CN102937104A - Turbine compressor test system - Google Patents
Turbine compressor test system Download PDFInfo
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- CN102937104A CN102937104A CN2012104224943A CN201210422494A CN102937104A CN 102937104 A CN102937104 A CN 102937104A CN 2012104224943 A CN2012104224943 A CN 2012104224943A CN 201210422494 A CN201210422494 A CN 201210422494A CN 102937104 A CN102937104 A CN 102937104A
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Abstract
The invention discloses a turbine compressor test system. The turbine compressor test system is characterized in that rotation output of a motor is driven to a turbine compressor main shaft of a turbine compressor through a transmission case and a torque sensor so as to form a test main engine, an air inlet disturbance unit, an exhaust disturbance unit, an airflow actuating device and a measure and control unit are respectively arranged aiming at the test main engine. The turbine compressor test system provided by the invention can test properties of the turbine compressor under various working conditions such as different air inlet condition saltations, air inlet distortion and exhaust conditional mutation, simulate the excitation of airflow to blades under different work conditions through an experimental method, and measure the parameters including stress and vibration frequency of the blades under situations with different excitation of airflow.
Description
Technical field
The invention belongs to the Compressor Technology field, be specifically related to a kind of turbocompressor test system and test method.
Background technique
Turbocompressor is the nucleus equipment in the essential industry fields such as petrochemical industry, metallurgy and Coal Chemical Industry, and its performance directly has influence on the performance and reliability of these large-scale plants.Tradition turbocompressor test system is usually for a certain steady working condition, in parameters such as the flow of standard turbocompressor test platform test turbocompressor under this operating mode, power, Suck and exhaust pressure, temperature, and with these parameters as estimating and the foundation of design compressor.
Along with former oil quality changes, the application of more and more new procesies etc., the Compressor Process parameter of the industrial fields such as refinery changes gradually aggravation, and this has proposed requirements at the higher level to characteristic and the reliability of turbocompressor under various sudden loads.The conventionally test system and method can not be measured the performance under the sudden load of compressor well.
Publication number is that the application for a patent for invention of CN 101251411A discloses a kind of natural frequency measuring device, carry out exciting by vibration exciter to measuring blade, by being installed in the natural frequency of the electric vortex sensor measuring blade on the blade, can not test compression machine stress performance on the blade under the sudden load.
Summary of the invention
The present invention is for avoiding the existing deficiency of above-mentioned prior art, provide a kind of turbocompressor test system and test method, in the hope of testing the performance of turbocompressor under the operating modes such as various inlet air conditions sudden changes, inlet distortion and exhaust conditions sudden change; Method is simulated different operating mode downstream to the excitation of blade by experiment, and the parameters such as stressed and vibration frequency of different air-flow excitation situation lower blades are measured; And by parts such as vacuum pump and valves test system being maintained under the lower pressure, the effect of strengthening flow exciting is obviously reduced the testing apparatus power consumption.
The present invention is that the technical solution problem adopts following technological scheme:
The characteristics of turbocompressor test system of the present invention are:
The rotation output of motor drives to the turbocompressor main shaft formation Test Host of turbocompressor through gearbox and torque sensor;
Suction port at described turbocompressor arranges air inlet disturbance unit, and described air inlet disturbance unit is to set gradually inlet pressure temperature transducer, air inlet disturbance device, flowmeter and suction valve at the air inlet pipeline from the turbocompressor suction port;
Relief opening at described turbocompressor arranges exhaust disturbance unit, described exhaust disturbance unit is to set gradually outlet pressure temperature transducer, outlet disturbance device, safety valve, main inlet control valve and outlet valve at the gas exhaust piping from the turbocompressor relief opening, be arranged in parallel the auxiliary adjustment valve at described main inlet control valve, between the entrance of the outlet in parallel of described main inlet control valve and auxiliary adjustment valve and outlet valve, connect a vacuum pump by regulating valve;
The air-flow exciting bank is set, is used for the jet-impingement that direction and speed is adjustable at the turbocompressor blade;
Measurement and control unit is set, record and preservation dependence test signal, described dependence test signal comprises the test signal of described torque sensor, inlet pressure temperature transducer, flowmeter and the output of outlet pressure temperature transducer.
