CN205175696U - Measurement device for be used for aeroengine structure spare natural frequency - Google Patents
Measurement device for be used for aeroengine structure spare natural frequency Download PDFInfo
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- CN205175696U CN205175696U CN201520832586.8U CN201520832586U CN205175696U CN 205175696 U CN205175696 U CN 205175696U CN 201520832586 U CN201520832586 U CN 201520832586U CN 205175696 U CN205175696 U CN 205175696U
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Abstract
The utility model discloses a measurement device for be used for aeroengine structure spare natural frequency, include: the noise meter and is surveyed structure interval and relative the setting, and the acoustic signals who generates is surveyed in order to detect in the microphone of the noise meter probe perpendicular to structure surface of being surveyed the structure when structure vibrates under the external drive, charge amplifier receives the voltage signal of noise meter output and amplifies the processing, charge amplifier is connected to dynamic signal analysis appearance for the receipt is amplified the signal after handling and is vibrated the natural frequency that spectrum analysis obtained being surveyed the structure through charge amplifier. The utility model provides a because of unable rigid mounting vibrational acceleration sensor detects the problem of being surveyed the structure vibration signal, and owing to need not installation vibrational acceleration sensor on being surveyed the structure, avoided the added mass of the sensor of rigidity contact to cause the influence to the rigidity of being surveyed the structure to the accuracy of testing result has been improved.
Description
Technical field
The utility model relates to aeromotor detection field, especially, relates to a kind of for aeromotor structural member natural frequency measurement, device.
Background technology
Aeromotor in commissioning process, at over-difference of vibration under a certain rotary regimes, suspect sometimes fundamental frequency that engine a certain structure rank natural frequencys may be corresponding with this working speed close to after there is resonance effect.Therefore, the vibration test system that often need form by means of vibration acceleration sensor, secondary instrument and dynamic signal analyzer device, utilizing hammering method to carry out quiet frequency test to needing certain structure member of engine measuring natural frequency after initial analysis, being further analyzed again after measurement.This technology is after becoming transient force according to the exciting force in structure forced vibration equation, this equation is converted into Free Vibration Equations in the short period of time, solved the limited rank eigen vector of this equation by current constraints, be model frequency and Mode Shape or natural frequency and natural mode of vibration.
In prior art, generally select vibration acceleration sensor, charge amplifier, dynamic signal analyzer device and vibration-testing line some, form vibration test system.Utilize hammering method to measure structural natural frequencies, the structure of or surperficial irregularity less for quality, measure rough result.
Utilize contact vibration acceleration sensor to carry out the test of structural member natural frequency, following four critical problems can be run in some cases:
1, some structure of engine is less, because vibration acceleration sensor only just can not impact because of the rigidity of the additional mass of sensor to institute's geodesic structure much larger than it at measured architecture quality, so cannot its natural frequency of Measurement accuracy for structure small parts application vibration acceleration sensor;
2, only there is curved surface or corrugated surface in some structure of engine, the required plane of installing of friction acceleration transducer, if under the impact not considering the extraneous vibration of adapter for the structure can installing vibration measuring adapter and indirectly install vibration transducer and the condition with sufficient time processing adapter, this situation problem can be met.If but institute's geodesic structure cannot install vibration measuring adapter, then the quiet frequency test of this structure can be caused to occur difficulty;
3, effectively vibration transducer can be installed in engine structure parts and under the condition that multiple vibration transducer display result is inconsistent for a certain reason, a kind of attitude of suspection can be held the result of carrying out quiet frequency test, cannot next step vibration analysis be carried out;
If 4 sensors are arranged on the node location of structure, the model frequency due to structure exists infinite multiple in theory, just cannot measure this natural frequency corresponding to Mode Shape of rank.
Utility model content
The utility model provides a kind of for aeromotor structural member natural frequency measurement, device, causes Measurement accuracy natural frequency and vibration acceleration sensor to be difficult to the technical matters of installation and test result instability to solve existing natural frequency mechanism for testing because of the additional mass treating geodesic structure.
