CN112577686B - High-temperature vibration characteristic test system for composite material aero-engine flame tube - Google Patents
High-temperature vibration characteristic test system for composite material aero-engine flame tube Download PDFInfo
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- CN112577686B CN112577686B CN202011485692.5A CN202011485692A CN112577686B CN 112577686 B CN112577686 B CN 112577686B CN 202011485692 A CN202011485692 A CN 202011485692A CN 112577686 B CN112577686 B CN 112577686B
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 37
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- 238000012545 processing Methods 0.000 description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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Abstract
The invention discloses a high-temperature vibration characteristic test system of a flame tube of a composite aero-engine, which comprises a first electromagnetic vibration table; a composite material engine flame tube is fixedly arranged above the first electromagnetic vibration table; a quartz lamp radiation heater bracket is fixedly arranged right above the flame tube; the bottom surface of the quartz lamp radiation heater bracket is provided with a hollow cylindrical reflecting plate; a plurality of quartz lamps are arranged on the inner peripheral side wall of 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 adhered with a high-temperature strain gauge and a temperature measuring sensor; the high-temperature strain gauge is connected with the 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 invention can simulate the high-temperature working environment of the flame tube and acquire vibration response acceleration data and vibration strain data of the flame tube under a certain-order resonance frequency in the high-temperature environment.
Description
Technical Field
The invention relates to the technical field of mechanical environment tests of composite material aero-engine flame tubes, in particular to a high-temperature vibration characteristic test system of a composite material aero-engine flame tube.
Background
The flame tube of the aeroengine is a key component of the aeroengine, is a part for burning fuel gas of the engine, and is in a high-temperature environment in the running process of the engine. In order to improve thrust-weight ratio and thermal efficiency of the engine, reduce weight and noise level, composite materials are adopted to replace alloy materials, and the method is a direction of developing flame tubes of the aero-engine.
At present, as the composite material is applied to the design of the flame tube, the design is still in a research and development stage, and relatively few data can be referred to. In order to verify whether the structural design of the composite aero-engine flame tube meets the requirement of the working condition 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 the resonance frequency of a certain order (such as a first order, a second order or a third order) are required to be obtained in a high-temperature environment.
However, there is no technology that can acquire vibration characteristics (including vibration response acceleration and vibration stress) at a resonance frequency of a certain order (for example, first order, second order or third order) of the flame tube in a high-temperature environment.
Disclosure of Invention
The invention aims at providing a high-temperature vibration characteristic test system of a flame tube of a composite aeroengine, aiming at the technical defects existing in the prior art.
Therefore, the invention provides a high-temperature vibration characteristic test system of a flame tube of a composite aero-engine, which comprises a first electromagnetic vibration table;
wherein, the moving coil at the top of the first electromagnetic vibrating table is fixedly provided with a water cooling plate through bolts;
the top of the water cooling plate is fixedly provided with a heat insulation plate through bolts;
the top of the heat insulation plate is fixedly provided with a high-temperature adapter plate through bolts;
the top of the high-temperature adapter plate is fixedly provided with a flame tube of the composite material engine through bolts;
the first electromagnetic vibration table is used as a vibration excitation device and is used for providing exciting force for a vibration characteristic test of the flame tube of the composite material engine;
wherein, a ring-shaped quartz lamp radiation heater bracket is fixedly arranged right above the flame tube of the composite material engine;
the bottom surface of the quartz lamp radiation heater bracket is provided with a hollow cylindrical reflecting plate;
the inner peripheral side wall of the cylindrical reflecting plate is provided with a plurality of quartz lamps;
the composite material engine flame tube is positioned in the inner cavity of the cylindrical reflecting plate;
the surface of the flame tube of the composite engine is adhered 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 flame tube of the composite material engine 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 flame tube of the composite material engine 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 flame tube of the composite material engine;
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 vibration response acceleration of a designated part on the flame tube of the composite material engine and then sending the vibration response acceleration to the data recorder;
the data recorder is used for receiving and recording vibration response acceleration of a designated part on the composite material engine flame tube sent by the laser vibration meter, vibration stress of the composite material engine flame tube sent by the high-temperature strain gauge and temperature at a preset temperature measuring point on the surface of the composite material engine flame tube sent by the temperature sensor.