The characteristics of turbocompressor test system of the present invention also are:
Described air inlet disturbance device is arranged on the import distortion device in the turbocompressor air inlet pipeline, and described import distortion device is radial distortion net, circumferential distortion net or entry guide vane; Described import distortion device is connected with the import gas holder by the air inlet adjustment valve.
Described outlet disturbance device is that fast-acting modulator valve is set in gas exhaust piping, is used for changing Compressor Discharge Pressure and pulsation rule.
Described air-flow exciting bank is to consist of at turbocompressor blade top nozzle by the air compressor that connects successively, safety valve, gas holder, excitation valve, air filter, control valve with direction and the adjustable jet-impingement of speed, at described turbocompressor blade strain transducer is set.
Compared with the prior art, beneficial effect of the present invention is embodied in:
1, the present invention is the method that adopts flow-induced vibration, the suffered different air-flows excitations in actual motion of the parameter simulation blades such as the frequency by adjusting flow-induced vibration, size and Orientation, measure the stressed and vibration frequency of blade under the air-flow excitation by strain transducer, be applicable to the measurement of the performance of turbocompressor under sudden load;
2, the present invention adopts gearbox to be connected with motor, makes the compressor in the test system reach high rotating speed, and state of runtime machine is closer to the compressor of actual motion;
3, the present invention adopts the parts such as vacuum pump and valve that test system is maintained under the lower pressure, in the effect of strengthening flow exciting, the power consumption of test system is obviously reduced;
4, the present invention adopts import disturbance device, outlet disturbance device and three kinds of conflicting modes of air-flow exciting bank, and these three kinds of conflicting modes can work alone and work simultaneously, with the performance of test turbocompressor under sudden load.
Description of drawings
Fig. 1 is turbocompressor test system schematic representation of the present invention;
Fig. 2 is intake and exhaust disturbance cell schematics among the present invention;
Fig. 3 is air-flow exciting unit schematic representation among the present invention;
Number in the figure: 1 motor; 2 gearboxes; 3 torque sensors; 4 air inlet disturbance devices; 5 inlet pressure temperature transducers; 6 air-flow exciting banks; 7 flowmeters; 8 suction valves; 9 vacuum pumps; 10 outlet valves; 11 regulating valves; 12 main inlet control valves; 13 auxiliary adjustment valves; 14 safety valves; 15 outlet disturbance devices; 16 measurement and control units; 17 outlet pressure temperature transducers; 18 turbocompressors; 41 gas holder; 42 air inlet adjustment valves; 43 imports distortion device; 61 control valves; 62 nozzles; 63 strain transducers; 151 fast-acting modulator valves; 181 bearings; 182 turbocompressor main shafts; 183 turbocompressor blades.
Embodiment
Referring to Fig. 1, the turbocompressor test system is set in the present embodiment:
The rotation output of motor 1 drives to the main shaft 182 formation Test Hosts of turbocompressor 18 through gearbox 2 and torque sensor 3.
Suction port at turbocompressor 18 arranges air inlet disturbance unit, and air inlet disturbance unit is to set gradually inlet pressure temperature transducer 5, air inlet disturbance device 4, flowmeter 7 and suction valve 8 at the air inlet pipeline from the turbocompressor suction port; Relief opening at turbocompressor 18 arranges exhaust disturbance unit, exhaust disturbance unit is to set gradually outlet pressure temperature transducer 17, outlet disturbance device 15, safety valve 14, main inlet control valve 12 and outlet valve 10 at the gas exhaust piping from the turbocompressor relief opening, be arranged in parallel auxiliary adjustment valve 13 at main inlet control valve 12, between the entrance of the outlet in parallel of main inlet control valve 12 and auxiliary adjustment valve 13 and outlet valve 10, connect vacuum pump 9 by regulating valve 11.
