CN112697414A - Circumferential pull rod rotor experiment system - Google Patents
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Abstract
The utility model provides a circumference pull rod rotor experimental system, this experimental system is including supporting base, driving motor, experiment rotor, generator, lubricating-oil tank, converter and data acquisition and processing system. The experimental rotor comprises an experimental rotor turbine shaft section and an experimental rotor compressor shaft section, and the two sections are connected through a coupler to form a detachable structure of the integral rotor. The invention has higher experimental flexibility and can research the rotor dynamics characteristics under different contact states; the intermediate coupling can be used for not only carrying out dynamic experiments on the whole rotor, but also carrying out component-level dynamic experiments on the rotor; the size and the proportion of the rotor and the wheel disc are reasonably designed, so that the gas turbine rotor can effectively work between second-order and third-order critical rotating speeds consistent with those of the actual gas turbine rotor, the defect that the third-order critical rotating speed cannot be measured due to the scaling effect of most experiment tables is overcome, and the gas turbine rotor disc simulation experiment device has important experiment and application values for simulating the operating characteristics of the rotor under different wheel disc contact states.
Description
Technical Field
The invention relates to the technical field of rotating machinery experiment systems, in particular to a circumferential pull rod rotor dynamic experiment system.
Background
Heavy duty gas turbines are widely used in the field of power generation. The circumferential pull rod rotor system is one of main rotor structure forms of the heavy-duty gas turbine, and the dynamic characteristics of the circumferential pull rod rotor system have important influence on the safety and the reliability of the whole heavy-duty gas turbine. Compared with an integrally welded rotor, the compressor wheel disc and the turbine wheel disc of the circumferential pull rod rotor system are pre-tightened through the circumferential pull rods, and additional contact rigidity is generated by the contact effect of contact interfaces of the circumferential pull rod rotor system, so that the natural frequency, the critical rotation speed and the vibration characteristic of the whole rotor are influenced. Therefore, experimental study of rotor system dynamics at the wheel disc contact interface is essential.
In recent years, as the application of heavy-duty gas turbines is becoming widespread, the dynamic characteristics, operational safety, and reliability of the tie rod rotor, which is an important rotating machine, are important. However, the research on heavy gas turbines in China is not mature, and complete design theory and experimental data are lacked. Therefore, the experimental study on the dynamic characteristics of the pull rod rotor can provide important experimental reference for the design, manufacture and safety evaluation of the rotor.
At present, a corresponding pull rod rotor experiment system is available in China, and can be used for experimental research of static and dynamic characteristics, but the existing experiment system still has the following defects: firstly, the existing part of pull rod rotor experiment tables are static experiment tables, dynamic experiments cannot be carried out, and the difference between the structural form of the rotor and the actual rotor is large; secondly, the existing partial pull rod rotor dynamic experiment table can only carry out dynamic experiments of a compressor wheel disc or a turbine wheel disc independently, and cannot carry out an integral rotor experiment comprising the compressor wheel disc and the turbine wheel disc; third, the rotating speed of the current pull rod rotor dynamic experiment table can only reach the second-order critical rotating speed, and the third-order critical rotating speed cannot be experimentally measured under the laboratory condition.
Disclosure of Invention
In order to solve the defects of the conventional pull rod rotor experiment table, the invention aims to provide a circumferential pull rod rotor experiment system, which can perform an integral rotor experiment comprising a compressor wheel disc and a turbine wheel disc, can perform a rotor static experiment and a rotor dynamic experiment, and can perform experimental measurement on the third-order critical rotation speed of a rotor, wherein the third-order critical rotation speed of the integral rotor is lower than the maximum rotation speed of the experiment system.