Preferably, the device also comprises a water cooling device;
the water cooling device is connected with the water cooling plate, the first electromagnetic vibration table and the cylindrical reflecting plate through water pipe pipelines and used for cooling the water cooling plate, the first electromagnetic vibration table and the cylindrical reflecting plate.
Preferably, the device further comprises a control temperature sensor;
the control temperature sensor is a K-shaped armored thermocouple sensor and is stuck 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 control instrument, 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 a specified excitation test condition;
the first power amplifier is connected with the first vibration controller and is 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 vibration table and feeding back the acceleration signal to the first vibration controller;
the first vibration controller is respectively connected with the first power amplifier and the high-temperature acceleration sensor and is used for correcting the vibration signal finally output by the first vibration controller by comparing the acceleration signal fed back by the high-temperature acceleration sensor with the vibration signal of the test spectrum set in the first vibration controller according to the acceleration signal fed back by the high-temperature acceleration sensor until the vibration signal generated by the first electromagnetic vibration table meets the tolerance requirement of the 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 of 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 (such as first order, second order or third order) resonance frequency under the high-temperature environment, is used for exploring the vibration characteristic of the composite material aero-engine flame tube under the high-temperature environment, and provides support for the technical research, development and structural optimization of the composite material flame tube.
Drawings
FIG. 1 is a schematic diagram of the overall structure of a high-temperature vibration characteristic test system of a composite material aero-engine flame tube;
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 view of a test system for a normal temperature sinusoidal vibration test in the present invention;
in the figure, 1 is a first electromagnetic vibration table, 2 is water cooling equipment, 3 is a water cooling plate, 4 is a heat insulating plate and 5 is a high-temperature adapter plate;
6 is a high-temperature strain gauge, 7 is a data recorder, 8 is a measuring temperature sensor, 9 is a control temperature sensor, and 10 is a composite material engine flame tube;
the laser vibration meter is 11, the quartz lamp radiation heater fixing bracket is 12, the quartz lamp is 13, the cylindrical reflecting plate is 14, and the quartz lamp radiation heater control system is 15;
a high-temperature acceleration sensor 16, a first vibration controller 17 and a first power amplifier 18;
21 is a second electromagnetic vibration table, 22 is a water-cooled cabinet, 23 is a switching tool, 24 is a normal-temperature strain gauge and 25-data acquisition instrument;
the reference numeral 27 denotes a normal temperature measurement acceleration sensor, 28 denotes a normal temperature control acceleration sensor, 29 denotes a second vibration controller, and 30 denotes a second power amplifier.
Detailed Description
In order that the manner in which the invention is practiced will be understood more readily, reference is now made to the following detailed description of the invention taken in conjunction with the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the application and not limiting of the application. It should be further noted that, for convenience of description, only the portions relevant to the present application are shown in the drawings.
It should be noted that, in the case of no conflict, the embodiments and features in the embodiments may be combined with each other. The present application will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
It should be noted that, in the description of the present application, terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," "outer," and the like indicate directions or positional relationships, which are merely for convenience of description, but do not indicate or imply that the apparatus or elements 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 explicitly specified and limited otherwise, the term "mounted" and the like should be construed broadly, and may be either fixedly mounted or detachably mounted, for example.
