CN112414657A - Electromagnetic excitation device for gas turbine compressor blade vibration measurement - Google Patents
Electromagnetic excitation device for gas turbine compressor blade vibration measurement Download PDFInfo
- Publication number
- CN112414657A CN112414657A CN202011325648.8A CN202011325648A CN112414657A CN 112414657 A CN112414657 A CN 112414657A CN 202011325648 A CN202011325648 A CN 202011325648A CN 112414657 A CN112414657 A CN 112414657A
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- gas turbine
- blade
- vibration
- compressor blade
- electromagnetic
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- 230000005284 excitation Effects 0.000 title claims abstract description 27
- 238000005259 measurement Methods 0.000 title claims description 14
- 238000004804 winding Methods 0.000 claims description 7
- 235000013871 bee wax Nutrition 0.000 claims description 3
- 239000012166 beeswax Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 239000000853 adhesive Substances 0.000 claims 1
- 230000001070 adhesive effect Effects 0.000 claims 1
- 125000006850 spacer group Chemical group 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 8
- 238000009434 installation Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 239000011253 protective coating Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/022—Vibration control arrangements, e.g. for generating random vibrations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses an electromagnetic excitation device for measuring vibration of a gas turbine compressor blade, which comprises a signal generator, a power amplifier, an electromagnet, a coil, a mounting box and a bracket. The signal generator is used for generating sine signals, the sine signals pass through the power amplifier and are transmitted to the electromagnetic vibration exciter, and exciting forces of various signals are applied to the blades of the air compressor. The invention solves the problems of additional mass, blade surface damage, difficult installation and the like caused by adopting a contact type excitation mode of the traditional blade, can meet the requirement of exciting the blade in the vibration test of the gas turbine compressor blade, and can adjust the amplitude of the exciting force.
Description
Technical Field
The invention relates to a gas turbine compressor blade vibration test device, in particular to an electromagnetic excitation device for gas turbine compressor blade vibration measurement.
Background
The vibration safety of the compressor blade of the gas turbine is realized. With the development of the design technology of the vibration and the structural strength of the blades of the gas turbine compressor and the continuous and deep research on the safety of the vibration of the blades, higher requirements are put forward on the accuracy of the vibration test work of the blades of the gas turbine compressor.
Vibration measurement of gas turbine compressor blades by using vibration exciters is generally divided into a connecting rod type or a push rod type, and both the two methods are in contact type vibration excitation. The connecting rod type vibration exciter needs to adopt a nut to connect and install the connecting rod and the blade, so that the installation is inconvenient, additional mass can be brought during vibration measurement, and the testing precision is influenced. The ejector rod type excitation can only generate ejection force in the direction, and cannot generate pulling force in the opposite direction, the ejector rod generates impact contact with the surface of the blade when applying excitation force to the blade, and the surface of the blade can be damaged when the excitation force is too large. In addition, when the surface of the gas turbine compressor blade is coated with a protective coating or the machining precision of the surface of the blade is high, the link-type and ejector-type excitation methods are not suitable.
Disclosure of Invention
The invention aims to provide an electromagnetic excitation device for measuring vibration of a gas turbine compressor blade, aiming at the defects of the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
an electromagnetic excitation device for measuring vibration of a gas turbine compressor blade comprises a signal generator, wherein the signal generator is connected with a power amplifier, the power amplifier is connected with an electromagnetic vibration exciter, the electromagnetic vibration exciter is arranged on an electromagnetic vibration exciter base, and the electromagnetic vibration exciter base is fixedly arranged on a support by adopting a fastener; the gas turbine compressor blade is fixed by a blade fixing device, and the blade body part of the compressor blade is provided with a vibration pickup which is connected with a vibration signal data acquisition system.
The invention is further improved in that the support is fixedly arranged on the base by adopting a fastening bolt.
The invention is further improved in that the bracket comprises a plurality of diagonal draw bars for reinforcing the bracket.
