CN105571867B - A kind of aero-engine vibration control experiment platform - Google Patents

Abstract

An aero-engine vibration control experimental platform, including a test bench base, an aero-engine body, a drive system, a measurement and control system, and a safety protection device; the first drive motor of the drive system transmits power to the aero-engine through a first coupling The low-pressure rotor system of the main body, the second drive motor transmits power to the high-pressure rotor system of the aero-engine body through the second coupling and the accessory transmission system of the aero-engine body, and the output shaft of the motor, the low-pressure rotor system and the high-pressure rotor system are Equipped with capacitive displacement sensors, the 2-stage casing, 3-stage casing, 6-stage casing, combustion chamber casing and high-pressure turbine casing corresponding to the 5 supporting bearings of the aero-engine are equipped with three-way vibration acceleration sensors. It can be used to test and analyze multi-factor coupling vibration problems of aero-engines; it is widely used in the research of vibration characteristics and vibration control strategies of aero-engine dual-rotor systems.

Description

An experimental platform for aero-engine vibration control

technical field

The invention relates to an engine experiment device, in particular to an aeroengine experiment platform.

Background technique

As the power device of aircraft, aeroengine is the key to measure a country's power research and development and manufacturing level, and an important symbol of the strength of a great power. Its related technical research has extremely high political, economic and military value. In recent years, the requirements for engine performance have been continuously improved, and the load on engine components has increased significantly, resulting in very prominent vibration problems. Vibration control has become one of the important research projects of aeroengines.

The research on the vibration control technology of aero-engine needs the support of the corresponding experimental platform. The existing experimental platform is generally oriented to the local construction of the aero-engine, which is suitable for the study of single factors one by one. After years of accumulation, there is an urgent need for an experimental platform that can fully reflect the various causes of vibration and noise for related research on vibration and noise control, especially in the new situation where the country is vigorously promoting military-civilian integration, and more units are involved in the aviation field. The support of class experiment platform. The existing experimental platform for research on vibration control of aero-engines simplifies aero-engines into different forms of rotor systems, which are used to study the dynamic response characteristics of aero-engines under various single or these few factors, and play a role in promoting the development of high-performance aero-engine technology. It has accumulated a large number of excellent results, but it can no longer meet the further research needs of multi-factor coupling vibration response characteristics that are more consistent with the actual operation of aero-engines. An aero-engine vibration control experiment platform disclosed in the present invention is a modification and utilization of a real aero-engine, and can be used for multi-factor coupling vibration response characteristics and control research.

Contents of the invention

In view of the above situation, the purpose of the present invention is to overcome the shortcomings and deficiencies of the prior art, and provides an aero-engine vibration control experimental platform, which can reflect the vibration of the aero-engine's high-low pressure dual-rotor system under maneuvering flight conditions. The real situation; and the overall structure is consistent with the real structure of the aero-engine, only part of the structure of the engine is modified, the cost of transformation is low, the difficulty of transformation is not high, and it is easy to popularize.

An aero-engine vibration control experimental platform, the experimental platform includes a test bench base, and an aero-engine body, a drive system, a measurement and control system and a safety protection device fixed on the test bench base; the first drive motor of the drive system The power is transmitted to the low-pressure rotor system of the aero-engine body through the first coupling, and the second drive motor of the drive system transmits power to the high-pressure rotor system of the aero-engine body through the second coupling and the accessory drive system of the aero-engine body. The rotor system, the motor output shaft of the first drive motor and/or the second drive motor, and the low-pressure rotor system and high-pressure rotor system of the aero-engine are provided with capacitive displacement sensors, and the 2 corresponding to the 5 supporting bearings of the aero-engine There are three-way vibration acceleration sensors on the first-stage casing, third-stage casing, sixth-stage casing, combustion chamber casing and high-pressure turbine casing.

The main body of the aero-engine is an aero-engine from which the afterburner and the tail nozzle have been removed.

In order to achieve structural optimization, further measures: the support method of the aero-engine body of the experimental platform is suspended and installed on the base of the experimental platform through four suspension points on the casing.

In order to facilitate the observation of the internal structure of the aero-engine and the installation relationship of each component, the first-level casing, the fourth-level casing, the combustion chamber casing, the combustion chamber casing, the combustion chamber casing, the heat shield, The outer wall of the afterburner diffuser is cut 1/8 to form an observation window.

The first drive motor of the drive system drives the low-pressure rotor by removing the fairing at the front end of the compressor, and then connects the low-pressure rotor system through the first coupling; the second drive motor of the drive system drives the low-pressure rotor by replacing the accessory The starter motor in the transmission system drives the high voltage rotor system.