The specific meaning of the terms in this application will 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 flame tube of a composite aero-engine, which is a test system for performing a high Wen Zhengxian vibration test and specifically comprises a first electromagnetic vibration table 1;
wherein, the moving coil at the top of the first electromagnetic vibrating table 1 is fixedly provided with a water cooling plate 3 through bolts;
the top of the water cooling plate 3 is fixedly provided with a heat insulation plate 4 through bolts;
the top of the heat insulation plate 4 is fixedly provided with a high-temperature adapter plate 5 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 vibration table 1 is used as a vibration excitation device and is used for providing exciting force for the vibration characteristic test of the flame tube 10 of the composite material engine;
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 fixture for transmitting the exciting force of the first electromagnetic vibration table 1 to the flame tube 10 of the composite engine.
Wherein, a ring-shaped quartz lamp radiation heater bracket 12 is fixedly arranged right above the flame tube 10 of the composite material engine;
the bottom surface of the quartz lamp radiation heater bracket 12 is provided with a hollow cylindrical reflecting plate 14;
a plurality of quartz lamps 13 are arranged on the inner peripheral side wall of the cylindrical reflecting plate 14;
a composite engine flame tube 10 positioned in the inner cavity of the cylindrical reflector plate 14;
the quartz lamp 13 and the annular reflecting plate 14 together form a quartz lamp radiant heater, and are fixed on the quartz lamp radiant heater bracket 12, so that the whole composite engine flame tube 10 is covered in the quartz lamp radiant 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 engine flame tube 10; the high temperature loading and controlling system comprises a quartz lamp 13, a cylindrical reflecting plate 14, a quartz lamp radiation heater controlling system 15, a quartz lamp radiation heater fixing bracket 12 and a control temperature sensor 9. The quartz lamp 13 is fixed on the hollow cylindrical reflecting plate 14 through a conductive copper bar, the cylindrical reflecting plate 14 is fixed on the quartz lamp radiation heater fixing support 12, the quartz lamp 13 is controlled by the conductive copper bar, a cable and the quartz lamp radiation heater control system 15, and the output power of the quartz lamp 13 can be controlled by adjusting parameters of the quartz lamp radiation heater control system 15, so that adjustment of different temperatures is realized.
The surface of the flame tube 10 of the composite engine 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 (namely vibration strain data) of the flame tube 10 of the composite material engine and then sending the vibration stress data to the data recorder 7;
the measuring temperature sensor 8 is connected with the data recorder 7 and is used for collecting the temperature at a preset temperature measuring point on the surface of the flame tube 10 of the composite material engine and then sending the temperature to the data recorder 7;
the high-temperature strain gauge 6 can be stuck to a strain measuring point specified on the surface of the composite material cylinder of the composite material engine flame tube 10 through special high-temperature glue 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 flame tube 10 of the composite material engine;
the laser vibration meter 11 is positioned right above the 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 vibration response acceleration of a designated part on the flame tube 10 of the composite material engine and then sending the vibration response acceleration to the data recorder 7;
the data recorder 7 is used for receiving and recording vibration response acceleration of a designated part on the composite material engine flame tube 10 sent by the laser vibration meter 11, vibration stress of the composite material engine flame tube 10 sent by the high-temperature strain gauge 6 and temperature at a preset temperature measuring point on the surface of the composite material engine flame tube 10 sent by the measured temperature sensor 8.
In the present invention, the laser vibration meter 11 is used to measure vibration response acceleration data of the composite engine flame tube 10, the high temperature strain gauge 6 is used to measure vibration strain data of the composite engine flame tube 10, the temperature sensor 8 is used to measure temperature response data of different positions of the composite engine flame tube 10, and vibration characteristics and temperature distribution of the composite engine flame tube 10 can be obtained by analyzing the measured data.
