CN201277910Y - Test parameter measurement system for aero engine - Google Patents
Test parameter measurement system for aero engine Download PDFInfo
- Publication number
- CN201277910Y CN201277910Y CNU200820218619XU CN200820218619U CN201277910Y CN 201277910 Y CN201277910 Y CN 201277910Y CN U200820218619X U CNU200820218619X U CN U200820218619XU CN 200820218619 U CN200820218619 U CN 200820218619U CN 201277910 Y CN201277910 Y CN 201277910Y
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Abstract
The utility model relates to an aeroengine test parameter measuring system which comprises a thrust transducer, a thrust meter, a vibration transducer, a vibration measurer, a temperature and pressure transmitter, a signal conditioner, a data collecting card, an industrial control computer, a configuration software test system, a performance computer, a display and a printer, wherein the thrust transducer is connected with the thrust meter which is connected with the industrial control computer, the vibration transducer is connected with the vibration measurer which is connected with the data collecting card, the temperature and pressure transmitter is connected with the signal conditioner which is connected with the data collecting card, the data colleting card is connected with the industrial control computer, the industrial control computer is respectively connected with the performance computer, the display and the printer, the configuration software test system is connected with the industrial control computer, and the data collecting card 7 adopts the PXI data collecting card. The utility model changes the traditional structure, improves the performance, and can be applied to the measurement of the engine test parameter.
Description
Technical field
The utility model relates to the mechano-electronic field, and a kind of measuring trial run parameter of aeroengine system is provided especially.
Background technology
The measurement of motivation test run parameter is to use sensor that physical quantitys such as the temperature of engine, pressure, rotating speed, vibration are measured, and converts suitable intermediate quantity to, as voltage or electric current, reproduces the process of engine parameter by instrument.Usually various sensors of employing and instrument are measured and are shown.Tens engine parameters of monitoring during test run need to be equipped with a plurality of test run personnel and divide the work to monitor manual record in the such measuring system of engine run.When carrying out the test run of engine transition state, needing test run personnel close coordination to cooperate just can finish, but error in dipping is still bigger. because the data of test run can not continuous recording, when carrying out engine performance analysis or fault analysis, because there are not continuous data to do support, can only take the method for repetition test run to reproduce fault.The function of physics instrument is fixed, can not flexible Application.
A kind of measuring trial run parameter of aeroengine of the utility model system, data acquisition is to obtain the process of object information by gathering dissimilar a plurality of variable data.Data acquisition system (DAS) need be used suitable sensor and hardware support kit, and will change transmission from the data that sensor obtains by corresponding software.The given figure extraction system is based on the PXI bussing technique, adopt modular design method, form by parts such as survey sensor, transmitter, signal conditioner, data collecting card, PXI cabinet, industrial computer, Network Transmission machines, can gather analog quantity, digital quantity, frequency quantity, switching values such as temperature, pressure, flows simultaneously, concrete structure as shown in Figure 1.
The utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art part, and a kind of measuring trial run parameter of aeroengine system is provided especially
The utility model provides a kind of measuring trial run parameter of aeroengine system, it is characterized in that: include thrust pickup 1, thrust meter 2, vibration transducer 3, vialog 4, temperature and pressure transmitter 5, signal conditioner 6, data collecting card 7, industrial control computer 8, configuration software test macro 9, performance computation machine 10, display 11, printer 12; Wherein thrust pickup 1 is connected with thrust meter 2, thrust meter 2 is connected with industrial control computer 8, vibration transducer 3 is connected with vialog 4, vialog 4 is connected with data collecting card 7, temperature and pressure transmitter 5 is connected with signal conditioner 6, signal conditioner 6 is connected with data collecting card 7, data collecting card 7 is connected with industrial control computer 8, industrial control computer 8 is connected with performance computation machine 10, display 11, printer 12 respectively, and configuration software test macro 9 is connected with industrial control computer 8.
Described measuring trial run parameter of aeroengine system, data collecting card 7 adopts the PXI data collecting cards.
Data acquisition is to obtain the process of object information by gathering dissimilar a plurality of variable data.Data acquisition system (DAS) need be used suitable sensor and hardware support kit, and will change transmission from the data that sensor obtains by corresponding software.The given figure extraction system is based on the PXI bussing technique, adopt modular design method, form by parts such as survey sensor, transmitter, signal conditioner, data collecting card, PXI cabinet, industrial computer, Network Transmission machines, can gather analog quantity, digital quantity, frequency quantity, switching values such as temperature, pressure, flows simultaneously, concrete structure as shown in Figure 1.Software systems are used the LabVIEW development platform, and in conjunction with the hardware product of NI company, the application program of customer requirements is satisfied in the exploitation of fast and high quality ground.