The technical solution adopted in the utility model is as follows:
A kind of for aeromotor structural member natural frequency measurement, device, comprising:
Sound meter, and tested structural member interval and being oppositely arranged, and the microphone probe vertical of sound meter in the body structure surface of tested structural member to detect the acoustic signals generated when tested structural member vibrates under external force drives;
Charge amplifier, receives the voltage signal of sound meter output and carries out amplification process;
Dynamic signal analyzer, connect charge amplifier, for receive through charge amplifier amplify process after signal and carry out the natural frequency that vibration frequency specturm analysis obtains tested structural member.
Further, charge amplifier is built in sound meter, and sound meter connects the input end of dynamic signal analyzer through vibration-testing line.
Further, the output terminal of dynamic signal analyzer connects the display module for showing rumble spectrum.
Further, the utility model also comprises for aeromotor structural member natural frequency measurement, device:
Vibration acceleration sensor, is installed on tested structural member, for detecting the vibration signal generated when tested structural member vibrates under external force drives, with complementary with sound meter; Vibration acceleration sensor connects the input end of dynamic signal analyzer through charge amplifier.
Further, vibration acceleration sensor is adsorbed on tested structural member through magnetic base.
Further, the spacing of sound meter and tested structural member is 5 to 8 centimetres.
Further, the microphone of sound meter adopts condenser type, crystal formula, formula in body or moving-coil microphone.
The utility model has following beneficial effect:
The utility model is used for aeromotor structural member natural frequency measurement, device, the acoustic signals generated when tested structural member being vibrated under external force drives by adopting sound meter, and by dynamic signal analyzer, vibration frequency specturm analysis is carried out to signal and obtain by the natural frequency of structural member to be measured, solve because rigidity the problem that vibration acceleration sensor detects tested structural member vibration signal cannot be installed, and due to without the need to installing vibration acceleration sensor on tested structural member, the rigidity of impost to tested structural member avoiding the sensor of rigid contact impacts, thus improve the accuracy of testing result.
Except object described above, feature and advantage, the utility model also has other object, feature and advantage.Below with reference to figure, the utility model is described in further detail.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide further understanding of the present utility model, and schematic description and description of the present utility model, for explaining the utility model, is not formed improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the utility model preferred embodiment for aeromotor structural member natural frequency measurement, device.
Description of reference numerals:
10, tested structural member;
20, sound meter;
30, dynamic signal analyzer;
40, vibration-testing line;
50, display module;
60, vibration acceleration sensor;
70, charge amplifier;
80, power supply;
90, hammer is knocked.
Embodiment
It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.Below with reference to the accompanying drawings and describe the utility model in detail in conjunction with the embodiments.
With reference to Fig. 1, preferred embodiment of the present utility model provides a kind of for aeromotor structural member natural frequency measurement, device, and the present embodiment measurement mechanism comprises:
Sound meter 20, and tested structural member 10 interval and being oppositely arranged, and the microphone probe vertical of sound meter 20 in the body structure surface of tested structural member 10 to detect the acoustic signals generated when tested structural member 10 vibrates under external force drives;
Charge amplifier, receives the voltage signal of sound meter 20 output and carries out amplification process;
Dynamic signal analyzer 30, connect charge amplifier, for receive through charge amplifier amplify process after signal and carry out the natural frequency that vibration frequency specturm analysis obtains tested structural member 10.
Wherein, dynamic signal analyzer 30 receives the signal of the vibration frequency for reflecting tested structural member 10, vibration frequency specturm analysis is carried out after vibration frequency specturm analysis obtains the natural frequency method of tested structural member 10 and existing dynamic signal analyzer 30 receives the vibration frequency of the tested structural member that vibration acceleration sensor detects, and then the method obtaining its natural frequency is identical, therefore belong to prior art, do not repeat them here.The improvement of the present embodiment is, change traditional rigidity on tested structural member 10 and vibration acceleration sensor is installed to detect the mode of the vibration frequency signal of tested structural member, by the detection mode adopting the present embodiment contactless, both solved because rigidity the problem that vibration acceleration sensor detects tested structural member 10 vibration signal cannot be installed, and due to without the need to installing vibration acceleration sensor on tested structural member 10, the rigidity of impost to tested structural member avoiding the sensor of rigid contact impacts, thus improve the accuracy of testing result.