In the present invention, the data recorder 7, the laser vibrometer 11, the high temperature strain gauge 6, and the measurement temperature sensor 8 together form 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 the concrete implementation, the water cooling plate 3 is connected with the water cooling equipment 2, and the water cooling plate 3 is used for preventing high temperature from being transmitted to the moving coil of the first electromagnetic vibration table 1 and protecting the first electromagnetic vibration table 1;
the concrete implementation is that the heat insulating plate 4 is made of high-temperature-resistant mineral powder, has the advantages of high temperature resistance, low heat conductivity and high compressive strength, and is positioned between the high-temperature adapter plate 5 and the water cooling plate 3, so that heat conduction loss is reduced;
in the concrete implementation, the high-temperature adapter plate 5 is made of a high-temperature alloy material, can keep good rigidity at high temperature, and is beneficial to transmitting exciting force to the composite engine flame tube 10;
in the invention, the concrete implementation way further comprises a water cooling device 2;
the water cooling equipment 2 is connected with the water cooling plate 3, the first electromagnetic vibration table 1 and the cylindrical reflecting plate 14 through water pipe pipelines and is used for cooling the water cooling plate 3, the first electromagnetic vibration table 1 and the cylindrical reflecting plate 14, and plays a role in cooling through water circulation.
The water cooling device 2 may be an existing circulation water chiller, for example, a circulation water chiller having a model number XT550W manufactured by LAUDA corporation, germany, and may be used to cool the water cooling plate 3.
In the invention, the measuring temperature sensor 8 is a K-shaped armored thermocouple sensor, is stuck at a temperature measuring point specified by the surface of a composite material cylinder of the composite material engine flame tube 10 through special high-temperature glue, is connected with the data recorder 7 through a testing cable, is used for collecting the temperature at the temperature measuring point on the surface of the composite material engine flame tube 10, and is used for acquiring the temperature distribution condition and the maximum temperature gradient of the surface of the composite material engine flame tube 10 and judging whether the temperature of the composite material engine flame tube 10 meets the test requirement.
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 which is more than 1 meter away from the top of the flame tube 10 of the composite engine through a bracket, is connected with the data recorder 7 through a test cable, and is used for collecting the vibration response of a designated part on the flame tube 10 of the composite engine.
In the invention, the method comprises a control temperature sensor 9;
the control temperature sensor 9 is a K-shaped armored thermocouple sensor, is stuck to a temperature measuring point specified on the surface of a composite material cylinder body of the composite material engine flame cylinder 10 through special high-temperature glue, and 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 which is used for controlling and adjusting the output power of the quartz lamp 13 so that the temperature of the composite material engine flame cylinder 10 reaches 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, for example, a quartz lamp radiant heating controller with model number KZGZL-P-DC300-02C manufactured by wuhan crowdsourcing measurement and control technology limited may be used to control the quartz lamp 13 to heat the flame tube 10.
The quartz lamp 13 and the cylindrical reflecting plate 14 together form a quartz lamp radiant heater, and are fixed on the quartz lamp radiant heater bracket 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 for realizing vibration test conditions prescribed by the test.
In the invention, the concrete implementation further comprises 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 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 excitation test condition;
the first 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;
a high-temperature acceleration sensor 16 for measuring an acceleration signal output from 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 is configured to correct a vibration signal finally output by the first vibration controller 17 (i.e., a vibration signal of a corrected test spectrum) by comparing the 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 the acceleration signal fed back by the high temperature acceleration sensor 16 until the vibration signal generated by the first electromagnetic vibration table 1 meets the tolerance requirement of the 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.
In the present invention, the correction means that 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 process is repeated continuously, so that the feedback signal and the set test spectrum are kept consistent.
The tolerance of the test conditions is generally regulated to be within ±3dB of the set test spectrum, so as to meet the requirements of the test standard.
In the present invention, the first electromagnetic vibration table 1 may be any electromagnetic vibration table, for example, a vibration table manufactured by the company limited of the space hill test in Beijing and having a model number MPA409/M437A/GT800M, and the vibration table has a direct-coupled electric vibration test system.
In the present invention, the data recorder 7 may be any data acquisition device with the above functions, for example, a data acquisition analyzer with model TST5912 manufactured by Jiangsu tesi electronics, inc., and having a dynamic signal test analysis system
In the present invention, the first vibration controller 17 may be a vibration controller with a model number of ECON VT-9016 manufactured by the company limited in glory, glory.
