CN209387124U - A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor - Google Patents
A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor Download PDFInfo
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- CN209387124U CN209387124U CN201920055612.9U CN201920055612U CN209387124U CN 209387124 U CN209387124 U CN 209387124U CN 201920055612 U CN201920055612 U CN 201920055612U CN 209387124 U CN209387124 U CN 209387124U
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Abstract
The utility model discloses a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor, including high-temperature cabinet, test vibration platform and data collecting mechanism, test vibration platform includes transmission arm, the free end of transmission arm is equipped with assembly side, high-temperature cabinet includes the first through hole and the second through hole through tank wall, test vibration platform is located at the first through hole side of high-temperature cabinet, and the free end of transmission arm passes through the first through hole and is located in high-temperature cabinet, there are vibratility adjustment spaces between first through hole and transmission arm, the conducting wire of data gather computer structure passes through the second through hole and mutually connects with magneto-electric vibrating sensor.The utility model sensibility testing arrangement is simple for structure, compares laser testing equipment and has feature at low cost and easily operated.Verification efficiency can be improved, production test demand is met, defect screening can be carried out in production link, is done over again again without rear end detection defect, is reduced repetition operating cost, have preferably economic value.
Description
Technical field
The utility model relates to a kind of sensibility testing arrangements of aero-engine magneto-electric vibrating sensor, belong to sensing
The technical field of device test equipment.
Background technique
Magneto-electric vibrating sensor is widely used in aero-engine field, and monitoring engine is played under harsh environment
The effect of working condition, hot environment have a significant impact to magneto-electric vibrating sensor performance.Current high temperature susceptability, because
The table top tolerance high temperature of standard vibration machine is limited.The test condition of combined test chamber is narrow.Test method is all that will vibrate biography at present
Sensor is put into high-temperature cabinet, as required temperature for a period of time after, take out immediately dress measuring on a vibration table.This test side
For method since the heat dissipation of heat radiation influences, temperature requirement more high effect is more bad.
Existing space industry high temperature susceptability absolute test method proper measurement field, precision is high, cost of manufacture is high, uncomfortable
The check test field that symphysis produces.
Utility model content
The purpose of this utility model is to solve above-mentioned the deficiencies in the prior art, for traditional mode of production detection test effect difference
Problem proposes a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor.
In order to achieve the above object, the technology employed by the present utility model is
A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor, including high-temperature cabinet, test vibration platform
With data collecting mechanism,
The test vibration platform includes a transmission arm, and the free end of the transmission arm is equipped with for assembling the magnetoelectricity
The assembly side of formula vibrating sensor,
The high-temperature cabinet includes the first through hole and the second through hole through tank wall,
The test vibration platform is located at the first through hole side of the high-temperature cabinet, and the free end of the transmission arm is worn
It crosses first through hole to be located in the high-temperature cabinet, there are vibratility adjustment skies between first through hole and the transmission arm
Between,
The conducting wire of the data gather computer structure passes through second through hole and mutually connects with the magneto-electric vibrating sensor.
Preferably, sealed elastic part is equipped between first through hole and the transmission arm.
Preferably, the sealed elastic part include be embedded in the vibratility adjustment space sealing and with the high-temperature cabinet
Lateral wall abuts against outer portion.
Preferably, the sealed elastic part is asbestos seal part.
Preferably, the data gather computer structure includes charge amplifier and digital voltmeter.
Preferably, the free end of the conducting wire of the data gather computer structure is equipped with fast-assembling interface.
The beneficial effects of the utility model are mainly reflected in:
1. sensibility testing arrangement is simple for structure, compares laser testing equipment and have feature at low cost and easily operated.
2. verification efficiency can be improved, meet production test demand, defect screening can be carried out in production link, is not necessarily to rear end
Detection defect is done over again again, reduces repetition operating cost, has preferably economic value.
Detailed description of the invention
Fig. 1 is that a kind of structure of the sensibility testing arrangement of aero-engine magneto-electric vibrating sensor of the utility model is shown
It is intended to.
Specific embodiment
The utility model provides a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor.Below in conjunction with
Technical solutions of the utility model are described in detail in attached drawing, so that it is more readily understood and grasps.
A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor, as shown in Figure 1, include high-temperature cabinet 1,
Test vibration platform 2 and data collecting mechanism 3, the vibration control of test vibration platform 2 and data gather computer structure 3 vibrate magneto-electric and pass
The data acquisition principle of sensor belongs to the prior art, and details are not described herein.
In this case, test vibration platform 2 includes a transmission arm 4, and the free end of transmission arm 4 is equipped with for assembling magneto-electric
The assembly side 6 of vibrating sensor 5.
High-temperature cabinet 1 includes the first through hole 7 and the second through hole 8 through tank wall.
Test vibration platform 2 is located at 7 side of the first through hole of high-temperature cabinet 1, and the free end of transmission arm 4 passes through first and passes through
Through-hole 7 is located in high-temperature cabinet 1, and there are vibratility adjustment spaces between the first through hole 7 and transmission arm 4.
The conducting wire of data gather computer structure 3 passes through the second through hole 8 and connects with 5 phase of magneto-electric vibrating sensor.
