.
Detailed Description
In order to make the technical means for realizing the invention easier to understand, the following detailed description of the present application is made in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application.
In addition, it should be noted that, in the description of the present application, unless otherwise explicitly specified and limited, the term "mounted" and the like should be interpreted broadly, and may be, for example, either fixedly mounted or detachably mounted.
The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
Referring to fig. 1, the invention provides a high-temperature vibration characteristic test system of a composite material aeroengine flame tube, which is a test system for performing a high-temperature sinusoidal vibration test and specifically comprises a first electromagnetic vibration table 1;
wherein, the moving coil at the top of the first electromagnetic type vibration table 1 is fixedly provided with a water cooling plate 3 through a bolt;
a heat insulation plate 4 is fixedly arranged at the top of the water cooling plate 3 through bolts;
a high-temperature adapter plate 5 is fixedly arranged at the top of the heat insulation plate 4 through bolts;
the top of the high-temperature adapter plate 5 is fixedly provided with a composite material engine flame tube 10 through bolts;
the first electromagnetic type vibration table 1 is used as a vibration exciting device and is used for providing exciting force for a vibration characteristic test of the composite material engine flame tube 10;
it should be noted that the water cooling plate 3, the heat insulation plate 4 and the high temperature adapter plate 5 together form an adapter fixing tool for transmitting the exciting force of the first electromagnetic vibration table 1 to the composite material engine flame tube 10.
Wherein, a ring-shaped quartz lamp radiation heater bracket 12 is fixedly arranged right above the composite material engine flame tube 10;
a hollow cylindrical reflecting plate 14 is arranged on the bottom surface of the quartz lamp radiation heater bracket 12;
a plurality of quartz lamps 13 are arranged on the inner peripheral side wall of the cylindrical reflecting plate 14;
the composite material engine flame tube 10 is positioned in the inner cavity of the cylindrical reflecting plate 14;
it should be noted that the quartz lamp 13 and the annular reflecting plate 14 together form a quartz lamp radiation heater, which is fixed on the quartz lamp radiation heater support 12, and the composite material engine flame tube 10 is integrally covered in the quartz lamp radiation heater.
It should be noted that, in the present invention, the high temperature loading and control system is provided around the flame tube 10, and is used for providing a high temperature environment meeting the test requirements for the composite material engine flame tube 10; the high temperature loading and control system comprises a quartz lamp 13, a cylindrical reflecting plate 14, a quartz lamp radiant heater control system 15, a quartz lamp radiant heater fixing support 12 and a control temperature sensor 9. The quartz lamp 13 is fixed on the hollow cylindrical reflecting plate 14 through the conductive copper bar, the cylindrical reflecting plate 14 is fixed on the quartz lamp radiation heater fixing support 12, the quartz lamp 13 is connected with the quartz lamp radiation heater control system 15 through the conductive copper bar and the cable, and the output power of the quartz lamp 13 can be controlled by adjusting the parameters of the quartz lamp radiation heater control system 15, so that the adjustment of different temperatures is realized.
Wherein, the surface of the composite material engine flame tube 10 is bonded with a high temperature strain gauge 6 and a measuring temperature sensor 8;
the high-temperature strain gauge 6 is connected with the data recorder 7 and is used for acquiring the vibration stress (namely vibration strain data) of the composite material engine flame tube 10 and then sending the vibration stress to the data recorder 7;
the measuring temperature sensor 8 is connected with the data recorder 7 and used for collecting the temperature of the surface of the composite material engine flame tube 1 at a preset temperature measuring point and then sending the temperature to the data recorder 7;
it should be noted that the high-temperature strain gauge 6 can be adhered to a strain measurement point specified on the surface of the composite material cylinder of the composite material engine flame tube 10 by a special high-temperature adhesive and a special bonding process, and the high-temperature strain gauge 6 is connected with the data recorder 7 through a test cable and is used for collecting vibration strain data of the composite material engine flame tube 10;
wherein, a laser vibration meter 11 is fixedly arranged right above the composite material engine flame tube 10;
a laser vibration meter 11 positioned right above the central through hole of the quartz lamp radiant heater support 12;
the laser vibration meter 11 is connected with the data recorder 7 and used for collecting vibration response acceleration of a specified part on the composite material engine flame tube 10 and then sending the vibration response acceleration to the data recorder 7;
and the data recorder 7 is used for receiving and recording the vibration response acceleration of the designated position on the composite material engine flame tube 10 sent by the laser vibration meter 11, the vibration stress of the composite material engine flame tube 10 sent by the high-temperature strain gauge 6 and the temperature of the preset temperature measuring point on the surface of the composite material engine flame tube 1 sent by the measuring temperature sensor 8.