Air-flow exciting bank 6 is set, is used for the jet-impingement that direction and speed is adjustable at turbocompressor blade 183, at the turbocompressor blade strain transducer 63 is set;
Measurement and control unit 16 is set, record and preservation dependence test signal, the dependence test signal comprises the test signal of torque sensor 3, inlet pressure temperature transducer 5, flowmeter 7, outlet pressure temperature transducer 17 and strain transducer 63 outputs.
In the implementation, as shown in Figure 2, air inlet disturbance device 4 is arranged on the import distortion device 43 in the turbocompressor air inlet pipeline, and import distortion device (43) is radial distortion net, circumferential distortion net or entry guide vane; Import distortion device 43 is connected with import gas holder 41 by air inlet adjustment valve 42; Outlet disturbance device 15 is that fast-acting modulator valve 151 is set in gas exhaust piping, is used for changing Compressor Discharge Pressure and pulsation rule.
As shown in Figure 3, air-flow exciting bank 6 is to consist of at turbocompressor blade top nozzle 62 by the air compressor 67 that connects successively, safety valve 66, gas holder 65, excitation valve 64, air filter 63, control valve 61 with direction and the adjustable jet-impingement of speed.
During corresponding system arranges, carry out system's control by measurement and control unit 16, control unit 16 is measured the power of turbocompressor by torque sensor 3, measure inlet pressure and the temperature of turbocompressor by inlet pressure temperature transducer 5, measure exhaust pressure and the temperature of turbocompressor by outlet pressure temperature transducer sensor 17, measure the stressed of turbocompressor blade 183 by strain transducer 63, measure the actual tolerance of turbocompressor by flowmeter 7.
Intake condition disturbance device 4 is used for the parameter such as the intake temperature, pressure, ricing to turbocompressor and causes disturbance, and then measures the performance of turbocompressor 18 under the import disturbance by measurement and control unit.Measurement and control unit is by the pressure and temperature of the gas holder 41 interior gases in the control air inlet disturbance device 4, and the switch of control air inlet adjustment valve 42, can form disturbance to the inlet condition of turbocompressor.Such as: when the gas pressure in the gas holder 41 greater than the turbocompressor air inlet pipeline in during gas pressure, open air inlet adjustment valve 42, the suction pressure of turbocompressor can raise suddenly, thereby causes that working conditions of compressor changes; Gas temperature in the gas temperature in the gas holder 41 and compressor inleting pipe road is opened air inlet adjustment valve 42 and also can be formed change to the inlet temperature of turbocompressor not simultaneously.Import distortion device 43 by in the measurement and control unit control air inlet disturbance device 4 can change compressor air inlet ricing, and then changes compressor internal work process.
In the outlet disturbance device, aperture size and operating frequency by measurement and control unit control fast-acting modulator valve 151 can cause to the exhaust pressure of turbocompressor specific disturbance, thus the performance of simulation test turbocompressor 18 when outlet parameter changes.
In the air-flow exciting bank 6, high pressure draught sprays on the turbocompressor blade through nozzle 62, the jet velocity and the direction that change air-flow encourage with simulation turbocompressor impeller 183 suffered gas in practical work process, can be so that various air-flows excitation the stressed of lower blade are measured by the strain transducer 63 that is pasted on the turbocompressor blade.
In actual test process, reduce the aperture of suction valve 8, thereby reduce the inlet pressure of turbocompressor.Because the no minimum of test cell is 1 barometric pressure, be external pressure, can move being lower than under the external pressure in order to make test system, can pass through throttle down 10, open the method for regulating valve 11 and startup vacuum pump 9, make the actual exhaust air pressure of compressor be lower than external pressure.This moment, the power consumption of compressor can obviously descend, thus the operating cost of saving test system.And the performance of compressor under hyperbaric environment can be calculated by the data analysis that records this moment.
Air inlet disturbance device 4, outlet disturbance device 15 and air-flow exciting bank 6 can work independently or co-operation, to test the performance of the turbocompressor 18 under the different disturbances.