The invention is further improved in that the blade fixing device is fixedly installed on the base by adopting a fastening bolt.
The invention is further improved in that the electromagnetic vibration exciter comprises a mounting box, a U-shaped electromagnet fixedly and hermetically mounted in the mounting box, and a winding resistor wound on the U-shaped electromagnet, wherein the winding resistor is connected with the power amplifier.
The invention is further improved in that the blade fixing device is provided with a cushion block at the blade root of the compressor blade of the gas turbine.
The invention is further improved in that the blade root of the gas turbine compressor blade is screwed and fixed by a fastening bolt on a vertical plate of the blade fixing device.
The invention is further improved in that the vibration pickup device is arranged at the vibration pickup position of the compressor blade of the gas turbine by adopting beeswax, bonding glue or a magnet.
Compared with the prior art, the invention has the following technical effects:
the invention relates to an electromagnetic excitation device for measuring the vibration of a gas turbine compressor blade, which is suitable for the vibration test of the gas turbine compressor blade. The electromagnetic harmonic vibration exciter can select different types of electromagnetic vibration exciters according to the size of the blade and the exciting force, cannot damage the blade, and is convenient to install. The power amplifier can be used for adjusting the size of the electromagnetic harmonic exciting force, and is convenient for changing and controlling the size of the exciting force in the blade vibration testing process.
In conclusion, the electromagnetic excitation device for the vibration measurement of the gas turbine compressor blade solves the problems that the traditional blade adopts a contact excitation mode to bring additional mass, cause blade surface damage, difficult installation and the like, can meet the requirement of exciting the blade in the vibration test of the gas turbine compressor blade, and can adjust the amplitude of the exciting force.
Drawings
FIG. 1 is an overall schematic diagram of an electromagnetic excitation device for gas turbine compressor blade vibration measurement;
FIG. 2 is a circuit connection diagram of an electromagnetic exciter;
FIG. 3 is a schematic view of a gas turbine compressor blade fixture.
Description of reference numerals:
1. a signal generator; 2. a power amplifier; 3. an electromagnetic vibration exciter; 4. a base of an electromagnetic vibration exciter; 5. a support; 6. fastening a bolt; 7. a base; 8. a diagonal brace; 9. gas turbine compressor blades; 10. a blade fixing device; 11. a vibration pickup; 12. a vibration signal data acquisition system; 13. a U-shaped electromagnet; 14. winding a resistor; 15. mounting a box; 16. a compressor blade root; 17. cushion blocks; 18. a vertical plate.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, a signal generator 1 is connected with a power amplifier 2, the power amplifier 2 is connected with an electromagnetic vibration exciter 3, the electromagnetic vibration exciter 3 is mounted on an electromagnetic vibration exciter base 4, the electromagnetic vibration exciter base 4 is fixedly mounted on a bracket 5 by adopting a fastener, the bracket 5 is fixedly mounted on a foundation base 7 by adopting a fastening bolt 6, and the bracket comprises a plurality of diagonal ribs 8 for reinforcing the bracket 5; a gas turbine compressor blade 9 is fixed by a blade fixing device 10 and fixedly installed on a base 7 by fastening bolts, a vibration pickup 11 is arranged at the blade body part of the gas turbine compressor blade, and the vibration pickup 11 is connected with a vibration signal data acquisition system 12.
The vibration pickup device 11 can be arranged at the vibration pickup position of the compressor blade 9 of the gas turbine by adopting beeswax, bonding glue, a magnet and the like.
Referring to fig. 2, the electromagnetic vibration exciter 3 includes a U-shaped electromagnet 13, a winding resistor 14 wound on the U-shaped electromagnet 13, and the winding resistor 14 is fixedly enclosed in a mounting box 15, and is connected to the power amplifier 2.
Referring to fig. 3, the blade fixing device 10 is provided with a cushion block 17 at a blade root 16 of a compressor blade of a gas turbine, and the blade root is screwed and fixed on a vertical plate 18 by a fastening bolt.