The measurement and control system includes a motor control cabinet, a capacitive displacement sensor, a three-way vibration acceleration sensor, a data acquisition system, a PC and connecting wires.

The start-stop and turn-around of the first drive motor and/or the second drive motor in the drive system are controlled by frequency conversion in the motor control cabinet of the measurement and control system.

The aero-engine body and drive system of the experimental platform are set inside the safety protection device, and the motor control cabinet of the measurement and control system is set outside the safety protection device.

Compared with the beneficial effects produced by the prior art, the present invention:

(I) The present invention can be modified on the prototype of the aero-engine or the body of the mass-produced machine, and the size and installation position of each rotor component are consistent with the actual situation, effectively avoiding the failure of the experimental results caused by the difference in form ;

(II) The overall structure of the present invention is scientific and reasonable, the transformation is not difficult, the transformation cost is low, there is no environmental pollution, and it is easy to popularize;

(Ⅲ) The low-pressure rotor system and the high-pressure rotor system of the present invention are equipped with capacitive displacement sensors that can be used to measure the radial runout and axial runout of the rotating shaft, and a three-way vibration acceleration sensor is provided on the casing corresponding to the position of each bearing It is used to measure the vibration of the system, which can better understand the actual operation of the engine, facilitate more comprehensive vibration monitoring of key components in the engine, and provide a good reference for the vibration evolution process and vibration control research of aero-engines under multiple factors. experimental conditions;

(Ⅳ) The present invention cuts parts of the engine so that we can easily observe the structural characteristics of each part of the engine, the structural relationship between the parts, and demonstrate the dual-rotor rotation function and dual-rotor slip function of the experimental platform, and The working condition of each functional component.

The invention is widely applicable to the vibration characteristic analysis, vibration control and state monitoring research of the double-rotor structure of the aero-engine.

The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

Description of drawings

Fig. 1 is the front view of the experimental bench structure of the present invention;

Fig. 2 is the top view of the experimental bench structure of the present invention;

Fig. 3 is the right view of the experimental bench structure of the present invention;

Fig. 4 is a schematic structural view of an aero-engine in the present invention;

Fig. 5 is a schematic diagram of a partially cut-away structure of an aero-engine casing in the present invention;

Fig. 6 is a top view of the support structure of the present invention;

Fig. 7 is the front view that sensor of the present invention is installed;

Fig. 8 is the structural block diagram of experiment platform of the present invention;

Fig. 9 is a block diagram of the measurement and control system of the present invention.

In the figure: 1. Aero-engine body; 3. Safety protection device; 5. Test bench base; 6. First coupling; 7. Second coupling; 8. Capacitive displacement sensor; 9. Three-way vibration Acceleration sensor; 10. Suspension point; 11. Low-voltage rotor system; 12. High-voltage rotor system; 21. First drive motor; 22. Second drive motor; 41. Motor control cabinet.

Detailed ways

As shown in Figure 1, an aero-engine vibration control experiment platform is composed of five parts: an aero-engine body 1 , a drive system, a safety protection device 3 , a measurement and control system and a test bench base 5 .

Described drive system comprises the first drive motor 21, the first shaft coupling 6, the second drive motor 22 and the second shaft coupling 7; Connect the low-pressure rotor system 11 that transmits power to the aero-engine body 1, and the second drive motor 22 of the drive system transmits power to the high-pressure rotor system of the aero-engine body 1 through the second coupling 7 and the accessory drive system in the aero-engine body 1. The rotor system 12; the drive system is sequentially connected with the aero-engine body 1 and fixed on the base 5 of the test bench. As a better experimental platform scheme, the inner rotor is connected to the first driving motor through the first coupling, and the outer rotor is connected to the second driving motor through the pulley and the second coupling, which is essentially the key structure of the aeroengine. There is still a large difference between the simulation and the actual structure. The outer rotor is connected with the second drive motor through the pulley and the second coupling, and the stability of power transmission is poor. The aero-engine body of an aero-engine vibration control experiment platform disclosed in the present invention is a real aero-engine with the afterburner and tail nozzle removed, and the research on vibration characteristics and control is carried out based on its actual structure, which fully meets the actual needs; the drive system The second driving motor transmits power to the high-pressure rotor system through the second coupling and the accessory transmission system of the aero-engine body, which has a more compact structure and better stability. It can be modified on the basis of decommissioned aero engines or prototypes, which is environmentally friendly and further saves costs.

