CN112378998A - Engine blade natural frequency testing method - Google Patents
Engine blade natural frequency testing method Download PDFInfo
- Publication number
- CN112378998A CN112378998A CN202011155476.4A CN202011155476A CN112378998A CN 112378998 A CN112378998 A CN 112378998A CN 202011155476 A CN202011155476 A CN 202011155476A CN 112378998 A CN112378998 A CN 112378998A
- Authority
- CN
- China
- Prior art keywords
- natural frequency
- blade
- engine
- engine blade
- testing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 42
- 238000000034 method Methods 0.000 claims abstract description 22
- 230000005236 sound signal Effects 0.000 claims abstract description 8
- 239000006185 dispersion Substances 0.000 claims description 29
- 238000007405 data analysis Methods 0.000 claims description 6
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 238000000605 extraction Methods 0.000 claims description 3
- 238000001914 filtration Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 238000013480 data collection Methods 0.000 claims 1
- 238000005452 bending Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000010998 test method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/045—Analysing solids by imparting shocks to the workpiece and detecting the vibrations or the acoustic waves caused by the shocks
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/12—Analysing solids by measuring frequency or resonance of acoustic waves
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/01—Indexing codes associated with the measuring variable
- G01N2291/014—Resonance or resonant frequency
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/023—Solids
Landscapes
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Engines (AREA)
Abstract
The application relates to a method for testing the natural frequency of an engine blade, which belongs to the technical field of testing and comprises the following steps: clamping and knocking the engine blade; detecting a blade vibration sound signal and carrying out vibration sound data acquisition; and processing the vibration sound data to obtain the natural frequency of the blade. The method for testing the natural frequency of the engine blade has the advantages of high testing efficiency and high precision.
Description
Technical Field
The application relates to the technical field of testing, in particular to a method for testing natural frequency of an engine blade.
Background
After the aeroengine blade is manufactured, a natural frequency test is required before assembly, and a plurality of blades mounted on an engine are ensured not to resonate. At present, a frequency sweep method is generally adopted for testing the inherent frequency of the blade of the aero-engine, namely, a vibration source is given to the blade of the aero-engine, the vibration frequency of the vibration source is continuously adjusted until resonance occurs, and the frequency of the vibration source at the moment is the inherent frequency of the blade of the aero-engine.
In view of the above-mentioned related art, the inventor believes that the testing of the natural frequency of the engine blade by the frequency sweep method has the defect of low testing efficiency.
Disclosure of Invention
In order to solve the problem of low testing efficiency in the prior art that the natural frequency of the engine blade is tested by a frequency sweeping method, the application provides a method for testing the natural frequency of the engine blade.
The engine blade natural frequency testing method provided by the application adopts the following technical scheme:
a method for testing the natural frequency of an engine blade comprises the following steps:
step S1: clamping and knocking the engine blade;
step S2: detecting a blade vibration sound signal and carrying out vibration sound data acquisition;
step S3: and processing the vibration sound data to obtain the natural frequency of the blade.
Through adopting above-mentioned technical scheme, strike and gather blade vibration sound data to the blade, can obtain the natural frequency of blade after processing vibration sound data, improved the efficiency of blade natural frequency test.
Further, the vibration sound data processing is carried out by a data analysis processing device built based on LabVIEW.
By adopting the technical scheme, the blade vibration sound data can be automatically and efficiently processed so as to obtain the natural frequency of the blade.
Further, the vibration sound data processing process comprises the steps of data interception, filtering, fast fourier transform and natural frequency extraction which are sequentially performed.
Further, the method for testing the natural frequency of the engine blade further comprises the step S4: and calculating the natural frequency of a plurality of identical engine blades, and if the dispersion degree exceeds a limited range, adjusting the engine blades to ensure that the dispersion degree is within the limited range.
By adopting the technical scheme, the dispersion degree of the group of engine blades can be adjusted, so that the engine blades can quickly pass through a rotating speed area where resonance occurs, and the stable operation of the engine is ensured.