The technical scheme of the invention is as follows:
the utility model provides a circumference pull rod rotor experimental system, this experimental system is including supporting base, driving motor, experiment rotor, generator, lubricating-oil tank, converter and data acquisition and processing system, its characterized in that: the experimental rotor comprises an experimental rotor turbine shaft section and an experimental rotor compressor shaft section; one end of the experimental rotor turbine shaft section is connected with an output shaft of the driving motor sequentially through the first rolling bearing and the first elastic coupling; one end of the experimental rotor compressor shaft section is connected with the generator through a second rolling bearing and a second elastic coupler; the other ends of the experimental rotor turbine shaft section and the experimental rotor compressor shaft section are connected through an intermediate coupler to form a detachable structure of an integral rotor; after disassembly, the experimental rotor turbine shaft section or the experimental rotor compressor shaft section can be independently installed between the first rolling bearing and the second rolling bearing.
The invention discloses a circumferential pull rod rotor experiment system, which is characterized in that: the experimental rotor turbine shaft section comprises a turbine pull rod wheel disc set and a turbine shaft, the turbine shaft comprises a first turbine shaft and a second turbine shaft, and the turbine pull rod wheel disc set is installed and pre-tightened through a turbine wheel disc pull rod; the first turbine shaft is connected with the turbine pull rod wheel disc set through a first turbine shaft flange, and the second turbine shaft is connected with the turbine pull rod wheel disc set through a second turbine shaft flange.
The invention discloses a circumferential pull rod rotor experiment system, which is characterized in that: the experimental rotor compressor shaft section comprises a compressor wheel disc set without a pull rod, a compressor wheel disc set with a pull rod, a compressor wheel disc and a compressor shaft; the compressor wheel disc set without the pull rod, the compressor wheel disc set with the pull rod and the two-stage compressor wheel disc are arranged on the compressor shaft through the expansion sleeve. The compressor wheel disc comprises a first-stage compressor wheel disc and a second-stage compressor wheel disc; the compressor shafts include a first compressor shaft and a second compressor shaft; the compressor wheel set without the pull rod is arranged on the first compressor shaft through the expansion sleeve, and the compressor wheel set with the pull rod is pre-tightened through the compressor wheel plate pull rod; the first compressor shaft is connected with a compressor wheel disk set without a pull rod through a first compressor shaft flange plate; the second compressor shaft is connected with a compressor wheel disk set containing a pull rod through a second compressor shaft flange.
Further, the total length of the experimental rotor is 2.3-2.4m, the wheel discs of the compressors in the shaft section of the experimental rotor compressor are seventeen stages, four stages of the wheel discs of the compressors containing the pull rods are total, eleven stages of the wheel discs of the compressors without the pull rods are total, and two stages of the rest of the wheel discs of the compressors are total; the turbine pull rod wheel disc group in the experimental rotor turbine shaft section has four stages.
Further, the diameters of the gas compressor wheel disc in the experimental rotor gas compressor shaft section and the wheel disc in the turbine pull rod wheel disc group are respectively between 250 and 450mm, and the thicknesses of the gas compressor wheel disc and the wheel disc are respectively 10-30 mm; the compressor and turbine shafts are the same diameter and are in the range of 35-55 mm. The ratio of the diameter of the compressor shaft and the turbine shaft to the diameter of the corresponding wheel disc should be in the range of 1: 3-1: 10 is between; the ratio of the total mass of the experimental rotor to the mass of all individual discs should be between 50: 1-15: 1, and the third-order critical speed of the experimental rotor is controlled to be between 3000rpm and 5000 rpm.
The data acquisition and processing system comprises a disc type torquemeter for acquiring torque signals in the running process of a rotor, a first horizontal direction acceleration sensor and a second horizontal direction acceleration sensor for respectively acquiring horizontal vibration acceleration signals of a turbine and a gas compressor, a first vertical direction acceleration sensor and a first vertical direction acceleration sensor for respectively adopting vertical vibration acceleration signals of the turbine and the gas compressor, a displacement sensor for acquiring vibration displacement signals of the rotor and a photoelectric encoder for acquiring real-time rotating speed signals; the signal collected by the sensor is input to the signal conditioner through a signal line, conditioned by the signal conditioner and output to the signal collection card, and finally the signal is calculated, analyzed, displayed and stored by a real-time display computer system comprising data collection software.
The support base is provided with a T-shaped groove.