The measurement and control system includes a motor control cabinet 41, a capacitive displacement sensor 8, a three-way vibration acceleration sensor 9, a data acquisition system, a PC and connecting wires. The motor control cabinet 41 is provided with a control system and a display. The capacitive displacement sensor 8 and the three-way vibration acceleration sensor 9 belong to the acquisition part. The signal output end of the acquisition part is filtered by a filter and then connected to the signal input end of the control system. The signal output end is connected to the signal input end of the display, and the acquisition part sends the signal to the control system, and the control system displays the corresponding data on the display after processing, or outputs the signal.

Referring to the accompanying drawings, the aero-engine body 1 is a real aero-engine assembly with the afterburner and tail nozzle removed. The structure of the aircraft engine body 1 of the present invention mainly includes a low-pressure rotor system 11 and a high-pressure rotor system 12. The low-pressure rotor system 11 is composed of a three-stage low-pressure compressor, a low-pressure rotor and a one-stage low-pressure turbine. The high-pressure rotor system 12 is composed of a three-stage high-pressure compressor. It is composed of a high-pressure rotor and a high-pressure turbine. The low-pressure shaft passes through the hollow high-pressure shaft to form a double-rotor system. Preferably, capacitive displacement sensors 8 are provided on the low-pressure rotor and the high-pressure rotor of the aeroengine. The whole dual-rotor system is supported by 5 bearings, the 2-stage low-pressure compressor is supported by the front support bearing, the 2-stage high-pressure compressor is supported by intermediate bearings, and the 3-stage high-pressure compressor is installed behind two roller bearings Support, there is a rear support bearing at the front end of the high-pressure turbine, and there is a roller bearing support between the high-pressure turbine and the low-pressure turbine; referring to Figure 4, there are casing supports at various levels outside the double rotor, mainly including the first-stage casing I and the second-stage casing. -3-stage casing II, 4-stage casing III, 5-stage casing IV, 6-stage casing V, combustor casing VI, high-pressure turbine casing VII, low-pressure turbine casing VIII, afterburner diffuser casing Ⅸ, afterburner receiver Ⅹ and exhaust pipe receiver Ⅺ.

In order to facilitate our observation of the structural characteristics of each component of the engine and the equipment relationship between the components, it is shown that the experimental platform has dual-rotor rotation functions, dual-rotor slip functions, and the working conditions of each functional component, as shown in Figure 5. 1/8 section of the aero-engine body 1's 1st-stage casing I, 4th-stage casing III, combustion chamber casing VI, combustion chamber casing, combustion chamber casing, heat shield, and afterburner diffuser outer wall Cut; the afterburner and the tail nozzle part of the aero-engine are removed, and the modified aero-engine is suspended and installed on the base 5 of the test bench through four suspension points 10 on the casing of the aero-engine body 1 . The engine is started by the starter, and the power of the starter comes from the starter motor, which needs to be transmitted through the accessory drive system. After the starter is started, it provides power for the accessories through the accessory drive system. work conditions are closely related. On a gas turbine engine, there are many accessories that need to be driven by the gas turbine of the engine. The function of the accessory drive system is to transmit the shaft power of the turbine to each accessory and meet the requirements of each accessory for speed, steering and power. The accessory drive system generally includes an accessory drive case and an accessory drive mechanism. The accessory casing is directly installed on the engine, and the accessory transmission mechanism is inside the accessory casing, which includes a cylindrical gear train and various forms of clutches. Centrally installed on the special accessory casing, driven by the high-pressure rotor.

Use the first drive motor 21 to drive the low-pressure rotor of the aero-engine, remove the fairing at the front end of the compressor, and then connect the low-pressure rotor system 11 and the first drive motor 21 through the first coupling 6 to drive the rotation of the low-pressure rotor , the operating speed of the low-pressure rotor is 300r/min; the second drive motor 22 drives the high-voltage rotor to rotate, and the second drive motor 22 is used to replace the starter motor in the accessory transmission system in the aeroengine to drive the high-voltage rotor system 12, and the work of the high-voltage rotor The speed is 1500r/min; the speed and start-stop of the two drive motors are controlled by frequency converters.

A safety protection device 3 for safety protection is installed on the outside of the aero-engine to prevent the rotating parts from accidentally flying off and injuring the test personnel, so as to ensure the safety of the test personnel and the safety of the test equipment. The safety protection device 3 is provided with a detection device and a locking device. The detection device is used to detect the operation of the safety protection device 3. The signal output end of the detection device is connected to the signal input end of the control system, and the signal output end of the control system is connected to the locking device. The signal input terminal of the device, the locking device is used for emergency stop or locking all buttons on the hardware and software. Once the safety protection device 3 is not ready, the test will be stopped immediately, and all control buttons of the hardware and software will be locked, and at the same time, a "safety protection device is not ready" prompt will be displayed on the display until the safety protection device 3 is reliable and ready. In addition, the opening of the safety protection device 3 and the spindle are controlled by the control system, and the safety protection device 3 can only be opened when the spindle speed is lower than the set speed safety value.