Further, the calculation formula of the dispersion degree is as follows:
dispersion = (maximum natural frequency-minimum natural frequency)/minimum natural frequency x 100%.
By adopting the technical scheme, the dispersion degree of the natural frequency of the engine blade can be calculated.
Further, the clamping force and the knocking force of the plurality of identical engine blades during testing are identical.
By adopting the technical scheme, the testing conditions of a plurality of engine blades in the same group are the same, and the influence of different clamping force and knocking force of the blades on the testing precision of the natural frequency is avoided.
Furthermore, the blade vibration sound signal is detected through a sound pressure sensor, and the vibration sound data is collected through a data acquisition card.
Through adopting above-mentioned technical scheme, can detect the sound signal of blade vibration and carry out data acquisition.
Further, the engine blade is clamped by a clamping device and knocked by a knocking device; the clamping device can rotate around a rotating shaft vertical to the horizontal plane so as to adjust the angle between the surface of the engine blade and the hammer head of the knocking device; the hammer head of the knocking device can be adjusted in position in the vertical direction to adapt to different blade heights.
Through adopting above-mentioned technical scheme, can adjust the position relation between blade and the tup, guarantee to strike the effect.
Further, the hammer head material of the knocking device is steel.
By adopting the technical scheme, the high-frequency vibration signal can be generated through knocking, and the accuracy of the natural frequency test of the blade is ensured.
In summary, the present application includes at least one of the following beneficial technical effects:
1. the method has the advantages that the sound data of the blade vibration are collected and processed by a data analysis processing device built based on LabVIEW to obtain the natural frequency of the blade vibration, so that the efficiency of testing the natural frequency of the blade is improved;
2. by calculating and adjusting the natural frequency dispersion degree of the plurality of blades, the blades can quickly pass through a rotating speed area where resonance occurs, and the engine can stably run.
Drawings
FIG. 1 is a block diagram of a testing process for a method of testing natural frequencies of an engine blade according to an embodiment of the present application;
FIG. 2 is a block diagram of a testing process of a method for testing the natural frequency of an engine blade according to another embodiment of the present application.
Detailed Description
The present application is described in further detail below with reference to figures 1-2.
Referring to fig. 1, the embodiment of the application discloses a method for testing natural frequency of an engine blade, which comprises the following steps:
step S1: clamping and knocking the engine blade;
step S2: detecting a blade vibration sound signal and carrying out vibration sound data acquisition;
step S3: and processing the vibration sound data to obtain the natural frequency of the blade.
In step S1, the mounting end of the engine blade is clamped and fixed by using a clamping device, and then the blade is knocked and vibrated by using an external knocking device. When a plurality of identical engine blades are tested, the positions, clamping force and knocking force of the identical blades on the clamp are the same, so that the consistency of test conditions is ensured, and the influence of the difference of the clamping force and the knocking force of the blades on the inherent frequency test precision is avoided. The clamping force may be adjusted by a torque wrench.
The clamping device can be bench clamp, a rotating shaft perpendicular to the horizontal plane can be arranged at the bottom end of the bench clamp, and the bench clamp can rotate around the rotating shaft to adjust the angle between the surface of the engine blade and the hammer head of the knocking device so as to ensure the knocking effect.
The knocking device comprises a hammer head which can be in a rod shape, the hammer head is connected with a push-pull rod of the push-pull electromagnet through a coupler, and the hammer head is driven by the push-pull electromagnet to knock the engine blade. The push-pull type electromagnet can be fixedly installed on the horizontal supporting plate, the supporting plate is sleeved on the three stand columns, the top ends of the three stand columns can be fixedly connected with the top plate, and the bottom ends of the three stand columns can be fixedly connected with the bottom plate. The support plate is matched with the upright post through a linear bearing with a clamping handle. Therefore, the support plate can drive the push-pull type electromagnet to move in the vertical direction, and when the push-pull type electromagnet is adjusted to a required position, the position can be fixed through the linear bearing with the clamping handle. Preferably, the material of the hammer head is steel, so as to ensure that a high-frequency signal can be excited. The structure of the bracket can be selected by the person skilled in the art according to the requirement, and the bracket structure can enable the push-pull type electromagnet to realize vertical movement.