Compared with the prior art, the invention has the following advantages and prominent technical effects: the invention simultaneously comprises a compressor shaft section wheel disc set and a turbine shaft section wheel disc set, the overall structural form of the rotor is similar to the actual gas turbine rotor structure, and the defect that most rotors can only carry out static experiments of the overall rotor or dynamic experiments of part of the rotors is overcome; and the size and the proportion of the rotor and the wheel disc are reasonably designed, so that the gas turbine can effectively work between second-order and third-order critical rotating speeds consistent with those of the actual gas turbine rotor, and the defect that the third-order critical rotating speed cannot be measured due to the scaling effect of most experiment tables is overcome. The invention has higher experimental flexibility, and the rotor dynamics characteristics under different contact states can be researched by adjusting the pre-tightening force of the pull rod; the dynamic experiment of the whole rotor can be carried out through the intermediate coupling, and meanwhile, the component level experiment of the rotor can be carried out; the generator is arranged at the tail end of the rotor and controlled by the frequency converter, so that the load of the rotor experiment table can be flexibly adjusted.
In order to solve the defects or shortcomings of the conventional pull rod rotor experiment table, the rotor experiment system simultaneously comprises a compressor shaft section wheel disc set and a turbine shaft section wheel disc set. Meanwhile, the third-order critical rotating speed of the rotor is lower than the maximum rotating speed of the experimental system, and experimental measurement can be carried out on the third-order critical rotating speed of the rotor.
In a word, the dynamic characteristics of the compressor shaft section wheel disc set, the turbine shaft section wheel disc set and the whole rotor in the first three-order critical rotating speed can be effectively simulated, experimental data support can be provided for theoretical research of a pull rod rotor experiment table, experimental data reference can be provided for actual design and manufacture of the circumferential pull rod rotor of the heavy-duty gas turbine, and the method has important application value in the field of design and manufacture of the heavy-duty gas turbine.
Drawings
FIG. 1 is a schematic overall structure diagram of an embodiment of a circumferential tie-rod rotor experimental system.
Fig. 2 is a schematic structural diagram of an experimental rotor compressor shaft section.
FIG. 3 is a sectional view of the experimental rotor compressor shaft section configuration.
FIG. 4 is a schematic illustration of the construction of the experimental rotor shaft section.
FIG. 5 is a sectional view of the experimental rotor shaft section configuration.
In the figure: 1-a circumferential pull rod rotor experimental system; 2-driving the motor; 3-a flange plate; 4-disc torquemeter; 5-a first resilient coupling; 6-a first horizontal direction acceleration sensor; 7-experimental rotor turbine shaft section; 8-a turbine shaft; 8 a-a first turbine shaft; 8 b-a second turbine shaft; 9-a displacement sensor; 10-testing the shaft section of the rotor compressor; 11-compressor shaft; 11 a-a first compressor shaft; 11 b-a second compressor shaft; 12-a second horizontal direction acceleration sensor; 13-a photoelectric encoder; 14-a second resilient coupling; 15-a generator; 16-a support base; 17-a first rolling bearing; 18-a first vertical direction acceleration sensor; 19-intermediate coupling; 20-lubricating oil pipe; 21-frequency converter control line; 22-a second vertical direction acceleration sensor; 23-a second rolling bearing; 24-a lubricating oil tank; 25-a frequency converter; 26-sensor signal line; 27-a signal conditioner; 28-signal acquisition card; 29-a data acquisition and processing system; 30-compressor disk set without tie rod; 31-a first compressor shaft flange; 32-a compressor wheel disc pull rod; 33-a compressor pulley set with a pull rod; 34-a second compressor shaft flange; 35-a second stage compressor wheel disc; 36-a first stage compressor disk; 37-a first turbine shaft flange; 38-turbine wheel disc tie rod; 39-turbine disk set; 40-a second turbine shaft flange.
Detailed Description
The overall structure, the working principle and the working process of the circumferential pull rod rotor experimental system are described in detail with reference to the accompanying drawings.