In the present invention, in a specific implementation, the first power amplifier 18 may be a power amplifier manufactured by the company limited of the testing technology of Beijing and space, and having a model MPA409, which is an intelligent switching power amplifier.
In the present invention, the high-temperature acceleration sensor 16 may be any high-temperature acceleration sensor, for example, a model 8202A type high-temperature acceleration sensor manufactured by the company of the instruments, inc. Of the Chery-shi Dan Le, i.e., a ceramic shear high Wen Dianhe output type accelerometer.
In the present invention, the laser vibration meter 11 may be a model OFV-505/5000 high-performance single-point laser vibration meter manufactured by Polytec in germany, which is a Polytec high-performance single-point laser vibration meter based on the laser doppler principle.
In the present invention, the high temperature strain gauge 6 may be a type 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 flow of the present invention for performing a high Wen Zhengxian vibration test, specifically including the following steps:
1. the water cooling plate 3 is fixed on the moving coil of the first electromagnetic vibration table 1 through bolts;
2. the heat insulation plate 4 and the high-temperature adapter plate 5 are fixed 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 the 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 a normal state;
4. pasting the high-temperature strain gauge 6 and the measurement temperature sensor 8 at a specified test position, connecting the high-temperature strain gauge 6 and the measurement temperature sensor 8 with the data recorder 7 through a cable, starting the data recorder 7, and debugging the data of the high-temperature strain gauge 6 and the measurement temperature sensor 8 to be normal;
5. fixing a flame tube 10 of the composite material engine 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, covering the whole flame tube 10 in the quartz lamp radiation heater, sticking a control temperature sensor 9 on the flame tube 10 of the composite material engine, 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 a cable, starting the laser vibration meter 11 and the data recorder 7, and performing focusing debugging until signals are normal;
8. setting prescribed vibration test conditions on the first vibration controller 17, setting data acquisition parameters on the data recorder 7, and debugging the control system and the measurement system to be normal;
9. starting a quartz lamp radiation heater control system 15, setting a test temperature, heating a composite material engine flame tube 10, and preserving heat when the temperature at a control temperature sensor 9 reaches a specified control temperature until the temperature fluctuation at 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 sinusoidal sweep vibration test, monitoring a vibration control curve, starting a data recorder 7 after vibration reaches a specified condition (the specific condition is a sinusoidal sweep test condition, the frequency range is 10-2000 Hz, the vibration acceleration magnitude is 1 g) and 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 fixed frequency test is performed with the determined modal frequency as the test frequency of the sinusoidal fixed frequency vibration (i.e., the vibration test frequency in the high temperature state, and in order to determine the vibration test frequency in the high temperature state, specific confirmation steps are described below). The strain response of the high temperature strain gauge of the composite engine flame tube 10 at a prescribed magnitude and test frequency is obtained. And meanwhile, the vibration fatigue performance of the flame tube is checked.
In the present invention, the flame tube is subjected to a sinusoidal fixed-frequency vibration test, and if the flame tube body and its components are cracked or damaged during the test or after the test is completed, the vibration fatigue performance is not qualified, and if no abnormality exists, the vibration fatigue performance is qualified.
In the present invention, the predetermined excitation test conditions for the first vibration controller 17 include: vibration test frequency in high temperature state, which is resonance frequency of certain order (such as first order, second order or third order) of flame tube in 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:
s1, carrying out finite element modal analysis and finite element frequency response analysis of the flame tube of the composite material aeroengine 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 may be performed using well-established finite element modeling analysis software, such as Patran, ansys, and the like.
In particular implementation, the basic flow of finite element modal analysis is as follows: establishing a geometric model of the flame tube of the composite aeroengine, meshing the geometric model to establish a finite element analysis model, setting boundary constraint of the model, setting material data of the model, submitting to perform finite element modal analysis, acquiring finite element modal analysis results, and extracting the maximum vibration mode and strain position of the flame tube under a certain-order resonant frequency of interest.