Preferably, charge amplifier is built in sound meter 20, and sound meter 20 connects the input end of dynamic signal analyzer 30 through vibration-testing line 40.
The microphone of the present embodiment sound meter 20 adopts condenser type, crystal formula, formula in body or moving-coil microphone.Preferably, adopt condenser microphone, the output terminal of condenser microphone connects charge amplifier, and the two is integrated in sound meter.Preferably, sound meter 20 is 5 to 8 centimetres, to guarantee good Detection results with the spacing of tested structural member 10.
Alternatively, the output terminal of dynamic signal analyzer 30 connects the display module 50 for showing rumble spectrum.In the present embodiment, with reference to Fig. 1, dynamic signal analyzer 30 connects the main frame being used for signal operation process, and main frame connects mouse, keyboard through input port, and main frame connects the display being used for rumble spectrum display through output port.The present embodiment measurement mechanism is also provided with the power supply 80 into dynamic signal analyzer 30 power supply.
Preferably, the object examined mutually to realize utilizing vibration acceleration sensor and sound meter to realize frequency, the present embodiment measurement mechanism also comprises:
Vibration acceleration sensor 60, is installed on tested structural member 10, for detecting the vibration signal generated when tested structural member 10 vibrates under external force drives, with complementary with sound meter 20; Vibration acceleration sensor 60 connects the input end of dynamic signal analyzer 30 through charge amplifier 70, vibration-testing line 40.
Preferably, in order to improve measuring accuracy, before testing, need calibrate sound meter 20, vibration acceleration sensor 60.In actual applications, need standard vibration machine, standard sounding device to calibrate the vibration acceleration sensor 60 tested for natural frequency, sound meter 20, after meeting alignment requirements, be applied to natural frequency test.
The present embodiment measurement mechanism before testing, should keep scene to be in quiet environment, avoids because ground unrest affects the measurement result of sound meter.Two analog quantity channels of dynamic signal analyzer 30 connect sound meter 20 through vibration-testing line 40 respectively, vibration acceleration sensor 60, wherein, vibration acceleration sensor 60 and tested structural member 10 rigid contact, sound meter 20 perpendicular to tested structural member 10 surface and distance is 5 to 8 centimetres, and be positioned over close to vibration acceleration sensor 60 position, then utilization is knocked hammer 90 and knock three times fast near vibration acceleration sensor 60 and sound meter 20, interval 2s, then the transverse vibration frequency spectrum of two passage resulting structures is carried out linear averaging respectively, obtain the model frequency that two passages record, contrast, both are consistent at measurement result in tolerance frequency error range.
For the tested structural member without curved surface or the corrugated surface supporting that vibration acceleration sensor rigidity is installed, select magnet base that vibration acceleration sensor is adsorbed in body structure surface, sound meter still adopts said method to place, structure is knocked fast 3 times near vibration acceleration sensor and sound meter, interval 2s, linear averaging, contrast model frequency, both measurement result frequency phase-differences are comparatively large, but in some levels.
The present embodiment measurement mechanism, contactless sound meter is adopted to carry out quiet frequency test to engine component, not only can eliminate additional mass and bring the problem of frequency test difficulty with cannot contact, and can avoid because of the processing adapter time lengthening troubleshooting time and eliminate extraneous vibration.Meanwhile, contactless sound meter and contact vibration acceleration sensor carry out quiet frequency to tested structural member and test the object that can reach and mutually check, and improve the accuracy that natural frequency is measured.
The foregoing is only preferred embodiment of the present utility model, be not limited to the utility model, for a person skilled in the art, the utility model can have various modifications and variations.All within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (7)
1., for an aeromotor structural member natural frequency measurement, device, it is characterized in that, comprising:
Sound meter (20), and tested structural member (10) interval and being oppositely arranged, and the microphone probe vertical of described sound meter (20) in the body structure surface of described tested structural member (10) to detect the acoustic signals generated when described tested structural member (10) is vibrated under external force drives;
Charge amplifier, the voltage signal that reception sound meter (20) exports also carries out amplification process;
Dynamic signal analyzer (30), connects described charge amplifier, amplifies the signal after process for receiving and carries out the natural frequency that vibration frequency specturm analysis obtains described tested structural member (10) through described charge amplifier.