Advantage of the present utility model: can carry out engine performance analysis or fault analysis to the data continuous recording, and can design Virtual Instrument and function according to the needs of test assignment.
Description of drawings
Fig. 1 forms sketch for the number extraction system.
Embodiment
Present embodiment provides a kind of measuring trial run parameter of aeroengine system, includes thrust pickup 1, thrust meter 2, vibration transducer 3, vialog 4, temperature and pressure transmitter 5, signal conditioner 6, data collecting card 7, industrial control computer 8, configuration software test macro 9, performance computation machine 10, display 11, printer 12; Wherein thrust pickup 1 is connected with thrust meter 2, thrust meter 2 is connected with industrial control computer 8, vibration transducer 3 is connected with vialog 4, vialog 4 is connected with data collecting card 7, temperature and pressure transmitter 5 is connected with signal conditioner 6, signal conditioner 6 is connected with data collecting card 7, data collecting card 7 is connected with industrial control computer 8, industrial control computer 8 is connected with performance computation machine 10, display 11, printer 12 respectively, and configuration software test macro 9 is connected with industrial control computer 8.
The described measuring trial run parameter of aeroengine of present embodiment system, data collecting card 7 adopts the PXI data collecting card.
Claims (2)
1, a kind of measuring trial run parameter of aeroengine system is characterized in that: include thrust pickup (1), thrust meter (2), vibration transducer (3), vialog (4), temperature and pressure transmitter (5), signal conditioner (6), data collecting card (7), industrial control computer (8), configuration software test macro (9), performance computation machine (10), display (11), printer (12); Wherein thrust pickup (1) is connected with thrust meter (2), thrust meter (2) is connected with industrial control computer (8), vibration transducer (3) is connected with vialog (4), vialog (4) is connected with data collecting card (7), temperature and pressure transmitter (5) is connected with signal conditioner (6), signal conditioner (6) is connected with data collecting card (7), data collecting card (7) is connected with industrial control computer (8), industrial control computer (8) respectively with performance computation machine (10), display (11), printer (12) connects, and configuration software test macro (9) is connected with industrial control computer (8).
2, according to the described measuring trial run parameter of aeroengine of claim 1 system, it is characterized in that: data collecting card (7) adopts the PXI data collecting card.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200820218619XU CN201277910Y (en) | 2008-10-22 | 2008-10-22 | Test parameter measurement system for aero engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU200820218619XU CN201277910Y (en) | 2008-10-22 | 2008-10-22 | Test parameter measurement system for aero engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201277910Y true CN201277910Y (en) | 2009-07-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CNU200820218619XU Expired - Fee Related CN201277910Y (en) | 2008-10-22 | 2008-10-22 | Test parameter measurement system for aero engine |
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Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101738159B (en) * | 2009-12-04 | 2011-10-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for measuring diameter of nozzle of aircraft engine tail |
| CN102445346A (en) * | 2011-10-18 | 2012-05-09 | 中国民航大学 | Method and system for diagnosing faults of ignition system of aircraft engine by using waveform matching |
| CN102539163A (en) * | 2010-12-27 | 2012-07-04 | 贵州双阳飞机制造厂 | Aircraft engine detection device |
| CN102053017B (en) * | 2009-11-09 | 2013-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| CN102944426A (en) * | 2012-10-23 | 2013-02-27 | 贵州凯阳航空发动机有限公司 | Measurement and control system and method for test bed of X-type aero-engine |
| CN103148882A (en) * | 2013-01-09 | 2013-06-12 | 华东理工大学 | Composite indication method of physical parameter measured value |
| CN103471854A (en) * | 2013-09-26 | 2013-12-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine body vibration characteristic analysis method |
| CN103879565A (en) * | 2012-12-23 | 2014-06-25 | 中航贵州飞机有限责任公司 | Aircraft ground test-run parameter detection device |
| CN104819847A (en) * | 2015-04-20 | 2015-08-05 | 四川迈迪测控技术有限公司 | Miniature turbojet aero-engine ground measurement and control system |
| CN105486507A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Modularized fault elimination device and method for trial test of aeroengine |