Fig. 1 is a schematic view of an overall structure of an embodiment of a circumferential tie rod rotor experiment system, wherein the circumferential tie rod rotor experiment system 1 mainly comprises a supporting base 16, a driving motor 2, an experiment rotor, a generator 15, a lubricating oil tank 24, a frequency converter 25 and a data acquisition and processing system: the experimental rotor comprises an experimental rotor turbine shaft section 7 and an experimental rotor compressor shaft section 10; one end of the experimental rotor turbine shaft section is connected with an output shaft of the driving motor 2 through a first rolling bearing 17 and a first elastic coupling 5 in sequence; one end of the experimental rotor compressor shaft section 10 is connected with the generator 15 through a second rolling bearing 23 and a second elastic coupling 14; the other ends of the experimental rotor turbine shaft section 7 and the experimental rotor compressor shaft section 10 are connected through an intermediate coupling 19 to form an integral rotor detachable structure; after disassembly, the test rotor turbine shaft section 7 or the test rotor compressor shaft section 10 can be mounted separately between the first rolling bearing 17 and the second rolling bearing 23.
The data acquisition and processing system comprises a disc type torquemeter 4 for acquiring torque signals in the running process of a rotor, a first horizontal direction acceleration sensor 6 and a second horizontal direction acceleration sensor 12 for respectively acquiring horizontal vibration acceleration signals of a turbine and a gas compressor, a first vertical direction acceleration sensor 18 and a first vertical direction acceleration sensor 22 for respectively adopting vertical vibration acceleration signals of the turbine and the gas compressor, a displacement sensor 9 for acquiring vibration displacement signals of the rotor, a photoelectric encoder 13 for acquiring real-time rotating speed signals, a sensor signal line 26, a signal conditioner 27, a signal acquisition card 28 and a data acquisition and processing system 29.
The driving motor 2 carries out rotation speed control through the frequency converter 25, the driving motor 2 can provide constant rotation speed for the experimental rotor, the driving motor 2 is connected with the disc type torque meter 4 through the flange plate 3, and the disc type torque meter 4 can measure the torque in real time in the rotor operation process. The disc type torque meter 4 is connected with an experimental rotor turbine shaft section 7 through a first elastic coupling 5; the experimental rotor turbine shaft section 7 is connected with the compressor shaft section wheel disc group 10 through an intermediate coupling 19, and the intermediate coupling 19 is detachable, so that the turbine shaft section wheel disc group 7 and the experimental rotor compressor shaft section 10 can respectively perform independent static or dynamic experiments. The experimental rotor compressor shaft section 10 is connected with the generator 15 through a second elastic coupling 14. The generator 15 is used to provide load torque. The first rolling bearing 17 and the second rolling bearing 23 are used to support the integrated rotor composed of the experimental rotor turbine shaft section 7 and the experimental rotor compressor shaft section 10. The support base 16 provides support for the whole circumferential pull rod rotor experiment system, and a T-shaped groove is formed in the support base. The first horizontal direction acceleration sensor 6 and the first vertical direction acceleration sensor 18 are mounted on a bearing seat of the first rolling bearing 17, and are used for measuring vibration acceleration signals generated on the first rolling bearing. The second horizontal direction acceleration sensor 12 and the second vertical direction acceleration sensor 22 are mounted on a bearing seat of the second rolling bearing 23, and are used for measuring vibration acceleration signals generated on the first rolling bearing. A displacement sensor 9 is mounted near the turbine shaft 8 for measuring a displacement signal. The photoelectric encoder 13 is mounted between the second rolling bearing 23 and the second elastic coupling 14. The inverter control line 21 is used for transmitting an inverter control signal to control the driving motor 2 to output a constant rotation speed and to control the generator 15 to output a constant torque. The lubricating oil pipe 20 supplies lubricating oil to the first rolling bearing 17 and the second rolling bearing 23 through the lubricating oil tank 24 to lubricate the two bearings.