The acquisition part mainly monitors the platform and test conditions in real time, such as working status monitoring, test data collection, etc., real-time display through the monitor, and exchange data with the control part to ensure the safety of the test. The main sensors in the data acquisition process include a three-way vibration acceleration sensor 9 and a capacitive displacement sensor 8. The main installation positions of the sensors are the output shaft of the first drive motor 21, the connecting shaft of the inner rotor of the aeroengine, and the connecting shaft of the outer rotor. The displacement sensor 8 is used to measure the axial runout and radial runout of the rotating shaft; in the 2-3 stage casing II, the 6th stage casing V, the combustion chamber casing VI and the high pressure turbine corresponding to the 5 support bearings of the aero-engine There is a three-way vibration acceleration sensor 9 on the box VII, which is used to measure its vibration; the data collected by each sensor can be monitored by each sensor in the working state, and the tolerance can be set. Once the tolerance is exceeded, the system will automatically start the buzzer to give an alarm, and Make a corresponding display on the software.

By collecting, analyzing and processing the experimental data, it is possible to have a good understanding of the actual operation of the engine, which facilitates a more comprehensive analysis of the key components in the engine and the vibration of the whole machine, and provides a comprehensive overview of the vibration evolution mechanism, vibration control and state. Monitoring provides excellent experimental conditions.

Working principle: the power output by the first driving motor 21 drives the rotation of the low-pressure rotor system 11 through the first coupling 6, and the rotation of the low-pressure rotor system 11 drives the rotation of the low-pressure compressor and the low-pressure turbine. The second driving motor 22 drives the rotation of the high-pressure rotor system 12 through the second coupling 7 and two pairs of spiral bevel gears in the casing transmission accessories, thereby driving the rotation of the high-pressure compressor and the high-pressure turbine.

Embodiment 1. Research on the vibration characteristics of high-pressure rotors of aero-engines:

Start the second driving motor 22, the power output by the second driving motor 22 is transmitted to the high-pressure rotor through the transmission system near the output shaft and the second coupling 7 aero-engine, thereby driving the rotation of the high-pressure rotor system 12, simulating the high-pressure rotor of the aero-engine Operation; by the capacitive displacement sensor 8 installed on the second drive motor 22 output shaft and the connecting shaft of the outer rotor of the aeroengine, it is used to measure the axial runout and radial runout of the rotating shaft. The three-way acceleration sensors on casing II, stage 6 casing V, combustion chamber casing VI and high-pressure turbine casing VII collect vibration acceleration signals, and connect the sensor output lines to the data acquisition system, which converts the collected signals into digital After receiving the signal, the data is transmitted to the computer data acquisition software through the network cable. By analyzing the collected signal, the vibration characteristics of the high-voltage rotor can be analyzed and the vibration control strategy can be studied.

Embodiment 2. Research on the vibration characteristics of the low-pressure rotor of an aero-engine:

Start the first drive motor 21, the power output by the first drive motor 21 is transmitted to the low-pressure rotor system 11 through the output shaft and the first coupling 6, thereby driving the low-pressure rotor system 11 to rotate, simulating the operation of the low-pressure rotor of an aeroengine, and the low-pressure rotor The operating speed is 300r/min; the capacitive displacement sensor 8 installed on the output shaft of the first drive motor 21 and the connecting shaft of the inner rotor of the aeroengine is used to measure the axial runout and radial runout of the rotating shaft; The three-way acceleration sensors on the 2-3 stage casing II, the 6 stage casing V, the combustion chamber casing VI and the high-pressure turbine casing VII corresponding to the 5 support bearings collect vibration acceleration signals, and connect the sensor output line to the data acquisition After the data acquisition system converts the collected signals into digital signals, the data is transmitted to the computer data acquisition software through the network cable. By analyzing the collected signals, the vibration characteristics of the low-pressure rotor can be analyzed and the vibration control strategy can be studied.