In particular implementation, the basic flow of the frequency response analysis is as follows: establishing a geometric model of the flame tube of the composite aeroengine, meshing 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, obtaining 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 resonance frequency of interest.
The finite element modal analysis result and the finite element frequency response analysis result obtained in the above are used as theoretical references of a modal test and a sinusoidal vibration test.
And S2, carrying out a mode analysis test of the flame tube of the composite aero-engine in a fixed state at the normal temperature through a test system of the normal temperature mode test to obtain the position of the maximum vibration response point and the position of the maximum strain in the mode shape corresponding to the first-order mode frequency of the flame tube 10 of the composite aero-engine.
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 exciting force;
a charge discharger for converting a charge signal input from the force sensor into a voltage signal;
the acceleration sensor is adhered to the flame tube 10 of the composite engine and is used for measuring vibration response signals;
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 frequencies, modal damping and modal vibration modes of the flame tube 10 of the composite engine, and recording the modal damping and modal vibration modes corresponding to each modal frequency;
in particular implementation, the test system for normal temperature modal analysis test has the following basic wanted flow for modal analysis:
step S21, fixing the composite engine flame tube 10 on an expansion table surface of the vibration table.
Step S22, referring to the mode shape obtained by the finite element mode analysis in the previous step S1, determining the measuring point position of the flame tube 10 of the composite material engine.
And S23, sticking an acceleration sensor at the measuring point, connecting a cable, and connecting with a data acquisition analyzer.
And step S24, connecting a force sensor of the modal force hammer to a charge amplifier by utilizing a signal wire, and then connecting the charge amplifier with a data acquisition analyzer.
And S25, setting parameters of a 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 the data acquisition analyzer to be normal.
Step S26, the modal force hammer is utilized to strike the flame tube 10 of the composite engine, and modal test data are obtained.
Step S27, processing test data by using a data acquisition analyzer to obtain a frequency response function, then carrying out modal parameter identification to obtain modal frequencies, modal damping and modal vibration modes, and recording the modal damping and modal vibration modes corresponding to each modal frequency;
and S28, comparing the modal frequencies, the modal damping and the modal shape obtained by 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 frequencies, the modal damping and the modal shape.
When the mode shape obtained by the mode test is consistent with the mode shape of the finite element mode analysis result, and the mode frequency obtained by the mode test is consistent with the mode frequency order and sequence of the finite element mode analysis result, the mode frequency, the mode damping and the mode shape data are determined to be effective.
And S29, determining a first-order modal frequency as a subsequent test frequency in the acquired modal test result, and determining the position of the maximum point of vibration response and the position of the maximum strain in the modal shape corresponding to the first-order modal frequency according to the modal shape corresponding to the first-order modal frequency.
And S3, carrying out a sinusoidal vibration test of the flame tube of the composite aero-engine in a fixed state at the normal temperature through a test system of the normal-temperature sinusoidal vibration test, and determining the vibration test frequency at the high temperature.
In particular, referring to fig. 3, the test system for the normal temperature sinusoidal vibration test includes: 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 exciting force for a sinusoidal vibration test of the flame tube 10 of the composite material engine;
a second vibration controller 29 for controlling the second electromagnetic vibration table 21 to output a sinusoidal signal;
the normal temperature measurement acceleration sensor 27 is used for measuring acceleration response at a specified measuring point on the composite engine flame tube 10.