For a further understanding of the invention, its operation will now be described.
When the vibration exciter works, various vibration exciting signals such as sine signals, saw teeth signals and the like are generated by the signal generator 1, and are transmitted to the electromagnetic vibration exciter 3 after passing through the power amplifier 2, the vibration exciting force is applied to the gas compressor blade 3 of the gas turbine, and the amplitude of the vibration exciting force can be changed by adjusting the amplification factor of the power amplifier. The invention solves the problems of additional mass, blade surface damage, difficult installation and the like caused by adopting a contact type excitation mode of the traditional blade, and can meet the excitation requirement on the blade in the vibration test of the gas turbine compressor blade.
Claims (8)
1. The electromagnetic excitation device for measuring the vibration of the gas turbine compressor blade is characterized by comprising a signal generator (1), wherein the signal generator (1) is connected with a power amplifier (2), the power amplifier (2) is connected with an electromagnetic vibration exciter (3), the electromagnetic vibration exciter (3) is arranged on an electromagnetic vibration exciter base (4), and the electromagnetic vibration exciter base (4) is fixedly arranged on a support (5) by adopting a fastener; a gas turbine compressor blade (9) is fixed by a blade fixing device (10), a vibration pickup (11) is arranged at the blade body part of the gas turbine compressor blade, and the vibration pickup (11) is connected with a vibration signal data acquisition system (12).
2. The electromagnetic excitation device for the vibration measurement of the compressor blade of the gas turbine as claimed in claim 1, characterized in that the support (5) is fixedly mounted on the base (7) by means of fastening bolts (6).
3. The electromagnetic excitation device for the vibration measurement of the gas turbine compressor blade according to claim 1, characterized in that the support comprises a plurality of diagonal braces (8) for reinforcing the support.
4. The electromagnetic excitation device for the vibration measurement of the blades of the gas turbine compressor as claimed in claim 1, characterized in that the blade fixing device (10) is fixedly mounted on the base (7) by fastening bolts.
5. The electromagnetic excitation device for the vibration measurement of the compressor blade of the gas turbine as claimed in claim 1, wherein the electromagnetic excitation device (3) comprises a mounting box (15), a U-shaped electromagnet (13) fixedly and hermetically mounted in the mounting box (15), and a winding resistor (14) wound on the U-shaped electromagnet (13), and the winding resistor (14) is connected with the power amplifier.
6. The electromagnetic excitation device for the vibration measurement of a gas turbine compressor blade according to claim 1, characterized in that the blade fastening device (10) is provided with a spacer (17) at the blade root (16) of the gas turbine compressor blade.
7. The electromagnetic excitation device for the vibration measurement of the compressor blade of the gas turbine engine according to claim 6, characterized in that the blade root (16) of the compressor blade of the gas turbine engine is fastened and fixed by fastening bolts on the vertical plate (18) of the blade fixing device (10).
