CN213956713U - 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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- CN213956713U CN213956713U CN202023021899.5U CN202023021899U CN213956713U CN 213956713 U CN213956713 U CN 213956713U CN 202023021899 U CN202023021899 U CN 202023021899U CN 213956713 U CN213956713 U CN 213956713U
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Abstract
The utility model discloses a high-temperature vibration characteristic test system of a composite material aero-engine 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 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 utility model discloses can simulate the high temperature operational environment of flame tube, acquire the vibration response acceleration data and the vibration strain data of flame tube under certain order resonant frequency under the high temperature environment.
Description
Technical Field
The utility model relates to a mechanical environmental test technical field of combined material aeroengine flame tube especially relates to a high temperature vibration characteristic test system of combined 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.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a high temperature vibration characteristic test system of combined material aeroengine flame tube to the technical defect that prior art exists.
Therefore, the utility model provides a high temperature vibration characteristic test system of a composite material aeroengine flame tube, which comprises a first electromagnetic 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.
By the above the technical scheme the utility model provides a it is visible, compare with prior art, the utility model provides a high temperature vibration characteristic test system of combined material aeroengine flame section of thick bamboo, its high temperature operational environment that can simulate the flame section of thick bamboo acquires the vibration response acceleration data and the vibration strain data of flame section of thick bamboo under certain rank (for example first order, second order or third order) resonant frequency under the high temperature environment for explore combined material aeroengine flame section of thick bamboo vibration characteristic under the high temperature environment, provide the support for the technical development and the structural optimization of combined material flame section of thick bamboo.
Drawings
FIG. 1 is a schematic view of the overall structure of a high-temperature vibration characteristic test system for a composite material aircraft engine flame tube provided by the present invention;
fig. 2 is a schematic structural diagram of a test system for normal-temperature modal analysis tests according to the present invention;
FIG. 3 is a schematic structural diagram of a test system for a normal temperature sinusoidal vibration test according to 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 of the present invention easier to understand, the present application will be further described in detail with reference to the accompanying drawings and examples. 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 utility model provides a high temperature vibration characteristic test system of a composite material aeroengine flame tube, which is a test system for 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 measurement 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 10 at a preset temperature measurement 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, to the utility model discloses, laser vibrometer 11 is used for measuring the vibration response acceleration data of combined material engine flame tube 10, and high temperature foil gage 6 is used for measuring the vibration strain data of combined material engine flame tube 10, measures the temperature response data that temperature sensor 8 is used for measuring the different positions department of combined material engine flame tube 10, through the data of analysis and measurement, can obtain the vibration characteristic and the temperature distribution of combined material engine flame tube 10.
It should be noted that, to the utility model discloses, data record 7, laser vibrometer 11, high temperature foil gage 6 and measurement temperature sensor 8 are together constituteed measurement system.
The utility model discloses in, on specifically realizing, water-cooling plate 3 is connected with heat insulating board 4 and high temperature keysets 5 through the bolt, and combined material engine flame section of thick bamboo 10 is fixed on high temperature keysets 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;
the utility model also comprises a water cooling device 2 in the concrete realization;
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.
The utility model discloses in, in the concrete realization, measure temperature sensor 8, for K shape armor high temperature thermocouple sensor, glue through special high temperature, paste the temperature survey department at the combined material barrel surface regulation of combined material engine flame tube 10, be connected through the test cable with data record appearance 7, a temperature for gathering combined material engine flame tube 10 surface temperature survey department, acquire the temperature distribution condition and the maximum temperature gradient on 1 surface of combined material engine flame tube, a temperature for judging combined material engine flame tube 10 accords with experimental requirement.
The utility model discloses in, on specifically realizing, laser vibrometer 11 is non-contact's doppler high performance single-point laser vibrometer, fixes in the position department more than 1 meter apart from combined material engine flame section of thick bamboo 10 top through the support, passes through the test cable with data record appearance 7 and is connected for gather the vibration response at the appointed position on the combined material engine flame section of thick bamboo 10.
In the utility model, a control temperature sensor 9 is also included in the concrete realization;
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.
The utility model also comprises a vibration control system in the concrete realization;
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, to the utility model discloses, the correction is the meaning of adjustment, and the acceleration voltage signal of high temperature acceleration sensor 16 feedback compares with the experimental register of first vibration control appearance 17 settlement, and when feedback signal was less than the experimental register of settlement, first vibration control appearance 17 can increase output signal, and when feedback signal was greater than the experimental register of settlement, first vibration control appearance 17 can reduce output signal, and process more than the continuous repetition finally makes feedback signal and the experimental register of settlement keep unanimous.
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 the present invention, in the concrete implementation, the first electromagnetic vibration table 1 may be any electromagnetic vibration table, for example, a vibration table with a model MPA409/M437A/GT800M, which is manufactured by beijing space hill test technology limited, and the vibration table has a direct-coupling type electric vibration test system.
The utility model discloses in, in the concrete realization, data acquisition instrument 7, can be any kind of data acquisition instrument that has above function, for example can make the model that limited company produced for Jiangsu Tester electronic equipment for TST 5912's data acquisition analysis appearance, and it has dynamic signal test analytic system
The utility model discloses in, in the concrete realization, first vibration control appearance 17, the model that can produce for hundred million constant technology ltd of Hangzhou state is ECON VT-9016's vibration control appearance.