In particular, the top of the second electromagnetic vibration table 21 is provided with an adapting tool 23 (an existing adapting tool, for example, an existing clamping tool);
the composite material engine flame tube 10 is fixed on the switching tool 23;
the surface of the flame tube 10 of the composite engine is adhered with a normal temperature strain gauge 24;
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 flame tube 10 of the composite material engine and then sending the vibration stress data to the data acquisition instrument 25;
the top of the composite engine flame tube 10 is provided with a normal temperature measurement acceleration sensor 27;
the normal temperature measuring acceleration sensor 27 is connected with the data acquisition instrument 25 and is used for acquiring the temperature of the surface of the flame tube 10 of the composite material engine and then sending the temperature to the data acquisition instrument 25;
in the concrete implementation, the normal temperature control acceleration sensor 28 is arranged on the switching tool 23;
a normal temperature control acceleration sensor 28 connected to the second vibration controller 29;
a second vibration controller 29 connected to the second power amplifier 30
In particular, the second electromagnetic vibration table 21 is also connected with the existing water cooling cabinet.
The method specifically realizes the flow of the normal-temperature sinusoidal vibration test performed by the test system of the normal-temperature sinusoidal vibration test, and specifically comprises the following steps:
step S31, fixing the composite engine flame tube 10 on the expansion table surface of the second electromagnetic vibration table 21.
Step S32, sticking a measurement acceleration sensor (namely, a normal temperature measurement acceleration sensor 27) on the flame tube by referring to the mode shape and the maximum strain point position obtained by the finite element mode analysis in the previous step S1, specifically sticking the acceleration sensor on the maximum vibration shape point position of the flame tube 10 of the composite material engine, and sticking a normal temperature strain gauge (namely, a normal temperature strain gauge 24) on the maximum strain point position and the nearby position;
an acceleration sensor (i.e., a normal temperature control acceleration sensor 28) is attached to the connection between the composite engine flame tube 10 and the tool as a vibration control sensor.
Step S33, connecting the strain gauge with a data acquisition analyzer, and debugging to be normal;
step S34, connecting the second vibration controller with the second power amplifier and the normal temperature control acceleration sensor 28, and debugging to be normal;
and S35, setting sine sweep test conditions on the second vibration controller, running a vibration control test system, and performing sine sweep test.
Step S36, a transfer function curve of each measuring point in a sinusoidal sweep test is obtained, then the transfer function curve is compared with the finite element modal analysis result and the finite element frequency response analysis result obtained in the step S1, and the modal frequency and the test direction which are the vibration test frequency in a high temperature state are determined 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;
for the flame tube product, the sweep frequency direction is vertical and horizontal, transfer function curve data of the two directions are respectively obtained through a sweep frequency test, the obtained transfer function curve and modal vibration mode are compared with a modal simulation analysis result, the direction with larger vibration response and strain response amplitude under a certain-order modal frequency is used as the test direction, and the modal frequency is used as the test frequency.
And selecting the direction with the largest vibration response and strain response as the test direction. By determining the test direction, it is possible to ensure that the structural strength of the test product can be checked under the most severe test conditions.
Step S37, performing a constant frequency sinusoidal vibration test in the determined modal frequency and test direction, and determining the position of the maximum strain as the position of the strain point in the high temperature vibration characteristic and vibration fatigue test (i.e., the strain point position to which the high temperature strain gauge 6 is attached).
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 complex modal test at high temperature is solved.
2. The invention can measure and acquire the strain data of the composite material flame tube in a high-temperature state, and can provide a relatively real strain data support for the analysis of the vibration characteristics of the flame tube in a high-temperature environment.
3. The invention can obtain the vibration characteristic of the composite material flame tube at normal temperature, mutually verify with the finite element analysis result, and obtain the vibration characteristic of the composite material flame tube at high temperature, thereby providing data basis for the evaluation of the vibration characteristic of the composite material flame tube at high temperature.
Based on the technical scheme, the method can acquire vibration response acceleration data and vibration strain data of the flame tube under the resonance frequency of important attention of a certain order in a high-temperature environment, acquire the vibration fatigue characteristic of the composite flame tube under the resonance frequency, and provide support for technical research and development and structural optimization of the composite flame tube.