8. The electromagnetic excitation device for the vibration measurement of the compressor blade of the gas turbine engine as claimed in claim 1, characterized in that the vibration pickup (11) is arranged at the vibration pickup position of the compressor blade (9) of the gas turbine engine by using beeswax, adhesive glue or a magnet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011325648.8A CN112414657A (en) | 2020-11-23 | 2020-11-23 | Electromagnetic excitation device for gas turbine compressor blade vibration measurement |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011325648.8A CN112414657A (en) | 2020-11-23 | 2020-11-23 | Electromagnetic excitation device for gas turbine compressor blade vibration measurement |
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| Publication Number | Publication Date |
|---|---|
| CN112414657A true CN112414657A (en) | 2021-02-26 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011325648.8A Pending CN112414657A (en) | 2020-11-23 | 2020-11-23 | Electromagnetic excitation device for gas turbine compressor blade vibration measurement |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113049236A (en) * | 2021-03-10 | 2021-06-29 | 华电电力科学研究院有限公司 | Blade frequency measurement device based on Internet of things identification technology |
| CN113432818A (en) * | 2021-06-25 | 2021-09-24 | 上海交通大学 | Programmable force-excited blade vibration testing device |
| CN113959664A (en) * | 2021-11-19 | 2022-01-21 | 华能国际电力股份有限公司 | Blade dynamic frequency remote measuring device using piezoelectric sheet |
| CN114166336A (en) * | 2021-12-02 | 2022-03-11 | 成都市鸿侠科技有限责任公司 | Intelligent airplane generator blade frequency measuring tool and machining process thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003098031A (en) * | 2001-09-25 | 2003-04-03 | Mitsubishi Heavy Ind Ltd | Excitation device |
| CN103353383A (en) * | 2013-07-31 | 2013-10-16 | 沈阳工程学院 | Experimental apparatus for testing vibration mode of simulated impeller of turbine |
| CN105258886A (en) * | 2015-10-22 | 2016-01-20 | 西安热工研究院有限公司 | Electromagnetic harmonic wave exciting device for high-speed rotating impeller |
| CN105699074A (en) * | 2016-04-01 | 2016-06-22 | 山东大学 | Fluid-structure interaction dynamic property testing device for blade-rotor system |
| CN205620096U (en) * | 2016-04-26 | 2016-10-05 | 沈阳工程学院 | Experimental apparatus is measured to detuning bladed disk system vibration characteristic |
| CN207248535U (en) * | 2017-08-30 | 2018-04-17 | 华能国际电力股份有限公司 | Gas turbine blade end wall heat transfer test system |
| CN213397563U (en) * | 2020-11-23 | 2021-06-08 | 华能国际电力股份有限公司 | Electromagnetic excitation device for gas turbine compressor blade vibration measurement |
-
2020
- 2020-11-23 CN CN202011325648.8A patent/CN112414657A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003098031A (en) * | 2001-09-25 | 2003-04-03 | Mitsubishi Heavy Ind Ltd | Excitation device |
| CN103353383A (en) * | 2013-07-31 | 2013-10-16 | 沈阳工程学院 | Experimental apparatus for testing vibration mode of simulated impeller of turbine |
| CN105258886A (en) * | 2015-10-22 | 2016-01-20 | 西安热工研究院有限公司 | Electromagnetic harmonic wave exciting device for high-speed rotating impeller |
| CN105699074A (en) * | 2016-04-01 | 2016-06-22 | 山东大学 | Fluid-structure interaction dynamic property testing device for blade-rotor system |
| CN205620096U (en) * | 2016-04-26 | 2016-10-05 | 沈阳工程学院 | Experimental apparatus is measured to detuning bladed disk system vibration characteristic |
| CN207248535U (en) * | 2017-08-30 | 2018-04-17 | 华能国际电力股份有限公司 | Gas turbine blade end wall heat transfer test system |
| CN213397563U (en) * | 2020-11-23 | 2021-06-08 | 华能国际电力股份有限公司 | Electromagnetic excitation device for gas turbine compressor blade vibration measurement |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113049236A (en) * | 2021-03-10 | 2021-06-29 | 华电电力科学研究院有限公司 | Blade frequency measurement device based on Internet of things identification technology |
| CN113432818A (en) * | 2021-06-25 | 2021-09-24 | 上海交通大学 | Programmable force-excited blade vibration testing device |
| CN113959664A (en) * | 2021-11-19 | 2022-01-21 | 华能国际电力股份有限公司 | Blade dynamic frequency remote measuring device using piezoelectric sheet |
| CN114166336A (en) * | 2021-12-02 | 2022-03-11 | 成都市鸿侠科技有限责任公司 | Intelligent airplane generator blade frequency measuring tool and machining process thereof |
| CN114166336B (en) * | 2021-12-02 | 2024-04-05 | 成都市鸿侠科技有限责任公司 | Intelligent aircraft generator blade frequency measurement tool and processing technology thereof |
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