It should be noted that, for the present invention, the laser vibration meter 11 is used to measure the vibration response acceleration data of the composite material engine flame tube 10, the high temperature strain gauge 6 is used to measure the vibration strain data of the composite material engine flame tube 10, the measurement temperature sensor 8 is used to measure the temperature response data at different positions of the composite material engine flame tube 10, and the vibration characteristics and the temperature distribution of the composite material engine flame tube 10 can be obtained by analyzing the measured data.
It should be noted that, for the present invention, the data recorder 7, the laser vibration meter 11, the high temperature strain gauge 6 and the measurement temperature sensor 8 together constitute a measurement system.
In the invention, the water-cooling plate 3 is connected with the heat-insulating plate 4 and the high-temperature adapter plate 5 through bolts, and the composite material engine flame tube 10 is fixed on the high-temperature adapter plate 5.
In particular, the water cooling plate 3 is connected with the water cooling device 2, and the water cooling plate 3 is used for preventing high temperature from being transmitted to a moving coil of the first electromagnetic vibration table 1 and protecting the first electromagnetic vibration table 1;
in particular, the heat insulation plate 4 is made of high-temperature-resistant mineral powder and has the advantages of high temperature resistance, low thermal conductivity and high compressive strength, and the heat insulation plate 4 is positioned between the high-temperature adapter plate 5 and the water cooling plate 3 and used for reducing heat conduction loss;
in particular, the high-temperature adapter plate 5 is made of a high-temperature alloy material, so that good rigidity can be kept at high temperature, and the excitation force can be favorably transmitted to the composite material engine flame tube 10;
in the invention, the device also comprises a water cooling device 2;
the water cooling device 2 is connected with the water cooling plate 3, the first electromagnetic type vibration table 1 and the cylindrical reflection plate 14 through water pipe pipelines, and is used for cooling the water cooling plate 3, the first electromagnetic type vibration table 1 and the cylindrical reflection plate 14, and the water cooling device plays a role in cooling through water circulation.
The water cooling equipment 2 may be a conventional circulation water chiller, for example, a circulation water chiller having a model number XT550W manufactured by LAUDA corporation of germany, and used for cooling the water-cooled plate 3.
In the invention, the measurement temperature sensor 8 is a K-shaped armored high-temperature thermocouple sensor, is adhered to a temperature measurement point specified on the surface of a composite material cylinder body of the composite material engine flame tube 10 through special high-temperature glue, is connected with the data recorder 7 through a test cable, and is used for collecting the temperature at the temperature measurement point on the surface of the composite material engine flame tube 1, acquiring the temperature distribution condition and the maximum temperature gradient of the surface of the composite material engine flame tube 1, and judging whether the temperature of the composite material engine flame tube 10 meets the test requirements.
In the invention, the laser vibration meter 11 is a non-contact doppler high-performance single-point laser vibration meter, is fixed at a position more than 1 m away from the top of the composite material engine flame tube 10 through a bracket, is connected with the data recorder 7 through a test cable, and is used for collecting the vibration response of the designated position on the composite material engine flame tube 10.
In the present invention, in particular, the present invention further includes a control temperature sensor 9;
the control temperature sensor 9 is a K-shaped armored high-temperature thermocouple sensor and is adhered to a temperature measuring point specified on the surface of a composite material cylinder body of the composite material engine flame tube 10 through special high-temperature glue, the control temperature sensor 9 is connected with the quartz lamp radiation heater control system 15 through a cable to form a temperature closed-loop control system, and the temperature closed-loop control system is used for controlling and adjusting the output power of the quartz lamp 13 so that the temperature of the composite material engine flame tube 10 can meet the specified test temperature requirement.