| CN106525436A (en) * | 2016-09-09 | 2017-03-22 | 西安航天动力试验技术研究所 | Measuring system and method for centralized distributed parameters of engine test long range exhaust system |
| CN107367393A (en) * | 2017-08-08 | 2017-11-21 | 王光宗 | A kind of remote automobile detection and warning device |
| CN108061660A (en) * | 2017-10-23 | 2018-05-22 | 上海卫星工程研究所 | The in-orbit thrust real-time calibration method of satellite engine based on linearly coupled measurement |
| CN108507791A (en) * | 2018-04-08 | 2018-09-07 | 上海理工大学 | A kind of virtual running test platform interactive system |
| CN109085782A (en) * | 2018-08-17 | 2018-12-25 | 大连凌海华威科技服务有限责任公司 | Visualize aerodynamic parameter acquisition system |
| CN109357874A (en) * | 2018-11-27 | 2019-02-19 | 西安航天动力测控技术研究所 | A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand |
| CN109523856A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Test run person's training system and control method based on the emulation of aero-engine operating condition |
| CN114295387A (en) * | 2022-01-04 | 2022-04-08 | 中国人民解放军陆军装甲兵学院 | Real vehicle running parameter testing system for engine of tracked vehicle |
-
2008
- 2008-10-22 CN CNU200820218619XU patent/CN201277910Y/en not_active Expired - Fee Related
Cited By (23)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102053017B (en) * | 2009-11-09 | 2013-01-09 | 沈阳黎明航空发动机(集团)有限责任公司 | Method and system for testing air flow field of indoor engine test-bed |
| CN101738159B (en) * | 2009-12-04 | 2011-10-05 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for measuring diameter of nozzle of aircraft engine tail |
| CN102539163A (en) * | 2010-12-27 | 2012-07-04 | 贵州双阳飞机制造厂 | Aircraft engine detection device |
| CN102445346A (en) * | 2011-10-18 | 2012-05-09 | 中国民航大学 | Method and system for diagnosing faults of ignition system of aircraft engine by using waveform matching |
| CN102944426A (en) * | 2012-10-23 | 2013-02-27 | 贵州凯阳航空发动机有限公司 | Measurement and control system and method for test bed of X-type aero-engine |
| CN103879565A (en) * | 2012-12-23 | 2014-06-25 | 中航贵州飞机有限责任公司 | Aircraft ground test-run parameter detection device |
| CN103148882B (en) * | 2013-01-09 | 2018-01-09 | 华东理工大学 | A kind of composite indication method of physical parameter measured value |
| CN103148882A (en) * | 2013-01-09 | 2013-06-12 | 华东理工大学 | Composite indication method of physical parameter measured value |
| CN103471854A (en) * | 2013-09-26 | 2013-12-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine body vibration characteristic analysis method |
| CN103471854B (en) * | 2013-09-26 | 2016-04-06 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aeromotor complete machine oscillation characteristic analysis method |
| CN104819847B (en) * | 2015-04-20 | 2017-03-08 | 四川迈迪测控技术有限公司 | Aero-engine ground observing and controlling system is sprayed in a kind of miniature whirlpool |
| CN104819847A (en) * | 2015-04-20 | 2015-08-05 | 四川迈迪测控技术有限公司 | Miniature turbojet aero-engine ground measurement and control system |
| CN105486507A (en) * | 2015-11-23 | 2016-04-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Modularized fault elimination device and method for trial test of aeroengine |
| CN105486507B (en) * | 2015-11-23 | 2017-11-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Aeroengine test run modularization fault removal device and its troubleshooting methodology |
| CN106525436A (en) * | 2016-09-09 | 2017-03-22 | 西安航天动力试验技术研究所 | Measuring system and method for centralized distributed parameters of engine test long range exhaust system |
| CN106525436B (en) * | 2016-09-09 | 2019-10-18 | 西安航天动力试验技术研究所 | A kind of engine test long-range exhaust system collecting and distributing type parameter measurement system and method |
| CN107367393A (en) * | 2017-08-08 | 2017-11-21 | 王光宗 | A kind of remote automobile detection and warning device |
| CN108061660A (en) * | 2017-10-23 | 2018-05-22 | 上海卫星工程研究所 | The in-orbit thrust real-time calibration method of satellite engine based on linearly coupled measurement |
| CN108507791A (en) * | 2018-04-08 | 2018-09-07 | 上海理工大学 | A kind of virtual running test platform interactive system |
| CN109085782A (en) * | 2018-08-17 | 2018-12-25 | 大连凌海华威科技服务有限责任公司 | Visualize aerodynamic parameter acquisition system |
| CN109357874A (en) * | 2018-11-27 | 2019-02-19 | 西安航天动力测控技术研究所 | A kind of engine test parameter measurement system for solid propellant rocket ground whirling test stand |
| CN109523856A (en) * | 2018-11-29 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | Test run person's training system and control method based on the emulation of aero-engine operating condition |
| CN114295387A (en) * | 2022-01-04 | 2022-04-08 | 中国人民解放军陆军装甲兵学院 | Real vehicle running parameter testing system for engine of tracked vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090722 Termination date: 20131022 |