The skilled person can also strike the blade with a hammer of the type known in the art.
When in knocking, the part of the engine blade close to the edge is preferably knocked so as to ensure that the blade vibrates well and improve the test effect.
In step S2, the blade vibration sound signal is detected by the sound pressure sensor and dynamically acquired by the data acquisition card. The sound pressure sensor is arranged close to the surface of the blade, the output end of the sound pressure sensor is connected with the input end of the data acquisition card, and the data acquisition card transmits data to the data analysis processing device for processing after acquiring the data.
In step S3, the processing of the vibration sound data is completed by the data analysis processing means. The data analysis processing device is built based on LabVIEW and comprises an industrial personal computer, and a signal analysis and processing module built based on LabVIEW is arranged in the industrial personal computer. In the data processing process, the signal analysis and processing module sequentially carries out data interception, filtering, fast Fourier transform and natural frequency extraction on the vibration sound data. Through fast Fourier transform, the vibration sound data can be transformed from a time domain waveform to a frequency domain waveform, and in a frequency domain waveform diagram, the corresponding frequency when the vibration amplitude is maximum is the natural frequency of the engine blade.
In the engine, a plurality of identical blades are mounted on the same turbine disc, the smaller the natural frequency dispersion degree of the identical blades is, the better the natural frequency dispersion degree is, and the smaller the natural frequency dispersion degree is, the smaller the rotating speed range occupied by the engine to avoid resonance is, so that the stable operation of the engine is facilitated. The natural frequency dispersion of a plurality of identical blades is calculated using the following formula:
dispersion = (maximum natural frequency-minimum natural frequency)/minimum natural frequency x100%
Wherein the maximum natural frequency is the maximum natural frequency measured by a plurality of same blades in the same group; the minimum natural frequency is the minimum natural frequency measured for a plurality of identical blades in the same group.
Therefore, referring to fig. 2, in order to make the natural frequency dispersion of a group of engine blades within a reasonable range, the engine blade natural frequency testing method disclosed in the present application further includes step S4: and calculating the dispersion degree of the natural frequencies of the plurality of engine blades, and if the dispersion degree exceeds a limited range, adjusting the engine blades to ensure that the dispersion degree is within the limited range.
In step S4, if the calculated dispersion degree of the blade group exceeds the limit range, the maximum natural frequency blade or the minimum natural frequency blade may be replaced with another blade of the same type so that the dispersion degree of the natural frequencies of the blade group is within the limit range. For example, when the natural frequency dispersion of a group of engine blades is within a defined range, the blade with the largest natural frequency may be replaced by another blade with a smaller natural frequency, or the blade with the smallest natural frequency may be replaced by another blade with a larger natural frequency, so that the natural frequency dispersion of the group of engine blades is within the defined range.