It should be noted that the quartz lamp radiant heater control system 15 is a control module of an existing quartz lamp radiant heater, and for example, a quartz lamp radiant heating controller manufactured by wuhan technologies, ltd, and having a model number of kzgzzl-P-DC 300-02C, may be used to control the quartz lamp 13 to heat the flame tube 10.
It should be noted that the quartz lamp 13 and the cylindrical reflector 14, which together form the quartz lamp radiant heater, are fixed on the quartz lamp radiant heater support 12, and the composite engine flame tube 10 is integrally covered in the quartz lamp radiant heater.
The first electromagnetic vibration table 1, the first vibration controller 17, the first power amplifier 18, and the high-temperature acceleration sensor 16 are connected to form a vibration closed-loop control system, and are used for implementing vibration test conditions specified in the test.
In the invention, a vibration control system is also included in the concrete implementation;
the vibration control system is a closed-loop control system and comprises a first vibration controller 17, a first power amplifier 18 and a high-temperature acceleration sensor 16;
wherein, the high-temperature acceleration sensor 16 is arranged on the top of the high-temperature adapter plate 5;
a first vibration controller 17 for outputting a vibration signal to a first power amplifier 18 according to a predetermined vibration excitation test condition;
the second power amplifier 18 is connected with the first vibration controller 17 and is used for amplifying the vibration signal transmitted by the first vibration controller 17 and then outputting the amplified vibration signal to the first electromagnetic vibration table 1 to drive the first electromagnetic vibration table 1 to vibrate;
the high-temperature acceleration sensor 16 is used for measuring an acceleration signal output by the first electromagnetic vibration table 1 and feeding back the acceleration signal to the first vibration controller 17;
the first vibration controller 17 is connected to the first power amplifier 18 and the high-temperature acceleration sensor 16, and configured to correct a vibration signal (i.e., a vibration signal of a corrected test spectrum) finally output by the first vibration controller 17 by comparing an acceleration signal fed back by the high-temperature acceleration sensor 16 with a vibration signal of a test spectrum set in the first vibration controller 17 according to an acceleration signal fed back by the high-temperature acceleration sensor 16 until the vibration signal generated by the first electromagnetic vibration table 1 meets an allowance requirement of an excitation test condition, where the vibration signal output by the first vibration controller 17 is the vibration signal generated by the first electromagnetic vibration table 1.
It should be noted that, in the present invention, the correction means adjustment, the acceleration voltage signal fed back by the high-temperature acceleration sensor 16 is compared with the test spectrum set by the first vibration controller 17, when the feedback signal is smaller than the set test spectrum, the first vibration controller 17 increases the output signal, when the feedback signal is larger than the set test spectrum, the first vibration controller 17 decreases the output signal, and the above processes are repeated continuously, so that the feedback signal is finally kept consistent with the set test spectrum.
It should be noted that the tolerance of the test condition is generally specified to be within ± 3dB of the set test spectrum, so as to meet the requirement of the test standard.
In a specific implementation of the present invention, the first electromagnetic vibration table 1 may be any electromagnetic vibration table, for example, a vibration table manufactured by beijing space schel test technologies ltd and having a model number MPA409/M437A/GT800M, and the vibration table has a direct-coupled electric vibration test system.
In the present invention, in a specific implementation, the data acquisition instrument 7 may be any data acquisition instrument having the above functions, for example, a data acquisition analyzer manufactured by setaste electronics manufacturers ltd of Jiangsu, model number TST5912, which has a dynamic signal testing and analyzing system
In the present invention, in a specific implementation, the first vibration controller 17 may be a vibration controller manufactured by yogzhou hundred million constant technologies ltd and having a model number of eco VT-9016.
In a specific implementation of the present invention, the first power amplifier 18 may be a power amplifier with a model number of MPA409, which is manufactured by beijing space schill test technology ltd, and is an intelligent switching power amplifier.
In the present invention, in a specific implementation, the high temperature acceleration sensor 16 may be any high temperature acceleration sensor, for example, a 8202A type high temperature acceleration sensor manufactured by qishi instrument gmbh of cz switzerland, that is, a ceramic shear high temperature charge output type accelerometer.
