CN114167026A - Experimental device for turbine blade crack quantity online identification - Google Patents
Experimental device for turbine blade crack quantity online identification Download PDFInfo
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- CN114167026A CN114167026A CN202111393779.4A CN202111393779A CN114167026A CN 114167026 A CN114167026 A CN 114167026A CN 202111393779 A CN202111393779 A CN 202111393779A CN 114167026 A CN114167026 A CN 114167026A
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- 239000007789 gas Substances 0.000 description 4
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- 239000002131 composite material Substances 0.000 description 1
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- 238000003745 diagnosis Methods 0.000 description 1
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- G—PHYSICS
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- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
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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
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Abstract
The invention provides an experimental device for online identification of the number of cracks of a turbine blade, which comprises the following steps: firstly, a rotor-bearing-blade motion system is respectively composed of a driving motor, an elastic coupling, a rotor, a bearing, a blade disc, a blade and a speed measuring gear; the bearing seat and the base form a fixed supporting system; the photoelectric sensor, the magnetoelectric sensor, the displacement sensor, the data acquisition instrument and the upper computer form a test system. Then, the number of the blade cracks is adjusted according to a single variable principle, and the running state of the rotor under different numbers of the cracks is measured and observed. And finally, establishing a rotor system operation characteristic database corresponding to different crack numbers for online identification of the crack numbers. The method is based on the experimental principle of single variable, identifies the number of the blade cracks on line by testing and analyzing the dynamic characteristics of the complex rotor system, has the advantages of simple operation and definite physical mapping relation, and can accurately identify the number of the blade cracks in the complex rotor-bearing-blade system.
Description
Technical Field
The invention relates to the technical field of turbine fault diagnosis, in particular to an experimental device for online identification of the number of blade cracks.
Background
A turbine is a machine that converts energy contained in a fluid medium into mechanical work. The working conditions of the turbine are different from the media used, so the structure of the turbine is various, but the basic working principle is similar. The most important components of a turbine are the rotating elements, including the rotor and the impeller, which are mounted on the turbine shaft with blades arranged uniformly around the circumference. The high-strength composite material is one of main parts of an aeroengine, a gas turbine and a steam turbine, and has important economic value and national defense safety property. The working environment of the turbine is generally fuel gas or working medium gas under a high-temperature and high-pressure state, so that the turbine blade not only bears alternating stress caused by expansion of the working medium, but also bears the corrosive action of the working medium gas. Under the combined action of alternating stress load and corrosive gas, the turbine blade is very easy to generate fatigue cracks. The occurrence of cracks not only reduces the operating efficiency of the turbine, but also leads to significant safety hazards. Therefore, the safe operation of the unit can be ensured by finding the blade cracks as soon as possible, and the operation cost can be greatly reduced. However, due to the complex characteristics of the turbine set, the control variables are more, the logic relation is complex, and the fault mechanism of blade crack is not easy to discover. In addition, if a turbine unit is subjected to a destructive test of the blades, the whole unit is easily scrapped, and the experimental research cost is high. Therefore, it is necessary to simplify the turbine set and build an experimental bench with clear logical relations, which is used for researching the failure mechanism of the blade crack number and determining the influence of the blade crack number on the rotor dynamics.
Disclosure of Invention
The invention aims to solve the problem of online identification of the number of blade cracks by a rotor-bearing-blade system, and provides an experimental device for online identification of the number of blade cracks.
The purpose of the invention is realized as follows:
an experimental device for online identification of crack number of a turbine blade comprises a driving motor, an elastic coupling, a rotor, a bearing seat, a blade disc, a blade, a speed measuring gear, a base, a displacement sensor, an optical code band, a photoelectric sensor, a magnetic current sensor, a motor controller, a data acquisition instrument and an upper computer (PC); the blade is arranged on a blade disc which is fixed on a rotor, two ends of the rotor are supported by ball bearings, the blade, the rotor and the bearings form a rotor-blade-bearing system, the rotor is a slender shaft flexible rotor, the bearings are adjustable double-row ball bearings, and the blade disc is an adjustable pre-tightening force tightening blade disc. The system is driven to rotate by a driving motor, and the driving motor is connected with the system through an elastic coupling.
Further, the driving motor is a 1PH8107-1DF00-2BA1 type synchronous permanent magnet motor.
Further, the motor controller is a VFD25AMS43ANSAA type 11Kw constant torque frequency converter.