It should be noted that high-temperature cabinet 1 has chamber door, and chamber door and tank wall described in the first through hole are non-coplanar.
Specifically realize process and principle explanation:
Test vibration platform 2 and high-temperature cabinet 1 are relatively fixed setting structure.
When carrying out sensitivity test, the chamber door of high-temperature cabinet 1 is opened, magneto-electric vibrating sensor 5 is fixed on transmission arm 4
In assembly side 6, complete to be coupled by the conducting wire of data gather computer structure 3 and magneto-electric vibrating sensor 5.
By adjusting shake table vibration frequency and vibration level, magneto-electric vibration is acquired further according to data gather computer structure 3 and is passed
The output voltage of sensor 5 can calculate sensitivity.
It should be noted that this case can be calibrated using standard transducer, standard transducer is fixed on assembly side 6
On, shake table vibration frequency and vibration level are adjusted, the connected digital table of observation transmission device end standard vibrating sensor
Output voltage can calculate the vibration level of standard vibration sensor according to output voltage, when digital voltmeter show value reaches
To defined vibration level and after stablizing, current vibration parameters are recorded, with the vibration parameters to magneto-electric vibrating sensing to be measured
Device 5 is tested.Including room temperature test and high temperature test, when high temperature test, which passes through high-temperature cabinet 1 and carries out temperature, to be set i.e.
It can.
In a specific embodiment, sealed elastic part 9 is equipped between the first through hole 7 and transmission arm 4.The sealed elastic
Part 9 is used for thermal insulation, it is ensured that set temperature accuracy in high-temperature cabinet.
In order to facilitate the assembly of sealed elastic part 9 comprising insertion vibratility adjustment space sealing and with outside high-temperature cabinet
Side wall abuts against outer portion.The design of outer portion can prevent sealed elastic part 9 from falling in high-temperature cabinet in vibration processes, increase
The safety of device.
More specifically, sealed elastic part 9 is asbestos seal part.
Data collecting mechanism 3 is refined comprising charge amplifier and digital voltmeter, in room temperature test mode
Under, while charge amplifier and digital voltmeter are used, under high temperature test state, it is only necessary to access digital voltmeter, charge
The used aloned of amplifier and digital voltmeter and circuit is used in combination belongs to the prior art, details are not described herein.
In a specific embodiment, the free end of the conducting wire of data gather computer structure 3, which is equipped with, has fast attaching resistant to high temperature
Mouthful, convenient for carrying out quick assembling with magneto-electric vibrating sensor 5, improve detection efficiency.
Finally, it should be noted that the set temperature of high-temperature cabinet is no more than 500 DEG C.
By above description it can be found that a kind of sensitivity of aero-engine magneto-electric vibrating sensor of the utility model
Test device, sensibility testing arrangement is simple for structure, compares laser testing equipment and has feature at low cost and easily operated.Energy
Verification efficiency is improved, meets production test demand, defect screening can be carried out in production link, is returned again without rear end detection defect
Work reduces repetition operating cost, has preferably economic value.
The technical solution of the utility model is fully described above, it should be noted that the tool of the utility model
Body embodiment is simultaneously not limited by the description set out above, and those skilled in the art exist according to the Spirit Essence of the utility model
All technical solutions that structure, method or function etc. are formed using equivalents or equivalent transformation, all fall within this reality
Within novel protection scope.
Claims (6)
1. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor, including high-temperature cabinet, test vibration platform and
Data gather computer structure, it is characterised in that:
The test vibration platform includes a transmission arm, and the free end of the transmission arm is equipped with for assembling the magneto-electric vibration
The assembly side of dynamic sensor,
The high-temperature cabinet includes the first through hole and the second through hole through tank wall,
The test vibration platform is located at the first through hole side of the high-temperature cabinet, and the free end of the transmission arm passes through institute
The first through hole is stated to be located in the high-temperature cabinet, there are vibratility adjustment space between first through hole and the transmission arm,
The conducting wire of the data gather computer structure passes through second through hole and mutually connects with the magneto-electric vibrating sensor.
2. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor according to claim 1, feature
It is:
Sealed elastic part is equipped between first through hole and the transmission arm.
3. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor according to claim 2, feature
It is:
The sealed elastic part includes being embedded in the sealing in the vibratility adjustment space and abutting against with the high-temperature cabinet lateral wall
Outer portion.
4. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor according to Claims 2 or 3, special
Sign is:
The sealed elastic part is asbestos seal part.
5. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor according to claim 1, feature
It is:
The data gather computer structure includes charge amplifier and digital voltmeter.
6. a kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor according to claim 1, feature
It is:
The free end of the conducting wire of the data gather computer structure is equipped with fast-assembling interface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920055612.9U CN209387124U (en) | 2019-01-14 | 2019-01-14 | A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920055612.9U CN209387124U (en) | 2019-01-14 | 2019-01-14 | A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209387124U true CN209387124U (en) | 2019-09-13 |
Family
ID=67853232
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920055612.9U Active CN209387124U (en) | 2019-01-14 | 2019-01-14 | A kind of sensibility testing arrangement of aero-engine magneto-electric vibrating sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209387124U (en) |
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2019
- 2019-01-14 CN CN201920055612.9U patent/CN209387124U/en active Active
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