In the present invention, the laser vibrometer 11 may be a high-performance single-point laser vibrometer manufactured by Polytec of germany, which is a Polytec high-performance single-point laser vibrometer based on the laser doppler principle, and has a model number of OFV-505/5000.
In the present invention, in a specific implementation, the high temperature strain gauge 6 may be a model ZWP-NC-063-120 high temperature strain gauge manufactured by Vishay, usa, which is a high temperature wire strain gauge.
In order to more clearly understand the present invention, the following describes a specific process of the present invention for performing a high-temperature sinusoidal vibration test, which specifically includes the following steps:
1. fixing a water-cooling plate 3 on a moving coil of the first electromagnetic type vibration table 1 through a bolt;
2. fixing the heat insulation plate 4 and the high-temperature adapter plate 5 on the water cooling plate 3 through high-temperature bolts;
3. a high-temperature acceleration sensor 16 is fixed on the high-temperature adapter plate 5, a cable is connected with a first vibration controller 17 and then connected with a first electromagnetic vibration table 1 and a first power amplifier 18 to form a vibration closed-loop control system, and the system is debugged to be in a normal state;
4. the high-temperature strain gauge 6 and the measurement temperature sensor 8 are pasted at a specified test position, connected with the data recorder 7 through a cable, the data recorder 7 is started, and the data of the high-temperature strain gauge 6 and the measurement temperature sensor 8 are debugged to be normal;
5. fixing the composite material engine flame tube 10 on the high-temperature adapter plate 5;
6. assembling a quartz lamp 13, a cylindrical reflecting plate 14 and a quartz lamp radiation heater bracket 12, integrally covering a flame tube 10 in the quartz lamp radiation heater, sticking a control temperature sensor 9 on the composite material engine flame tube 10, connecting a quartz lamp radiation heater control system 15 to form a temperature loading closed-loop control system, and debugging the system to a normal state;
7. installing and fixing a laser vibration meter 11, connecting the laser vibration meter 11 and the data recorder 7 through cables, starting the laser vibration meter 11 and the data recorder 7, and carrying out focusing debugging until signals are normal;
8. setting specified vibration test conditions on a first vibration controller 17, setting data acquisition parameters on a data recorder 7, and debugging a control system and a measurement system to normal;
9. starting a quartz lamp radiant heater control system 15, setting a test temperature, heating the composite material engine flame tube 10, and preserving heat when the temperature of the control temperature sensor 9 reaches a specified control temperature until the temperature fluctuation of each measurement temperature sensor 8 on the composite material engine flame tube 10 is within +/-5 ℃;
10. starting a first vibration controller 17 and a first power amplifier 18, performing a sine frequency sweep vibration test, monitoring a vibration control curve, starting a data recorder 7 when vibration reaches a specified condition (the specific condition is a sine frequency sweep test condition, the frequency range is 10-2000 Hz, and the vibration acceleration magnitude is 1g) and the control is stable, collecting vibration response signals of a laser vibration meter 11 and a high-temperature strain gauge 6, and obtaining a vibration acceleration transfer function curve of a laser measuring point and vibration strain data measured by the high-temperature strain gauge (namely the high-temperature strain gauge);
11. and determining the exact numerical value of the modal frequency of a certain order in the high-temperature state according to the measured transfer function curve.
12. The sinusoidal constant frequency test is performed with the determined modal frequency as a test frequency of sinusoidal constant frequency vibration (i.e., a vibration test frequency in a high temperature state, and a specific confirmation procedure for determining the vibration test frequency in the high temperature state is described below). And acquiring the strain response of the high-temperature strain gauge of the composite material engine flame tube 10 under the specified magnitude and test frequency. And meanwhile, the vibration fatigue performance of the flame tube is examined.
In the present invention, the sinusoidal fixed frequency vibration test is performed on the liner, and during or after the test, if the liner and its parts are cracked or damaged, the vibration fatigue performance is not satisfactory, and if there is no abnormality, the vibration fatigue performance is satisfactory.
In the present invention, the predetermined excitation test conditions for the first vibration controller 17 include: the vibration test frequency in the high temperature state is a certain order (for example, first order, second order or third order) resonance frequency of the flame tube in the high temperature environment.