Claims (4)
1. turbocompressor test system is characterized in that:
The rotation output of motor (1) drives to turbocompressor main shaft (182) the formation Test Host of turbocompressor (18) through gearbox (2) and torque sensor (3);
Suction port at described turbocompressor (18) arranges air inlet disturbance unit, and described air inlet disturbance unit is to set gradually inlet pressure temperature transducer (5), air inlet disturbance device (4), flowmeter (7) and suction valve (8) at the air inlet pipeline from the turbocompressor suction port;
Relief opening at described turbocompressor (18) arranges exhaust disturbance unit, described exhaust disturbance unit is to set gradually outlet pressure temperature transducer (17) at the gas exhaust piping from the turbocompressor relief opening, outlet disturbance device (15), safety valve (14), main inlet control valve (12) and outlet valve (10), be arranged in parallel auxiliary adjustment valve (13) at described main inlet control valve (12), between the entrance of the outlet in parallel of described main inlet control valve (12) and auxiliary adjustment valve (13) and outlet valve (10), connect a vacuum pump (9) by regulating valve (11);
Air-flow exciting bank (6) is set, is used for the jet-impingement that direction and speed is adjustable in turbocompressor blade (183), at described turbocompressor blade strain transducer (63) is set;
Measurement and control unit (16) is set, record and preservation dependence test signal, described dependence test signal comprises the test signal of described torque sensor (3), inlet pressure temperature transducer (5), flowmeter (7), outlet pressure temperature transducer (17) and strain transducer (63) output.
2. according to right 1 described turbocompressor test system, it is characterized in that: described air inlet disturbance device (4) is arranged on the import distortion device (43) in the turbocompressor air inlet pipeline, and described import distortion device (43) is radial distortion net, circumferential distortion net or entry guide vane; Described import distortion device (43) is connected with import gas holder (41) by air inlet adjustment valve (42).
3. according to right 1 described turbocompressor test system, it is characterized in that: described outlet disturbance device (15) is that fast-acting modulator valve (151) is set in gas exhaust piping, is used for changing Compressor Discharge Pressure and pulsation rule.
4. according to right 1 described turbocompressor test system, it is characterized in that: described air-flow exciting bank (6) is to consist of at turbocompressor blade top nozzle (62) by the air compressor (67) that connects successively, safety valve (66), gas holder (65), excitation valve (64), air filter (63), control valve (61) with direction and the adjustable jet-impingement of speed.
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012104224943A CN102937104A (en) | 2012-10-30 | 2012-10-30 | Turbine compressor test system |
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| CN2012104224943A CN102937104A (en) | 2012-10-30 | 2012-10-30 | Turbine compressor test system |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034377A (en) * | 2014-06-17 | 2014-09-10 | 西安交通大学 | Air compressor flow measurement device and calibration system and method thereof |
| CN105952688A (en) * | 2016-06-06 | 2016-09-21 | 合肥通用机械研究院 | System for suppressing forced vibration of centrifugal impeller and control method for system |
| CN106762772A (en) * | 2017-02-17 | 2017-05-31 | 株洲联诚集团有限责任公司 | A kind of real-time measurement apparatus of blower fan torque |
| CN106940558A (en) * | 2017-02-24 | 2017-07-11 | 武汉理工大学 | Electric automobile electric air-conditioning compressor controller development platform |
| CN108331757A (en) * | 2018-02-11 | 2018-07-27 | 好米动力设备有限公司 | A kind of performance test experiment table for single screw compressor |