The invention provides a high-temperature vibration characteristic test system of a composite material aeroengine flame tube, which is used for measuring and obtaining high-temperature vibration response and vibration strain data of the composite material flame tube under the mode frequency of a certain order (such as first order, second order or third order) which is focused on by utilizing a method of combining finite element mode analysis, frequency response analysis, normal-temperature mode test and normal-temperature sinusoidal vibration test, and obtaining the vibration characteristic of the composite material flame tube under a 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 resonance frequency in the high-temperature environment, is used for exploring the vibration characteristic of the composite material aero-engine flame tube under the high-temperature environment, and provides support for technical research, development and structural optimization of the composite material flame tube.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which are intended to be comprehended within the scope of the present invention.
Claims (2)
1. The high-temperature vibration characteristic test system of the composite material aero-engine flame tube is characterized by comprising a first electromagnetic vibration table (1);
the movable coil at the top of the first electromagnetic vibrating table (1) is fixedly provided with a water cooling plate (3) through bolts;
the top of the water cooling plate (3) is fixedly provided with a heat insulation plate (4) through bolts;
the top of the heat insulation plate (4) is fixedly provided with a high-temperature adapter plate (5) 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 vibration table (1) is used as a vibration excitation device and is used for providing exciting force for a vibration characteristic test of the composite material engine flame tube (10);
wherein, a ring-shaped quartz lamp radiation heater bracket (12) is fixedly arranged right above the flame tube (10) of the composite material engine;
the bottom surface of the quartz lamp radiation heater bracket (12) is provided with a hollow cylindrical reflecting plate (14);
a plurality of quartz lamps (13) are arranged on the inner peripheral side wall of the cylindrical reflecting plate (14);
a composite engine flame tube (10) positioned in the inner cavity of the cylindrical reflecting plate (14);
the surface of the flame tube (10) of the composite engine 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 flame tube (10) of the composite material engine 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 at a preset temperature measuring point on the surface of the flame tube (10) of the composite material engine and then sending the temperature to the data recorder (7);
wherein, a laser vibration meter (11) is fixedly arranged right above the flame tube (10) of the composite material engine;
the laser vibration meter (11) is positioned right above the 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 vibration response acceleration of a designated part on the flame tube (10) of the composite material engine and then sending the vibration response acceleration to the data recorder (7);
the data recorder (7) is used for receiving and recording vibration response acceleration of a designated part on the composite material engine flame tube (10) sent by the laser vibration meter (11), vibration stress of the composite material engine flame tube (10) sent by the high-temperature strain gauge (6) and temperature at a preset temperature measuring point on the surface of the composite material engine flame tube (10) sent by the temperature sensor (8);
the high-temperature vibration characteristic test system of the composite material aero-engine flame tube also comprises water cooling equipment (2);
the water cooling device (2) is connected with the water cooling plate (3), the first electromagnetic vibration table (1) and the cylindrical reflecting plate (14) through water pipe pipelines and is used for cooling the water cooling plate (3), the first electromagnetic vibration table (1) and the cylindrical reflecting plate (14);
the high-temperature vibration characteristic test system of the composite material aero-engine flame tube also comprises a control temperature sensor (9);
the control temperature sensor (9) is a K-shaped armored thermocouple sensor and is stuck to a temperature measuring point specified on the surface of a composite material cylinder body of the composite material engine flame cylinder (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.
2. The composite aero-engine flame tube high temperature vibration characteristic test system of claim 1, further comprising a vibration control system;
the vibration control system is a closed-loop control system and comprises a first vibration control instrument (17), a first power amplifier (18) and a high-temperature acceleration sensor (16);
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 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 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) 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) according to the acceleration signal fed back by the high-temperature acceleration sensor (16) 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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| 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 |
| CN114543970B (en) * | 2022-02-22 | 2024-01-12 | 西安航天动力试验技术研究所 | Rocket engine non-contact vibration test system and calibration method thereof |
| CN116822299B (en) * | 2023-06-30 | 2024-01-23 | 南京航空航天大学 | Rapid calculation method for thermal stress of aeroengine flame tube under service load course |
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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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