Furthermore, the elastic coupling is a high-rotating-speed diaphragm coupling.
Furthermore, the speed measuring fluted disc and the optical code belt are used for representing the instantaneous rotating speed of the rotor.
Further, the photoelectric sensor and the magnetoelectric sensor are used for measuring instantaneous rotating speed signals.
Further, the displacement sensor is used for measuring a displacement signal of the rotor.
Further, the data acquisition instrument and the upper computer are used for recording signals of the sensor.
Furthermore, the blade is a rectangular straight blade with adjustable crack number.
Compared with the prior art, the invention has the beneficial effects that:
according to the method, the number of the blade cracks is identified on line by adjusting the number of the blade cracks and measuring and observing the running state of a rotor system under different numbers of the cracks according to the principle of a single variable.
Drawings
FIG. 1 is a schematic view of an experimental device for online identification of the number of cracks in a turbine blade according to the present invention;
FIG. 2 is a schematic view of a turbine blade of the present invention illustrating the number of cracks being adjusted;
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
With reference to fig. 1, an experimental device for online identification of blade crack number includes a driving motor, an elastic coupling, a rotor, a bearing seat, a blade disc, a blade, a speed measuring gear, a base, a displacement sensor, an optical code band, a photoelectric sensor, a magnetic current sensor, a motor controller, a data acquisition instrument, and an upper computer (PC); the blades are arranged on a blade disc, the blade disc is fixed on a rotor, two ends of the rotor are supported by ball bearings, and the blades, the rotor and the bearings form a rotor-blade-bearing system. The system is driven to rotate by a driving motor, the driving motor is connected with the system through an elastic coupling, the elastic coupling is a high-rotating-speed diaphragm coupling, the driving motor is a 1PH8107-1DF00-2BA1 type synchronous permanent magnet motor, a motor controller is a VFD25AMS43ANSAA type 11Kw constant torque frequency converter, a speed-measuring fluted disc and an optical code band are used for representing the instantaneous rotating speed of a rotor, a photoelectric sensor and a magnetoelectric sensor are used for measuring instantaneous rotating speed signals, a displacement sensor is used for measuring displacement signals of the rotor, a data acquisition instrument and an upper computer are used for recording signals of the sensors, and the blades are rectangular straight blades with adjustable crack numbers.
Step 1: the driving motor and the two ball bearings are respectively fixed on corresponding bases, and the bases are fixedly connected with the ground;
step 2: the photoelectric sensor records the running state of the motor by measuring a pulse signal at the output end of the motor;
and step 3: the magnetoelectric sensor records the motion state of the rotor by measuring the pulse signal of the speed measuring gear;
and 4, step 4: the displacement sensor records the deflection state of the rotor by measuring a displacement signal of the rotor;
and 5: the data acquisition instrument and the upper computer can record and display data signals acquired by the sensor on line in real time, and judge the running state of the system by observing the amplitude of the signals;
step 6: with reference to fig. 2, the single variable is the number of cracks in the adjustment blade, and step 5 is repeated; and finally, respectively establishing rotor system operation characteristic databases corresponding to different crack numbers for online identification of the crack numbers.
Claims (9)
1. The utility model provides an experimental apparatus of online discernment of turbine blade crackle quantity which characterized by: the device comprises a driving motor, an elastic coupling, a rotor, a bearing seat, a blade disc, blades, a speed measuring gear, a base, a displacement sensor, an optical code band, a photoelectric sensor, a magnetic current sensor, a motor controller, a data acquisition instrument and an upper computer (PC); the blade is arranged on a blade disc which is fixed on a rotor, two ends of the rotor are supported by ball bearings, the blade, the rotor and the bearings form a rotor-blade-bearing system, the rotor is a slender shaft flexible rotor, the bearings are adjustable double-row ball bearings, and the blade disc is an adjustable pre-tightening force tightening blade disc. The system is driven to rotate by a driving motor, and the driving motor is connected with the system through an elastic coupling.
2. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the driving motor is a synchronous permanent magnet motor of 1PH8107-1DF00-2BA1 type.
3. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the motor controller is a VFD25AMS43ANSAA model 11Kw constant torque frequency converter.
4. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the elastic coupling is a high-speed diaphragm coupling.
5. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the speed measuring fluted disc and the optical code band are used for representing the instantaneous rotating speed of the rotor.