The data of the natural frequency test of 5 groups of engine blade samples by adopting the engine blade natural frequency test method disclosed by the application are as follows:
TABLE 1 first group of blade specimens
| Serial number | One bending frequency (Hz) |
| 1 | 243.1 |
| 2 | 243.4 |
| 3 | 243.4 |
| 4 | 243.4 |
| 5 | 243.4 |
| 6 | 243.5 |
| 7 | 243.7 |
| 8 | 243.5 |
| 9 | 243.8 |
| 10 | 243.5 |
| Degree of dispersion | 0.3% |
TABLE 2 second group of blade specimens
| Serial number | One bending frequency (Hz) |
| 1 | 658.2 |
| 2 | 658.4 |
| 3 | 658.8 |
| 4 | 659.0 |
| 5 | 659.0 |
| 6 | 659.0 |
| 7 | 658.8 |
| 8 | 658.8 |
| 9 | 659.0 |
| 10 | 658.7 |
| Degree of dispersion | 0.1% |
TABLE 3 third group of blade specimens
| Serial number | One bending frequency (Hz) |
| 1 | 668.3 |
| 2 | 668.1 |
| 3 | 668.3 |
| 4 | 667.9 |
| 5 | 667.8 |
| 6 | 668.4 |
| 7 | 668.3 |
| 8 | 668.1 |
| 9 | 668.1 |
| 10 | 668.0 |
| Degree of dispersion | 0.1% |
TABLE 4 fourth set of blade specimens
| Serial number | One bending frequency (Hz) |
| 1 | 971.5 |
| 2 | 971.8 |
| 3 | 971.9 |
| 4 | 971.9 |
| 5 | 972.2 |
| 6 | 972.1 |
| 7 | 972.5 |
| 8 | 972.8 |
| 9 | 972.1 |
| 10 | 972.9 |
| Degree of dispersion | 0.1% |
TABLE 5 fifth set of blade specimens
| Serial number | One bending frequency (Hz) |
| 1 | 1051.7 |
| 2 | 1051.6 |
| 3 | 1051.6 |
| 4 | 1051.9 |
| 5 | 1051.4 |
| 6 | 1052.3 |
| 7 | 1052.3 |
| 8 | 1052.4 |
| 9 | 1052.4 |
| 10 | 1052.4 |
| Degree of dispersion | 0.1% |
Before the natural frequency test of the engine blade, the test equipment is calibrated by using a standard blade with known natural frequency, and the error is +/-1%. According to the data, the natural frequency of the engine blade tested by the testing method disclosed by the application is high in efficiency and precision; the dispersity of the same group of blades is lower than 0.3%, the adaptability is good, and a resonance frequency area can be quickly avoided.
The above is a preferred embodiment of the present application, and the scope of protection of the present application is not limited by the above, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (9)
1. A method for testing the natural frequency of an engine blade is characterized by comprising the following steps:
step S1: clamping and knocking the engine blade;
step S2: detecting a blade vibration sound signal and carrying out vibration sound data acquisition;
step S3: and processing the vibration sound data to obtain the natural frequency of the blade.
2. The method for testing the natural frequency of the engine blade according to claim 1, wherein the vibration sound data processing is performed by a data analysis processing device built based on LabVIEW.
3. The engine blade natural frequency testing method according to claim 1, wherein the vibration sound data processing process comprises the steps of data interception, filtering, fast fourier transform and natural frequency extraction which are sequentially performed.
4. The engine blade natural frequency testing method as claimed in claim 1, further comprising step S4: and calculating the natural frequency of a plurality of identical engine blades, and if the dispersion degree exceeds a limited range, adjusting the engine blades to ensure that the dispersion degree is within the limited range.
5. The engine blade natural frequency testing method according to claim 4, wherein the calculation formula of the dispersion degree is:
dispersion = (maximum natural frequency-minimum natural frequency)/minimum natural frequency x 100%.
6. The method as claimed in claim 4, wherein the clamping force and the knocking force are the same when the plurality of identical engine blades are tested.
7. The method for testing the natural frequency of the engine blade according to claim 1, wherein the blade vibration sound signal is detected by a sound pressure sensor, and the vibration sound data is collected by a data collection card.
8. The engine blade natural frequency testing method according to claim 1, wherein the engine blade is clamped by a clamping device and is rapped by a rapping device;
the clamping device can rotate around a rotating shaft vertical to the horizontal plane so as to adjust the angle between the surface of the engine blade and the hammer head of the knocking device;
the hammer head of the knocking device can be adjusted in position in the vertical direction to adapt to different blade heights.