2. according to claim 1ly to it is characterized in that for aeromotor structural member natural frequency measurement, device,
Described charge amplifier is built in described sound meter (20), and described sound meter (20) connects the input end of described dynamic signal analyzer (30) through vibration-testing line (40).
3. according to claim 2ly to it is characterized in that for aeromotor structural member natural frequency measurement, device,
The output terminal of described dynamic signal analyzer (30) connects the display module (50) for showing rumble spectrum.
4. arbitrary described for aeromotor structural member natural frequency measurement, device according to claims 1 to 3, it is characterized in that, also comprise:
Vibration acceleration sensor (60), be installed on tested structural member (10), for detecting the vibration signal generated when described tested structural member (10) is vibrated under external force drives, with complementary with described sound meter (20); Described vibration acceleration sensor (60) connects the input end of described dynamic signal analyzer (30) through charge amplifier.
5. according to claim 4ly to it is characterized in that for aeromotor structural member natural frequency measurement, device,
Described vibration acceleration sensor (60) is adsorbed on described tested structural member (10) through magnetic base.
6. according to claim 1ly to it is characterized in that for aeromotor structural member natural frequency measurement, device,
Described sound meter (20) is 5 to 8 centimetres with the spacing of described tested structural member (10).
7. according to claim 1ly to it is characterized in that for aeromotor structural member natural frequency measurement, device,
The microphone of described sound meter (20) adopts condenser type, crystal formula, formula in body or moving-coil microphone.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520832586.8U CN205175696U (en) | 2015-10-26 | 2015-10-26 | Measurement device for be used for aeroengine structure spare natural frequency |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520832586.8U CN205175696U (en) | 2015-10-26 | 2015-10-26 | Measurement device for be used for aeroengine structure spare natural frequency |
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| CN205175696U true CN205175696U (en) | 2016-04-20 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109738521A (en) * | 2019-01-21 | 2019-05-10 | 浙江工业大学 | A kind of hand-held automatically exciting damage check instrument for structure flaw detection |
| CN109738522A (en) * | 2019-01-21 | 2019-05-10 | 浙江工业大学 | A kind of handheld electromagnetic absorption damage check instrument for steel building flaw detection |
| CN110940528A (en) * | 2019-12-19 | 2020-03-31 | 中国人民解放军海军士官学校 | Method and system for identifying working modal parameters of diesel engine based on detonation excitation |
| CN114199445A (en) * | 2021-11-17 | 2022-03-18 | 陕西高速星展科技有限公司 | Track bolt state detection method and device, electronic equipment and storage medium |
-
2015
- 2015-10-26 CN CN201520832586.8U patent/CN205175696U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109738521A (en) * | 2019-01-21 | 2019-05-10 | 浙江工业大学 | A kind of hand-held automatically exciting damage check instrument for structure flaw detection |
| CN109738522A (en) * | 2019-01-21 | 2019-05-10 | 浙江工业大学 | A kind of handheld electromagnetic absorption damage check instrument for steel building flaw detection |
| CN110940528A (en) * | 2019-12-19 | 2020-03-31 | 中国人民解放军海军士官学校 | Method and system for identifying working modal parameters of diesel engine based on detonation excitation |
| CN110940528B (en) * | 2019-12-19 | 2022-04-19 | 中国人民解放军海军士官学校 | Method and system for identifying working modal parameters of diesel engine based on detonation excitation |
| CN114199445A (en) * | 2021-11-17 | 2022-03-18 | 陕西高速星展科技有限公司 | Track bolt state detection method and device, electronic equipment and storage medium |
| CN114199445B (en) * | 2021-11-17 | 2024-06-07 | 陕西高速星展科技有限公司 | Track bolt state detection method and device, electronic equipment and storage medium |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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| CP01 | Change in the name or title of a patent holder |