6. The experimental device for the on-line identification of the number of cracks on the turbine blade according to claim 1, wherein the photoelectric sensor and the magnetoelectric sensor are used for measuring instantaneous rotating speed signals.
7. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the displacement sensor is used for measuring a displacement signal of the rotor.
8. The experimental device for the on-line identification of the number of cracks on the turbine blade as claimed in claim 1, wherein the data acquisition instrument and the upper computer are used for recording signals of the sensors.
9. The experimental device for the on-line identification of the number of cracks of the turbine blade as claimed in claim 1, wherein the blade is a rectangular straight blade with an adjustable number of cracks.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111393779.4A CN114167026A (en) | 2021-11-23 | 2021-11-23 | Experimental device for turbine blade crack quantity online identification |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111393779.4A CN114167026A (en) | 2021-11-23 | 2021-11-23 | Experimental device for turbine blade crack quantity online identification |
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| CN114167026A true CN114167026A (en) | 2022-03-11 |
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| CN202111393779.4A Pending CN114167026A (en) | 2021-11-23 | 2021-11-23 | Experimental device for turbine blade crack quantity online identification |
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100030493A1 (en) * | 2007-02-02 | 2010-02-04 | The Secretary, Department Of Atomic Energy, Govt. Of India | Method for non-intrusive on-line detection of turbine blade condition |
| JP2013061224A (en) * | 2011-09-13 | 2013-04-04 | Toshiba Corp | Blade vibration measuring apparatus |
| CN103592365A (en) * | 2013-11-14 | 2014-02-19 | 西安交通大学 | Rapid rotor crack detection method |
| CN104267097A (en) * | 2014-09-15 | 2015-01-07 | 北京工业大学 | Determination method of fan blade crack position |
| CN104595112A (en) * | 2013-10-30 | 2015-05-06 | 通用电气公司 | Wind turbine and method for evaluating health status of blades thereon |
| CN108956075A (en) * | 2018-08-31 | 2018-12-07 | 天津大学 | Movable vane piece crackle inline diagnosis method |
| CN109541028A (en) * | 2018-12-26 | 2019-03-29 | 湖南科技大学 | A kind of pneumatic equipment bladess crack position position finding and detection method and system |
| JP2019100210A (en) * | 2017-11-29 | 2019-06-24 | 三菱日立パワーシステムズ株式会社 | Rotor blade monitoring system, rotor blade monitoring device, rotor blade monitoring method, program |
| CN110926771A (en) * | 2019-11-20 | 2020-03-27 | 佛山科学技术学院 | Blade crack region determination method based on modal curvature error method |
-
2021
- 2021-11-23 CN CN202111393779.4A patent/CN114167026A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100030493A1 (en) * | 2007-02-02 | 2010-02-04 | The Secretary, Department Of Atomic Energy, Govt. Of India | Method for non-intrusive on-line detection of turbine blade condition |
| JP2013061224A (en) * | 2011-09-13 | 2013-04-04 | Toshiba Corp | Blade vibration measuring apparatus |
| CN104595112A (en) * | 2013-10-30 | 2015-05-06 | 通用电气公司 | Wind turbine and method for evaluating health status of blades thereon |
| CN103592365A (en) * | 2013-11-14 | 2014-02-19 | 西安交通大学 | Rapid rotor crack detection method |
| CN104267097A (en) * | 2014-09-15 | 2015-01-07 | 北京工业大学 | Determination method of fan blade crack position |
| JP2019100210A (en) * | 2017-11-29 | 2019-06-24 | 三菱日立パワーシステムズ株式会社 | Rotor blade monitoring system, rotor blade monitoring device, rotor blade monitoring method, program |
| CN108956075A (en) * | 2018-08-31 | 2018-12-07 | 天津大学 | Movable vane piece crackle inline diagnosis method |
| CN109541028A (en) * | 2018-12-26 | 2019-03-29 | 湖南科技大学 | A kind of pneumatic equipment bladess crack position position finding and detection method and system |
| CN110926771A (en) * | 2019-11-20 | 2020-03-27 | 佛山科学技术学院 | Blade crack region determination method based on modal curvature error method |
Non-Patent Citations (2)
| Title |
|---|
| 吴琪强等: "基于固有频率的风力机叶片裂纹精确定位与程度识别", 《振动与冲击》 * |
| 王燕等: "矿用通风机叶片裂纹诊断方法的研究", 《同煤科技》 * |
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Application publication date: 20220311 |