The sensor signal line 26 in the signal acquisition and data analysis system acquires the electrical signals output by the first horizontal acceleration sensor 6, the first vertical acceleration sensor 18, the second horizontal acceleration sensor 12, the second vertical acceleration sensor 22, the displacement sensor 9 and the photoelectric encoder 13, outputs the electrical signals to the signal conditioner 27, conditions the electrical signals acquired by the sensors by the signal conditioner and outputs the conditioned electrical signals to the signal acquisition card 28, the signal acquisition card 28 outputs the electrical signals to the data acquisition and processing system 29 including data acquisition software and real-time display, and the sensor signals are calculated, analyzed, displayed and stored by the computer system.
Fig. 2 and 3 are schematic structural diagrams of an experimental rotor compressor shaft section, where the experimental rotor compressor shaft section 10 includes a compressor wheel disk set 30 without a pull rod, a compressor wheel disk set 33 with a pull rod, other compressor wheel disks, and a compressor shaft 11; the compressor wheel set 30 without the tie rod, the compressor wheel set 33 with the tie rod and the two-stage compressor wheel are mounted on the compressor shaft through the expansion sleeves. The compressor wheel disc comprises a first-stage compressor wheel disc 36 and a second-stage compressor wheel disc 35; the compressor shaft 11 includes a first compressor shaft 11a and a second compressor shaft 11 b; the compressor disk set 30 without the tie rod is mounted on the first compressor shaft 11a through an expansion sleeve, and the compressor disk set 33 with the tie rod is pre-tightened through a compressor disk tie rod 32; the first compressor shaft 11a is connected to a compressor disk set 30 without tie rods via a first compressor shaft flange 31; the structure and the installation mode not only reduce the processing and manufacturing difficulty and are convenient to install and disassemble, but also enable the integral structure formed by the first compressor shaft 11a and the compressor wheel disk group 30 without the pull rod to have lower rigidity, thereby reducing the third-order critical rotating speed of the compressor shaft section wheel disk group and the whole pull rod rotor structure. The second compressor shaft 11b is connected with a compressor pulley set 33 containing a pull rod through a second compressor shaft flange 34; a first-stage compressor disk 36 and a second-stage compressor disk 35 are mounted on the second compressor shaft 11b through an expansion sleeve. A compressor wheel disc group 33 containing a pull rod in the compressor shaft section wheel disc group is installed and pre-tightened through a compressor wheel disc pull rod 32; the compressor wheel disk group 30 without the pull rod is installed on the first compressor shaft 11a through the expansion sleeve, the structure and the installation mode not only reduce the processing and manufacturing difficulty and facilitate installation and disassembly, but also enable the overall structure formed by the first compressor shaft 11a and the compressor wheel disk group 30 without the pull rod to have lower rigidity, and further reduce the third-order critical rotating speed of the compressor shaft section wheel disk group 10 and the whole pull rod rotor structure.
Fig. 4 and 5 are schematic structural views of experimental rotor shaft sections. The experimental rotor turbine shaft section 7 comprises a turbine wheel disc group 39 and a turbine shaft 8, the turbine shaft comprises a first turbine shaft 8a and a second turbine shaft 8b, and the turbine wheel disc group 39 is installed and pre-tightened through a turbine wheel disc pull rod 38; the first turbine shaft 8a is connected to a turbine tie rod disk set 39 via a first turbine shaft flange 37, and the second turbine shaft 8b is connected to the turbine tie rod disk set 39 via a second turbine shaft flange 40. The structure is similar to the compressor shaft segment wheel disc group, the connecting mode also reduces the processing and manufacturing difficulty of the shaft and the wheel disc, and the installation and the disassembly are convenient.