9. The method as claimed in claim 8, wherein the hammer head material of the knocking device is steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011155476.4A CN112378998A (en) | 2020-10-26 | 2020-10-26 | Engine blade natural frequency testing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011155476.4A CN112378998A (en) | 2020-10-26 | 2020-10-26 | Engine blade natural frequency testing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112378998A true CN112378998A (en) | 2021-02-19 |
Family
ID=74577677
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011155476.4A Pending CN112378998A (en) | 2020-10-26 | 2020-10-26 | Engine blade natural frequency testing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112378998A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113504310A (en) * | 2021-05-18 | 2021-10-15 | 西安交通大学 | Blade natural frequency identification method based on single or uniformly distributed blade end timing sensor |
| CN114152398A (en) * | 2021-12-02 | 2022-03-08 | 成都市鸿侠科技有限责任公司 | Measuring device and measuring method for natural frequency of aircraft engine blade |
| CN116718394A (en) * | 2023-05-18 | 2023-09-08 | 中国船舶集团有限公司第七〇三研究所 | Blade installation quality consistency detection device of axial-flow gas turbine |
| CN117451727A (en) * | 2023-12-25 | 2024-01-26 | 四川鑫华达科技有限公司 | Quality control method for nozzle machining process |
Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101013109A (en) * | 2007-01-26 | 2007-08-08 | 东南大学 | Audio based rotating machinery vane frequency intelligent test method |
| US20090266160A1 (en) * | 2008-04-24 | 2009-10-29 | Mike Jeffrey | Method and system for determining an imbalance of a wind turbine rotor |
| CN102564561A (en) * | 2010-12-30 | 2012-07-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Test method for natural frequency of blade of integral blade disc |
| CN103472741A (en) * | 2013-08-29 | 2013-12-25 | 东方电气集团东方汽轮机有限公司 | Control system for fatigue certification experimental test on blades of wind turbine |
| CN103528776A (en) * | 2013-09-27 | 2014-01-22 | 东北大学 | High-order rotating blade dynamic similarity test experiment table and test method |
| CN103727159A (en) * | 2012-10-16 | 2014-04-16 | 义乌市黑白矿山机械有限公司 | Resonance-resisting multi-step spring damping device |
| US20160084802A1 (en) * | 2014-09-19 | 2016-03-24 | King Fahd University Of Petroleum And Minerals | Process for determining weld quality using flexural characteristics |
| CN205157150U (en) * | 2015-12-03 | 2016-04-13 | 华东交通大学 | Magnetic current becomes elastomer intermediate layer roof beam vibration response test system |
| CN106017987A (en) * | 2016-05-18 | 2016-10-12 | 大连理工大学 | Measurement and control system and monitor and control method of vibratory bottom sampler |
| CN109932151A (en) * | 2019-03-28 | 2019-06-25 | 东北大学 | A kind of lower integral blade disk pitch diameter exercise test device and method of wave-passage excitation effect |
| CN110220662A (en) * | 2019-07-23 | 2019-09-10 | 湖南南方通用航空发动机有限公司 | A kind of test method of blade high frequency static frequency |
-
2020
- 2020-10-26 CN CN202011155476.4A patent/CN112378998A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101013109A (en) * | 2007-01-26 | 2007-08-08 | 东南大学 | Audio based rotating machinery vane frequency intelligent test method |
| US20090266160A1 (en) * | 2008-04-24 | 2009-10-29 | Mike Jeffrey | Method and system for determining an imbalance of a wind turbine rotor |
| CN102564561A (en) * | 2010-12-30 | 2012-07-11 | 沈阳黎明航空发动机(集团)有限责任公司 | Test method for natural frequency of blade of integral blade disc |
| CN103727159A (en) * | 2012-10-16 | 2014-04-16 | 义乌市黑白矿山机械有限公司 | Resonance-resisting multi-step spring damping device |
| CN103472741A (en) * | 2013-08-29 | 2013-12-25 | 东方电气集团东方汽轮机有限公司 | Control system for fatigue certification experimental test on blades of wind turbine |
| CN103528776A (en) * | 2013-09-27 | 2014-01-22 | 东北大学 | High-order rotating blade dynamic similarity test experiment table and test method |
| US20160084802A1 (en) * | 2014-09-19 | 2016-03-24 | King Fahd University Of Petroleum And Minerals | Process for determining weld quality using flexural characteristics |