| CN108953204A (en) * | 2018-06-26 | 2018-12-07 | 沈阳透平机械股份有限公司 | Pipeline compressor performance test method and system |
| CN109707636A (en) * | 2019-03-14 | 2019-05-03 | 扬州大学 | A kind of novel inlet distortions flow field axial-flow pump experimental provision |
| CN110793801A (en) * | 2019-11-28 | 2020-02-14 | 中国科学院工程热物理研究所 | Hybrid indirect cooling compressor experiment system |
| CN111007885A (en) * | 2018-10-05 | 2020-04-14 | 株式会社岛津制作所 | Estimation device and valve control device |
| CN113339309A (en) * | 2021-07-14 | 2021-09-03 | 上海燃料电池汽车动力系统有限公司 | Fuel cell air compressor testing system and method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060037316A1 (en) * | 2004-08-20 | 2006-02-23 | Richey Marlyn J | System and method for testing a rotary flow device |
| CN1854703A (en) * | 2005-04-28 | 2006-11-01 | 财团法人工业技术研究院 | Rotary fluid mechanical performance tester |
| CN101251411A (en) * | 2008-03-14 | 2008-08-27 | 西安交通大学 | Apparatus for measuring impeller blade |
| CN201363294Y (en) * | 2009-01-12 | 2009-12-16 | 珠海格力电器股份有限公司 | Compressor performance testing system |
| US20100116044A1 (en) * | 2007-04-30 | 2010-05-13 | Nicola Mitaritonna | Method and system for turbine blade characterization |
-
2012
- 2012-10-30 CN CN2012104224943A patent/CN102937104A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060037316A1 (en) * | 2004-08-20 | 2006-02-23 | Richey Marlyn J | System and method for testing a rotary flow device |
| CN1854703A (en) * | 2005-04-28 | 2006-11-01 | 财团法人工业技术研究院 | Rotary fluid mechanical performance tester |
| US20100116044A1 (en) * | 2007-04-30 | 2010-05-13 | Nicola Mitaritonna | Method and system for turbine blade characterization |
| CN101251411A (en) * | 2008-03-14 | 2008-08-27 | 西安交通大学 | Apparatus for measuring impeller blade |
| CN201363294Y (en) * | 2009-01-12 | 2009-12-16 | 珠海格力电器股份有限公司 | Compressor performance testing system |
Non-Patent Citations (2)
| Title |
|---|
| 徐道春等: "螺杆式空气压缩机性能测试系统设计", 《机械设计与制造》 * |
| 陈宏斌: "汽车空压机全性能试验台", 《汽车技术》 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104034377A (en) * | 2014-06-17 | 2014-09-10 | 西安交通大学 | Air compressor flow measurement device and calibration system and method thereof |
| CN105952688B (en) * | 2016-06-06 | 2019-04-09 | 合肥通用机械研究院有限公司 | A kind of centrifugal impeller forced vibration inhibits system and its control method |
| CN105952688A (en) * | 2016-06-06 | 2016-09-21 | 合肥通用机械研究院 | System for suppressing forced vibration of centrifugal impeller and control method for system |
| CN106762772A (en) * | 2017-02-17 | 2017-05-31 | 株洲联诚集团有限责任公司 | A kind of real-time measurement apparatus of blower fan torque |
| CN106940558A (en) * | 2017-02-24 | 2017-07-11 | 武汉理工大学 | Electric automobile electric air-conditioning compressor controller development platform |
| CN108331757A (en) * | 2018-02-11 | 2018-07-27 | 好米动力设备有限公司 | A kind of performance test experiment table for single screw compressor |
| CN108953204A (en) * | 2018-06-26 | 2018-12-07 | 沈阳透平机械股份有限公司 | Pipeline compressor performance test method and system |
| CN111007885A (en) * | 2018-10-05 | 2020-04-14 | 株式会社岛津制作所 | Estimation device and valve control device |
| CN111007885B (en) * | 2018-10-05 | 2023-05-02 | 株式会社岛津制作所 | Estimation device and valve control device |
| CN109707636A (en) * | 2019-03-14 | 2019-05-03 | 扬州大学 | A kind of novel inlet distortions flow field axial-flow pump experimental provision |
| CN109707636B (en) * | 2019-03-14 | 2023-10-24 | 扬州大学 | Novel inlet distortion flow field axial flow pump experiment device |
| CN110793801A (en) * | 2019-11-28 | 2020-02-14 | 中国科学院工程热物理研究所 | Hybrid indirect cooling compressor experiment system |
| CN110793801B (en) * | 2019-11-28 | 2021-07-30 | 中国科学院工程热物理研究所 | Hybrid indirect cooling compressor experiment system |
| CN113339309A (en) * | 2021-07-14 | 2021-09-03 | 上海燃料电池汽车动力系统有限公司 | Fuel cell air compressor testing system and method |
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Application publication date: 20130220 |