In particular, in order to determine the vibration test frequency in the high temperature state, the method specifically includes the following operation steps S1 to S3:
and step S1, carrying out finite element modal analysis and finite element frequency response analysis of the composite material aero-engine flame tube in a fixed state, and respectively obtaining a finite element modal analysis result and a finite element frequency response analysis result.
In particular, the finite element analysis can be performed by using mature finite element modeling analysis software, such as Patran, Ansys, and the like.
In particular, the basic flow of finite element modal analysis is as follows: establishing a geometric model of the composite material aero-engine flame tube, carrying out meshing on the geometric model to establish a finite element analysis model, setting boundary constraint of the model, setting material data of the model, submitting for finite element modal analysis, obtaining a finite element modal analysis result, and extracting the vibration mode and the maximum strain position of the flame tube under a certain order of concerned resonance frequency.
In particular, the basic flow of frequency response analysis is as follows: establishing a geometric model of a flame tube of the composite material aeroengine, carrying out meshing on the geometric model to establish a finite element analysis model, setting boundary constraint of the model, setting loading frequency parameters, setting material data of the model, submitting for frequency response analysis, acquiring a frequency response analysis result, and extracting a frequency response analysis result, a vibration mode and a maximum strain position of the flame tube under a certain order of concerned resonance frequency.
The obtained finite element modal analysis result and the finite element frequency response analysis result are used as theoretical references of modal tests and sinusoidal vibration tests.
Step S2, a modal analysis test of the composite material aero-engine flame tube in a fixed state is carried out at normal temperature through a test system of a normal-temperature modal test, and a vibration response maximum point position and a strain maximum position in a modal vibration mode corresponding to a first-order modal frequency of the composite material aero-engine flame tube 10 are obtained.
In particular, referring to fig. 2, the test system for normal temperature modal analysis test includes: the device comprises a modal force hammer, a charge amplifier, an acceleration sensor and a data acquisition analyzer;
the modal force hammer consists of a hammer body, a hammer head and a force sensor and is used for knocking the flame tube to generate an exciting force;
the charge discharger is used for converting a charge signal input by the force sensor into a voltage signal;
the acceleration sensor is adhered to the composite material engine flame tube 10 and used for measuring a vibration response signal;
the data acquisition analyzer is used for acquiring signals of the force sensor and the acceleration sensor, acquiring a frequency response function curve through a data processing function in software, identifying modal parameters, acquiring modal frequency, modal damping and modal vibration mode of the composite material engine flame tube 10 and recording the modal damping and modal vibration mode corresponding to each modal frequency;
in particular, the basic ideal flow of the normal-temperature modal analysis test is as follows:
and step S21, fixing the composite material engine flame tube 10 on the expansion table surface of the vibration table.
Step S22, determining the position of the measuring point of the composite material engine liner 10 with reference to the mode shape obtained by the finite element mode analysis of the previous step S1.
And step S23, adhering an acceleration sensor at the measuring point, connecting a cable and connecting the cable with a data acquisition analyzer.
Step S24, connecting the force sensor of the modal force hammer to the charge amplifier by a signal line, and then connecting the charge amplifier to the data acquisition analyzer.
And step S25, setting parameters of the modal test on the data acquisition instrument, and debugging a modal test system consisting of a modal force hammer, a charge amplifier, an acceleration sensor and a data acquisition analyzer to be normal.
And step S26, knocking the composite material engine flame tube 10 by using a modal force hammer to obtain modal test data.
Step S27, processing the test data by using a data acquisition analyzer to obtain a frequency response function, then performing modal parameter identification to obtain modal frequency, modal damping and modal shape, and recording the modal damping and modal shape corresponding to each modal frequency;
and step S28, comparing the modal frequency, modal damping and modal shape obtained in the modal test with the finite element modal analysis result obtained in the step S1, and determining the validity of the data such as the modal frequency, the modal damping and the modal shape.
It should be noted that when the modal shape obtained by the modal test is consistent with the modal shape of the finite element modal analysis result, and the modal frequency obtained by the modal test is consistent with the modal frequency order and sequence of the finite element modal analysis result, determining that the modal frequency, the modal damping and the modal shape data are valid.