Embodiment 3. Research on the vibration characteristics of the whole aircraft engine:

Start the first and second motors at the same time, and the two motors rotate forward synchronously to simulate the operation of the dual-rotor system of the aero-engine; the speed of the low-pressure rotor is 0-300r/min, and the speed of the high-pressure rotor is 0-1500r/min A capacitive displacement sensor 8 on the output shaft of the driving motor 21, the connecting shaft of the inner rotor of the aeroengine and the connecting shaft of the outer rotor is used to measure the axial runout and radial runout of the rotating shaft; The three-way acceleration sensors on the 2-3 stage casing II, the 6 stage casing V, the combustion chamber casing VI and the high-pressure turbine casing VII collect vibration acceleration signals; connect the sensor output line to the data acquisition system, and the data acquisition system will After the collected signal is converted into a digital signal, the data is transmitted to the computer data acquisition software through the network cable. By analyzing the collected signal, the vibration characteristics of the aero-engine machine can be analyzed and the vibration control strategy can be studied.

Embodiment 4, the modal analysis of aero-engine key components:

Apply the modal test system to test the key parts of the aero-engine, install the three-way acceleration sensor on the part to be modal test, collect the vibration acceleration signal, connect the sensor output line to the data acquisition system, and pass the application modal test The modal test module (MTC Hammer) in the system collects data and the built-in analysis module (Modal analysis) processes and analyzes the data to obtain the natural frequency and mode shape of the key components of the aero-engine.

Embodiment 5, modal analysis of aero-engine complete machine:

The modal test software is used to carry out the modal test on the whole machine of the aero-engine, which consists of the 2-3 stage casing II, the 6-stage casing V, the combustion chamber casing VI and the high-pressure turbine installed on the 5 support bearings of the aero-engine. The three-way acceleration sensor on the box VII collects vibration acceleration signals, connects the sensor output line to the data acquisition system, and uses the modal test module (MTC Hammer) in the modal test for data acquisition and its own analysis module (Modal analysis) The natural frequency and mode shape of the whole machine of the aero-engine can be obtained by processing and analyzing the data.

Claims (8)

1. a kind of aero-engine vibration control experiment platform, it is characterised in that：The experiment porch includes experiment sewing platform base（5）, And it is fixed on experiment sewing platform base（5）On aero-engine ontology（1）, drive system, TT＆C system and safety device （3）；First driving motor of the drive system（21）Through first shaft coupling（6）Impart power to aero-engine ontology （1）Low pressure rotor system（11）, the second driving motor of the drive system（22）Through second shaft coupling（7）And aeroplane engine Machine ontology（1）Accessory drive system impart power to aero-engine ontology（1）High pressure rotor system（12）, described One driving motor（21）And/or second driving motor（22）Motor output shaft and aero-engine low pressure rotor system （11）With high pressure rotor system（12）It is equipped with capacitive displacement transducer（8）, corresponding to 5 spring bearings of aero-engine 2 grades of casings, 3 grades of casings, 6 grades of casings, combustion box and high-pressure turbine casing are equipped with three-way vibration acceleration transducer （9）, in aero-engine ontology（1）Outside equipped with locking device be used for security protection safety device（3）.

2. according to a kind of aero-engine vibration control experiment platform described in claim 1, it is characterised in that：The aeroplane engine Machine ontology（1）To have removed the aero-engine of after-burner and jet pipe part.

3. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The experiment porch Aero-engine ontology（1）Supporting way be by four hitch points on casing（10）Suspension is mounted on experiment sewing platform base （5）On.

4. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：To the boat Empty engine body（1）1 grade of casing, 4 grades of casings, combustion box, burning Interior Layout, combustion outer case, heat screen, reinforcing Combustor diffuser outer wall carries out 1/8 cutting and forms observation window.

5. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The driving system First driving motor of system（21）By the radome fairing for compressor front end of dismantling, then pass through first shaft coupling（6）Connect low pressure Rotor-support-foundation system（11）To drive low pressure rotor；Second driving motor of the drive system（22）By replacing in aero-engine Startup motor in accessory drive system drives high pressure rotor system（12）.

6. a kind of aero-engine vibration control experiment platform according to claim 1, it is characterised in that：The observing and controlling system System includes motor controlling cabinet（41）, capacitive displacement transducer（8）, three-way vibration acceleration transducer（9）, data acquisition system System, PC machine and connecting line.

7. a kind of aero-engine vibration control experiment platform according to claim 6, it is characterised in that：The driving The first driving motor in system（21）And/or second driving motor（22）Start and stop and turn round by TT＆C system motor control Cabinet（41）Frequency control.

8. a kind of aero-engine vibration control experiment platform according to claim 6, it is characterised in that：The experiment porch Aero-engine ontology（1）It is set to safety device with drive system（3）It is interior, the motor controlling cabinet of TT＆C system（41） It is set to safety device（3）Outside.