The utility model discloses in, in the concrete realization, first power amplifier 18, the model that can be the production of Beijing space hilt test technology limited is MPA 409's power amplifier, and it is intelligence switch power amplifier.
The utility model discloses in, specifically realize, high temperature acceleration sensor 16, can be any kind of high temperature acceleration sensor, the model that for example can be the production of qi swiss qi shi le instrument gmbh type is the high temperature acceleration sensor of 8202A type, and ceramic shears high temperature charge output type accelerometer promptly.
The utility model discloses in, in the concrete realization, laser vibrometer 11, the model that can produce for German Polytec is OFV-505/5000 high performance single-point laser vibrometer, and it is the Polytec high performance single-point laser vibrometer based on laser Doppler principle.
In the present invention, in the specific implementation, the high temperature strain gauge 6 may be a high temperature strain gauge manufactured by Vishay in usa, model ZWP-NC-063-.
In order to understand the present invention more clearly, the following description describes the specific process of the 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.
It should be noted that, to the utility model discloses, carry out sinusoidal fixed frequency vibration test to the flame tube, in the experiment or after the experiment, if flame tube barrel and part produce crackle or damage, then explain its vibration fatigue performance unqualified, if do not have unusually, then explain its vibration fatigue performance qualified.
The utility model discloses in, to first vibration control appearance 17, the excitation test condition of regulation includes: 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 10 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 utility model discloses following beneficial technological effect has:
1. the utility model discloses a finite element analysis, normal atmospheric temperature modal test and normal atmospheric temperature sinusoidal vibration test can the vibration test frequency under the accurate definite high temperature state, have solved the difficult point that can't carry out complicated modal test under the high temperature and confirm test frequency.
2. The utility model discloses can measure and acquire the strain data of combined material flame tube under the high temperature state, can provide truer strain data support for the analysis of the vibration characteristic under the flame tube high temperature environment.
3. The utility model discloses both can obtain the vibration characteristic of combined material flame tube under normal atmospheric temperature, verify each other with the finite element analysis result, can acquire the vibration characteristic under the combined material flame tube high temperature again, provide the data foundation for the vibration characteristic aassessment under the combined material flame tube high temperature state.
According to the above technical scheme, to the utility model discloses, can acquire vibration response acceleration data and vibration strain data under the resonance frequency of the flame tube focus of certain order under the high temperature environment, acquire the vibration fatigue characteristic of combined material flame tube under resonance frequency, provide the support for the technical research and development and the structural optimization of combined material flame tube.
It should be noted that, to the utility model provides a pair of high temperature vibration characteristic test system of combined material aeroengine flame tube, it utilizes the method that finite element modal analysis, frequency response analysis and normal atmospheric temperature modal test, normal atmospheric temperature sinusoidal vibration test combined together, measures high temperature vibration response and the vibration strain data that obtains combined material flame tube under the modal frequency of some (for example first order, second order or third order) focus attention, has obtained combined material flame tube vibration characteristic under high temperature environment.
To sum up, compare with prior art, the utility model provides a pair of high temperature vibration characteristic test system of combined material aeroengine flame tube, its high temperature operational environment that can simulate the flame tube acquires vibration response acceleration data and vibration strain data of flame tube under the certain order resonant frequency under the high temperature environment for explore combined material aeroengine flame tube vibration characteristic under the high temperature environment, provide the support for the technical development and the structural optimization of combined 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, a plurality of 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 (10) 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 (10) 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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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112577686A (en) * | 2020-12-16 | 2021-03-30 | 天津航天瑞莱科技有限公司 | High-temperature vibration characteristic test system for composite material aircraft engine flame tube |
| CN113804381A (en) * | 2021-11-18 | 2021-12-17 | 天津航天瑞莱科技有限公司 | Low oxygen, high temperature and vibration integrated environment test system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112577686A (en) * | 2020-12-16 | 2021-03-30 | 天津航天瑞莱科技有限公司 | High-temperature vibration characteristic test system for composite material aircraft engine flame tube |
| CN112577686B (en) * | 2020-12-16 | 2024-04-02 | 中国航发商用航空发动机有限责任公司 | High-temperature vibration characteristic test system for composite material aero-engine flame tube |
| CN113804381A (en) * | 2021-11-18 | 2021-12-17 | 天津航天瑞莱科技有限公司 | Low oxygen, high temperature and vibration integrated environment test system |
| CN113804381B (en) * | 2021-11-18 | 2022-04-15 | 天津航天瑞莱科技有限公司 | Low oxygen, high temperature and vibration integrated environment test system |
| CN117232470A (en) * | 2023-11-15 | 2023-12-15 | 天津航天瑞莱科技有限公司 | Performance parameter calibration device of strain gauge at high temperature |
| CN117232470B (en) * | 2023-11-15 | 2024-01-30 | 天津航天瑞莱科技有限公司 | Performance parameter calibration device of strain gauge at high temperature |
| CN117664584A (en) * | 2024-01-30 | 2024-03-08 | 天津航天瑞莱科技有限公司 | Thermal noise test device for test piece |
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Effective date of registration: 20220913 Address after: No. 3998, Lianhua South Road, Minhang District, Shanghai, 200000 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: No.9, Zhongbei 3rd Street, West District, Binhai New Area Development Zone, Tianjin 300462 Patentee before: TIANJIN AEROSPACE RELIA TECHNOLOGY Co.,Ltd. Patentee before: BEIJING INSTITUTE OF STRUCTURE AND ENVIRONMENT ENGINEERING |
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