And step S29, determining a first-order modal frequency as a subsequent test frequency in the obtained modal test result, and determining a vibration response maximum point position and a strain maximum position in the modal shape corresponding to the first-order modal frequency according to the modal shape corresponding to the first-order modal frequency.
And step S3, carrying out a sine vibration test of the composite material aeroengine flame tube in a fixed state at normal temperature through a test system of the normal temperature sine vibration test, and determining the vibration test frequency at high temperature.
In particular, referring to fig. 3, the test system for the normal temperature sinusoidal vibration test includes: the system comprises a second electromagnetic vibration table 21, a second power amplifier 30, a second vibration controller 29, a normal-temperature measurement acceleration sensor 27, a normal-temperature control acceleration sensor 28, a normal-temperature strain gauge 24 and a data acquisition instrument 25;
the second electromagnetic vibration table 21 is used for providing an exciting force for a sinusoidal vibration test of the composite material engine flame tube 10;
a second vibration controller 29 for controlling the second electromagnetic vibration table 21 to output a sinusoidal signal;
and the normal temperature measurement acceleration sensor 27 is used for measuring the acceleration response of a specified measurement point on the composite material engine flame tube 10.
In particular, a transfer tool 23 (an existing transfer tool, for example, an existing clamping tool) is arranged at the top of the second electromagnetic vibration table 21;
the composite material engine flame tube 10 is fixed on the switching tool 23;
a normal temperature strain gauge 24 is adhered to the surface of the composite material engine flame tube 10;
the normal temperature strain gauge 24 is connected with the data acquisition instrument 25 and is used for acquiring the vibration stress (namely vibration strain data) of the composite material engine flame tube 10 and then sending the vibration stress to the data acquisition instrument 25;
a normal temperature measurement acceleration sensor 7 is arranged at the top of the composite material engine flame tube 10;
the normal temperature measurement acceleration sensor 7 is connected with the data acquisition instrument 25 and used for acquiring the temperature of the surface of the composite material engine flame tube 1 and then sending the temperature to the data acquisition instrument 25;
in particular, a normal temperature control acceleration sensor 28 is arranged on the switching tool 23;
the normal temperature control acceleration sensor 28 is connected with the second vibration controller 29;
a second vibration control instrument 2 connected with the second power amplifier 30
In particular, the second electromagnetic vibration table 21 is further connected to an existing water-cooled cabinet.
In the concrete implementation, the flow of the normal-temperature sinusoidal vibration test performed by the test system of the normal-temperature sinusoidal vibration test is as follows:
step S31 is to fix the composite engine liner 10 on the extension table of the second electromagnetic vibration table 21.
Step S32, referring to the mode shape and the maximum strain point position obtained by the finite element mode analysis in the previous step S1, attaching a measurement acceleration sensor (i.e., the normal temperature measurement acceleration sensor 27) to the liner, specifically, attaching an acceleration sensor to the maximum mode shape point position of the composite material engine liner 10, and attaching normal temperature strain gauges (i.e., the normal temperature strain gauge 24) to the maximum strain point position and the vicinity thereof;
an acceleration sensor (i.e., a normal temperature control acceleration sensor 28) is attached to a joint between the composite material engine liner 10 and the tool as a vibration control sensor.
Step S33, connecting the strain gauge with a data acquisition analyzer, and debugging to normal;
step S34, connecting the second vibration controller with the second power amplifier and the normal temperature control acceleration sensor 28, and debugging to normal;
and step S35, setting sine frequency sweep test conditions on the second vibration controller, operating the vibration control test system, and carrying out sine frequency sweep test.
Step S36, obtaining a transfer function curve of each measuring point in the sine sweep test, comparing the transfer function curve with the finite element modal analysis result and the finite element frequency response analysis result obtained in the step S1, and determining the modal frequency and the test direction as the vibration test frequency in the high-temperature state according to the vibration response and the strain response amplitude (namely the vibration response maximum point position and the strain maximum position in the modal shape corresponding to the first-order modal frequency determined in the step S29); the modal frequency of the vibration test frequency in the high-temperature state is used as a certain order resonance frequency in the high-temperature environment;
it should be noted that, for the flame tube product, the sweep frequency direction is vertical and horizontal, transfer function curve data in two directions are respectively obtained through a sweep frequency test, the obtained transfer function curve and modal shape are compared with a modal simulation analysis result, the direction with larger vibration response and strain response amplitude under a certain order of modal frequency is taken as the test direction, and the modal frequency is taken as the test frequency.