The total length of the experimental rotor is 2.3-2.4m, the wheel discs of the compressors in the shaft section 10 of the experimental rotor compressor are seventeen stages, four stages of the wheel discs of the compressors containing the pull rods are provided, eleven stages of the wheel discs of the compressors without the pull rods are provided, and two stages of the wheel discs of other compressors (the wheel disc 35 of the second stage compressor and the wheel disc 36 of the first stage compressor) are provided; the turbine pull rod wheel disc group in the experimental rotor turbine shaft section 7 has four stages. The diameters of the gas compressor wheel disc in the experimental rotor gas compressor shaft section 10 and the wheel disc in the turbine pull rod wheel disc group are respectively between 250 and 450mm, and the thicknesses are respectively between 10 and 30 mm; the compressor shaft 11 and the turbine shaft 8 are of the same diameter and are in the range of 35-55 mm. The ratio of the diameters of the compressor shaft 11 and the turbine shaft 8 to the corresponding diameters of the discs is in the range of 1: 3-1: 10 is between; the ratio of the total mass of the experimental rotor to the mass of all individual discs was 50: 1-15: 1, and the third-order critical speed of the experimental rotor is controlled to be between 3000rpm and 5000 rpm. Experimental research shows that the sizes of the rotor and the wheel disc and the proportional relation between the rotor and the wheel disc are reasonably controlled, so that the gas turbine can effectively work between second-order and third-order critical rotating speeds consistent with those of an actual gas turbine rotor, and the defect that the third-order critical rotating speed cannot be measured due to the scaling effect of most experimental tables is overcome.
The whole system of the invention works as follows: the frequency converter 25 controls the driving motor 2 to output a constant rotating speed, drives the integral rotor composed of the turbine shaft segment pulley disc group 7 and the compressor shaft segment pulley disc group 10 to rotate at the constant rotating speed, and drives the generator 15 to generate electricity. The generator 15 generates an alternating torque load by means of an alternating signal output by the frequency converter 25. The experiment on the influence of different disk contact surface states on the dynamic characteristics of the rotor can be realized by adjusting the mounting pretightening force of the compressor disk pull rod 32 or the turbine disk pull rod 38. By disassembling the intermediate coupling 19 and connecting the second turbine shaft 8b in the experimental rotor turbine shaft section 7 with the second elastic coupling 14, the dynamic experiment of the turbine shaft section wheel disc group can be independently performed. Similarly, the dynamic experiment of the wheel disc group of the experimental rotor compressor shaft section can be independently carried out by detaching the intermediate coupling 19 and connecting the first compressor shaft 11a in the experimental rotor compressor shaft section 10 with the first elastic coupling 5.
When carrying out the static experiment of the experimental rotor that comprises turbine shaft section rim plate group and compressor shaft section rim plate group, can independently dismantle the experimental rotor from the experimental system and come out, install flexible rope respectively at first turbine shaft 8a and second compressor shaft 11b and hoist and mount and utilize mode test equipment can carry out the static experiment.
Claims (9)
1. The utility model provides a circumference pull rod rotor experimental system, this experimental system is including supporting base (16), driving motor (2), experiment rotor, generator (15), lubricating-oil tank (24), converter (25) and data acquisition and processing system, its characterized in that: the experimental rotor comprises an experimental rotor turbine shaft section (7) and an experimental rotor compressor shaft section (10); one end of the experimental rotor turbine shaft section (7) is connected with an output shaft of the driving motor (2) through a first rolling bearing (17) and a first elastic coupling (5) in sequence; one end of the experimental rotor compressor shaft section (10) is connected with a generator (15) through a second rolling bearing (23) and a second elastic coupling (14); the other ends of the experimental rotor turbine shaft section (7) and the experimental rotor compressor shaft section (10) are connected through an intermediate coupling (19) to form a detachable structure of the integral rotor; after disassembly, the experimental rotor turbine shaft section (7) or the experimental rotor compressor shaft section (10) can be mounted between the first rolling bearing (17) and the second rolling bearing (23) separately.
2. The circumferential tie rod rotor experimental system of claim 1, wherein: the experimental rotor turbine shaft section (7) comprises a turbine pull rod wheel disc set (39) and a turbine shaft (8), the turbine shaft comprises a first turbine shaft (8a) and a second turbine shaft (8b), and the turbine pull rod wheel disc set (39) is installed and pre-tightened through a turbine wheel disc pull rod (38); the first turbine shaft (8a) is connected with the turbine pull rod wheel disc set (39) through a first turbine shaft flange (37), and the second turbine shaft (8b) is connected with the turbine pull rod wheel disc set (39) through a second turbine shaft flange (40).