| CN205157150U (en) * | 2015-12-03 | 2016-04-13 | 华东交通大学 | Magnetic current becomes elastomer intermediate layer roof beam vibration response test system |
| CN106017987A (en) * | 2016-05-18 | 2016-10-12 | 大连理工大学 | Measurement and control system and monitor and control method of vibratory bottom sampler |
| CN109932151A (en) * | 2019-03-28 | 2019-06-25 | 东北大学 | A kind of lower integral blade disk pitch diameter exercise test device and method of wave-passage excitation effect |
| CN110220662A (en) * | 2019-07-23 | 2019-09-10 | 湖南南方通用航空发动机有限公司 | A kind of test method of blade high frequency static frequency |
Non-Patent Citations (1)
| Title |
|---|
| 白静: "透平叶片固有频率和振型的测试方法分析", 新技术新工艺, pages 90 - 93 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113504310A (en) * | 2021-05-18 | 2021-10-15 | 西安交通大学 | Blade natural frequency identification method based on single or uniformly distributed blade end timing sensor |
| CN114152398A (en) * | 2021-12-02 | 2022-03-08 | 成都市鸿侠科技有限责任公司 | Measuring device and measuring method for natural frequency of aircraft engine blade |
| CN114152398B (en) * | 2021-12-02 | 2023-10-27 | 成都市鸿侠科技有限责任公司 | Device and method for measuring natural frequency of aircraft engine blade |
| CN116718394A (en) * | 2023-05-18 | 2023-09-08 | 中国船舶集团有限公司第七〇三研究所 | Blade installation quality consistency detection device of axial-flow gas turbine |
| CN117451727A (en) * | 2023-12-25 | 2024-01-26 | 四川鑫华达科技有限公司 | Quality control method for nozzle machining process |
| CN117451727B (en) * | 2023-12-25 | 2024-03-12 | 四川鑫华达科技有限公司 | Quality control method for nozzle machining process |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112378998A (en) | Engine blade natural frequency testing method | |
| CN100523765C (en) | Vibrating detection method for detecting looseness of large-scale generator rotor slot wedge and apparatus therefor | |
| CN101561379B (en) | Tap-scanning method for detecting structural damages | |
| CN105067239B (en) | The beam crack fault detection means and method vibrated based on swept frequency excitation | |
| CN108918064A (en) | A kind of tenon connects blade inherent characteristic non-contact testing experimental provision and test method | |
| CN101251411A (en) | Apparatus for measuring impeller blade | |
| CN108593230A (en) | A kind of Natural Frequency of Blade Auto-Test System | |
| CN203133033U (en) | Fruit firmness nondestructive detection device based on laser doppler vibrometry | |
| CN101949731B (en) | Method for testing high-order frequency of large wind-power blades | |
| CN110836721A (en) | Static frequency testing device and method for blades of blisk of aircraft engine | |
| CN111780866B (en) | Diesel engine test base installation state natural frequency testing method and device | |
| CN209979111U (en) | Test device for exploring nondestructive testing residual stress | |
| CN114295311B (en) | High acceleration vibration test system based on phase resonance principle | |
| CN104977218A (en) | Device and method for detecting rigidity of micro elastic parts | |
| CN111521255A (en) | Method and device for measuring natural frequency of blade in engine | |
| CN115015268B (en) | Tunnel lining defect disease diagnosis method based on laser technology | |
| CN206114594U (en) | Small -size irregular foundry goods spectrum nondestructive test device | |
| CN116296781A (en) | Method and system for determining critical strain value of I-type crack tip fracture process zone | |
| CN214953240U (en) | Device for measuring elastic modulus of excited vibration | |
| CN112326166B (en) | Adjustable random vibration magnitude amplification device and test method | |
| CN110940509B (en) | Servo electric cylinder reliability experiment device and test method based on load spectrum | |
| CN109142535A (en) | A kind of saw blade non-destructive testing device based on acoustic resonance spectrum | |
| CN1632495A (en) | Flexible rotor dynamic balance determination apparatus based on transfer function | |
| CN113484374A (en) | Voltage stability testing system for high-low voltage electric porcelain appliance | |
| CN209311256U (en) | Device for the assessment of bearing retainer wearability |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20210219 |