And selecting the direction with the maximum vibration response and the maximum strain response as the test direction. By determining the test direction, the structural strength of the test product can be assessed under the most severe test conditions.
In step S37, a constant frequency sinusoidal vibration test is performed at the specified modal frequency and test direction, and the position at which the strain is maximum is specified as the position of the strain point (i.e., the position of the strain point to which the high temperature strain gauge 6 is bonded) in the high temperature vibration characteristic and vibration fatigue test.
Compared with the prior art, the invention has the following beneficial technical effects:
1. according to the invention, through finite element analysis, normal-temperature modal test and normal-temperature sinusoidal vibration test, the vibration test frequency in a high-temperature state can be accurately determined, and the difficulty that the test frequency cannot be determined by performing a complex modal test at a high temperature is solved.
2. The method can measure and obtain the strain data of the composite material flame tube in a high-temperature state, and can provide a real strain data support for the analysis of the vibration characteristic of the flame tube in a high-temperature environment.
3. The method can obtain the vibration characteristic of the composite flame tube at normal temperature, and can be verified with the finite element analysis result, and also can obtain the vibration characteristic of the composite flame tube at high temperature, thereby providing data basis for the vibration characteristic evaluation of the composite flame tube at high temperature.
Based on the technical scheme, the vibration response acceleration data and the vibration strain data of the flame tube under the resonance frequency which is a certain order of important attention in the high-temperature environment can be obtained, the vibration fatigue characteristic of the composite material flame tube under the resonance frequency can be obtained, and the support is provided for the technical research and development and the structural optimization of the composite material flame tube.
It should be noted that, for the high-temperature vibration characteristic test system of the composite material aero-engine flame tube provided by the invention, a method of combining finite element modal analysis, frequency response analysis, normal-temperature modal test and normal-temperature sinusoidal vibration test is utilized to measure and obtain the high-temperature vibration response and the vibration strain data of the composite material flame tube under the modal frequency of a certain order (such as a first order, a second order or a third order) which is mainly concerned, so as to obtain the vibration characteristic of the composite material flame tube under the high-temperature environment.
In summary, compared with the prior art, the high-temperature vibration characteristic test system for the composite material aero-engine flame tube provided by the invention can simulate the high-temperature working environment of the flame tube, acquire vibration response acceleration data and vibration strain data of the flame tube under a certain order of resonance frequency in the high-temperature environment, be used for exploring the vibration characteristic of the composite material aero-engine flame tube in the high-temperature environment, and provide support for technical research and development and structural optimization of the composite material flame tube.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (4)
1. A high-temperature vibration characteristic test system for a composite material aeroengine flame tube is characterized by comprising a first electromagnetic vibration table (1);
wherein a water cooling plate (3) is fixedly arranged on a moving coil at the top of the first electromagnetic type vibration table (1) through a bolt;
a heat insulation plate (4) is fixedly arranged at the top of the water cooling plate (3) through bolts;
a high-temperature adapter plate (5) is fixedly arranged at the top of the heat insulation plate (4) through bolts;
the top of the high-temperature adapter plate (5) is fixedly provided with a composite material engine flame tube (10) through bolts;
the first electromagnetic type vibration table (1) is used as a vibration excitation device and is used for providing an excitation force for a vibration characteristic test of a composite material engine flame tube (10);
wherein, an annular quartz lamp radiation heater bracket (12) is fixedly arranged right above the composite material engine flame tube (10);
a hollow cylindrical reflecting plate (14) is arranged on the bottom surface of the quartz lamp radiation heater bracket (12);
a plurality of quartz lamps (13) are arranged on the peripheral side wall in the cylindrical reflecting plate (14);
the composite material engine flame tube (10) is positioned in the inner cavity of the cylindrical reflecting plate (14);
wherein, the surface of the composite material engine flame tube (10) is adhered with a high-temperature strain gauge (6) and a measuring temperature sensor (8);
the high-temperature strain gauge (6) is connected with the data recorder (7) and is used for collecting the vibration stress of the composite material engine flame tube (10) and then sending the vibration stress to the data recorder (7);
the measuring temperature sensor (8) is connected with the data recorder (7) and is used for collecting the temperature of a preset temperature measuring point on the surface of the composite material engine flame tube (1) and then sending the temperature to the data recorder (7);
wherein, a laser vibration meter (11) is fixedly arranged right above the composite material engine flame tube (10);
the laser vibration meter (11) is positioned right above a central through hole of the quartz lamp radiation heater bracket (12);
the laser vibration meter (11) is connected with the data recorder (7) and is used for collecting the vibration response acceleration of the specified part on the composite material engine flame tube (10) and then sending the vibration response acceleration to the data recorder (7);
and the data recorder (7) is used for receiving and recording the vibration response acceleration of the designated position on the composite material engine flame tube (10) sent by the laser vibration meter (11), the vibration stress of the composite material engine flame tube (10) sent by the high-temperature strain gauge (6) and the temperature of the preset temperature measuring point of the surface of the composite material engine flame tube (1) sent by the temperature sensor (8).