3. The circumferential tie rod rotor experimental system of claim 1, wherein: the experimental rotor compressor shaft section (10) comprises a compressor wheel disc set (30) without a pull rod, a compressor wheel disc set (33) with a pull rod, a compressor wheel disc and a compressor shaft (11); the compressor wheel disc set (30) without the pull rod, the compressor wheel disc set (33) with the pull rod and the two-stage compressor wheel disc are arranged on the compressor shaft through the expansion sleeve.
4. The circumferential tie rod rotor experimental system of claim 3, wherein: the compressor wheel disc comprises a first-stage compressor wheel disc (36) and a second-stage compressor wheel disc (35); the compressor shaft (11) comprises a first compressor shaft (11a) and a second compressor shaft (11 b); the compressor wheel disc set (30) without the pull rod is arranged on the first compressor shaft (11a) through an expansion sleeve, and the compressor wheel disc set (33) with the pull rod is pre-tightened through a compressor wheel disc pull rod (32); the first compressor shaft (11a) is connected with a compressor wheel disk set (30) without a pull rod through a first compressor shaft flange (31); the second compressor shaft (11b) is connected to a compressor disk set (33) comprising a tie rod via a second compressor shaft flange (34).
5. A circumferential pull rod rotor experiment system according to any one of claims 1 to 4, wherein the total length of the experiment rotor is 2.3 to 2.4m, the total length of the compressor wheel discs in the compressor shaft section (10) of the experiment rotor is seventeen stages, the compressor wheel discs containing pull rods are four stages, the compressor wheel discs without pull rods are eleven stages, and the rest compressor wheel discs are two stages; the turbine pull rod wheel disc group in the experimental rotor turbine shaft section (7) has four stages in total.
6. The circumferential tie rod rotor experimental system of claim 5, wherein: the diameters of the gas compressor wheel disc in the experimental rotor gas compressor shaft section (10) and the wheel disc in the turbine pull rod wheel disc group are respectively between 250 and 450mm, and the thicknesses are respectively between 10 and 30 mm; the compressor shaft (11) and the turbine shaft (8) have the same diameter and are in the range of 35-55 mm.
7. The circumferential tie rod rotor experimental system of claim 6, wherein: the ratio of the diameter of the compressor shaft (11) and the turbine shaft (8) to the corresponding diameter of the wheel disc is 1: 3-1: 10 is between; the ratio of the total mass of the experimental rotor to the mass of all individual discs was 50: 1-15: 1, and the third-order critical speed of the experimental rotor is controlled to be between 3000rpm and 5000 rpm.
8. The circumferential tie rod rotor experimental system of claim 1, wherein: the data acquisition and processing system comprises a disc type torquemeter (4) for acquiring torque signals in the running process of a rotor, a first horizontal direction acceleration sensor (6) and a second horizontal direction acceleration sensor (12) for respectively acquiring horizontal vibration acceleration signals of a turbine and a gas compressor, a first vertical direction acceleration sensor (18) and a first vertical direction acceleration sensor (22) for respectively adopting vertical vibration acceleration signals of the turbine and the gas compressor, a displacement sensor (9) for acquiring vibration displacement signals of the rotor and a photoelectric encoder (13) for acquiring real-time rotating speed signals; the signal collected by the sensor is input to a signal conditioner (27) through a signal line (26), is conditioned by the signal conditioner and then is output to a signal acquisition card (28), and finally is calculated, analyzed, displayed and stored by a computer system (29) comprising data acquisition software and real-time display.
9. The circumferential tie rod rotor experiment system of claim 1, wherein the support base (16) is provided with a T-shaped groove.
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| CN113761800A (en) * | 2021-09-02 | 2021-12-07 | 哈尔滨工业大学 | Shafting dynamic parameter model scaling design method based on critical rotating speed correspondence |
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|---|---|---|---|---|
| CN113761800A (en) * | 2021-09-02 | 2021-12-07 | 哈尔滨工业大学 | Shafting dynamic parameter model scaling design method based on critical rotating speed correspondence |
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