2. The system for testing high-temperature vibration characteristics of a composite material aircraft engine flame tube according to claim 1, further comprising a water cooling device (2);
the water cooling equipment (2) is connected with the water cooling plate (3), the first electromagnetic type vibration table (1) and the cylindrical reflecting plate (14) through water pipe pipelines and used for cooling the water cooling plate (3), the first electromagnetic type vibration table (1) and the cylindrical reflecting plate (14).
3. The system for testing high temperature vibration characteristics of a composite aircraft engine flame tube of claim 1, further comprising a control temperature sensor (9);
the control temperature sensor (9) is a K-shaped armored high-temperature thermocouple sensor and is adhered to a temperature measuring point specified on the surface of a composite material cylinder body of the composite material engine flame tube (10) through special high-temperature glue;
the control temperature sensor (9) is connected with a quartz lamp radiation heater control system (15) through a cable to form a temperature closed-loop control system.
4. A composite aircraft engine liner high temperature vibration performance testing system according to any of claims 1 to 3, further comprising a vibration control system;
the vibration control system is a closed-loop control system and comprises a first vibration controller (17), a first power amplifier (18) and a high-temperature acceleration sensor (16);
wherein, the high-temperature acceleration sensor (16) is arranged at the top of the high-temperature adapter plate (5);
a first vibration controller (17) for outputting a vibration signal to a first power amplifier (18) according to a predetermined excitation test condition;
the first power amplifier (18) is connected with the first vibration controller (17) and used for amplifying the vibration signal transmitted by the first vibration controller (17) and then outputting the amplified vibration signal to the first electromagnetic vibration table (1) to drive the first electromagnetic vibration table (1) to vibrate;
the high-temperature acceleration sensor (16) is used for measuring an acceleration signal output by the first electromagnetic vibration table (1) and feeding back the acceleration signal to the first vibration controller (17);
the first vibration controller (17) is respectively connected with the first power amplifier (18) and the high-temperature acceleration sensor (16), and is used for correcting the vibration signal finally output by the first vibration controller (17) according to the acceleration signal fed back by the high-temperature acceleration sensor (16) and the vibration signal of the test spectrum set in the first vibration controller (17) by comparing the acceleration signal fed back by the high-temperature acceleration sensor (16) with the vibration signal of the test spectrum set in the first vibration controller (17) until the vibration signal generated by the first electromagnetic vibration table (1) meets the tolerance requirement of the excitation test condition, wherein the vibration signal output by the first vibration controller (17) is the vibration signal generated by the first electromagnetic vibration table (1).
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Effective date of registration: 20220921 Address after: No. 3998, Lianhua South Road, Minhang District, Shanghai, 200000 Applicant after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: No.9, Zhongbei 3rd Street, West District, Binhai New Area Development Zone, Tianjin 300462 Applicant before: TIANJIN AEROSPACE RELIA TECHNOLOGY Co.,Ltd. Applicant before: BEIJING INSTITUTE OF STRUCTURE AND ENVIRONMENT ENGINEERING |
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