CN207263431U - Blade of aviation engine high-temperature high-frequency fatigue life test device - Google Patents
Blade of aviation engine high-temperature high-frequency fatigue life test device Download PDFInfo
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- CN207263431U CN207263431U CN201721270769.0U CN201721270769U CN207263431U CN 207263431 U CN207263431 U CN 207263431U CN 201721270769 U CN201721270769 U CN 201721270769U CN 207263431 U CN207263431 U CN 207263431U
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- blade
- temperature
- fatigue life
- test device
- life test
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- Testing Of Engines (AREA)
Abstract
The utility model discloses a kind of blade of aviation engine high-temperature high-frequency fatigue life test device, it includes：High-temperature control unit at least the temperature of blade to be adjusted, it includes heating generator, heating generator includes an at least induction coil, induction coil is non-contactly sheathed on blade, induction coil is electrically connected with high frequency electric source and is used to make blade spontaneous heating heat up, vibrate generating unit, at least to provide to blade carry out testing fatigue needed for vibration frequency and vibration level, displacement monitoring unit and strain monitoring unit, at least monitoring the vibration amplitude of the specified location on blade and strain value, displacement monitoring unit is connected with strain monitoring unit and vibration generating unit respectively.Blade of aviation engine high-temperature high-frequency fatigue life test device provided by the utility model can make blade of aviation engine temperature fast lifting to operating temperature, and keep at these elevated temperatures, carrying out the fatigue life test under different vibration levels.
Description
Technical field
More particularly to a kind of blade of aviation engine high-temperature high-frequency fatigue life test device of the utility model, belongs to environment
Experimental technique field.
Background technology
Environmental test is the test of the various equipments of simulation and parts under the conditions of local environment in actual work, passes through survey
Try to judge to equip working status and endurance life under actual working conditions.Environment includes mechanical environment, climatic environment
And weather environment.Mechanical environment refers to various mechanical environments, such as vibrates, impacts and waves；Climatic environment refers to high/low temperature ring
Border and humidity environment etc.；Weather environment refers to illumination, low pressure, mould and salt fog etc..
Traditional blade fatigue life test is completed at normal temperatures.Foil gauge is pasted in specified location, is allowed at blade
Vibrated in intrinsic frequency, the fatigue strength of blade and fatigue life are derived by monitoring strain size and time of vibration.
But for the blade for being partially in high-temperature work environment, the result of the test under room temperature has deviation.
Utility model content
The main purpose of the utility model is that provide a kind of blade of aviation engine high-temperature high-frequency fatigue life test dress
Put, with overcome the deficiencies in the prior art.
To realize foregoing purpose of utility model, the technical solution adopted in the utility model includes：
The utility model embodiment provides a kind of blade of aviation engine high-temperature high-frequency fatigue life test device, described
Test device includes：
At least to the high-temperature control unit that the temperature of blade is adjusted, it includes heating generator, the high frequency
Heater includes an at least induction coil, and the induction coil is non-contactly sheathed on blade, the induction coil and high frequency
Power electric connection simultaneously is used to make the blade spontaneous heating heat up,
Vibrate generating unit, at least to provide to the blade carry out testing fatigue needed for vibration frequency and vibratory output
Level,
Displacement monitoring unit, at least monitoring the vibration amplitude of the specified location on blade
Strain monitoring unit, at least to monitor the strain value of the specified location on blade,
The displacement monitoring unit is connected with strain monitoring unit and vibration generating unit respectively, and the blade is fixed on institute
On the work top for stating the shake table in vibration generating unit, the high-temperature control unit is connected with the blade.
Further, the high-temperature control unit further includes temperature measurement module and power governor, the heating generator with
Power governor connects, and the power governor is connected with temperature measurement module, and the temperature measurement module is at least used to monitor the blade
Temperature.
In some more specific embodiment, the temperature measurement module uses infrared temperature measurement device.
Further, the displacement monitoring unit includes acquisition module, laser displacement sensor, the laser displacement sensing
Device is used for the vibration amplitude for monitoring the specified location on the blade；The strain monitoring unit includes foil gauge, described to answer
Become the specified location that piece is installed on blade, the acquisition module is connected with laser displacement sensor and foil gauge respectively.
Further, the vibration generating unit includes shake table, blade fixture, power amplifier and signal generator,
The blade is fixed on by blade fixture on the work top of the shake table, the signal generator and the displacement monitoring
Unit is connected with power amplifier.
Further, described device further includes cooling unit, the cooling unit be at least used for the blade fixture into
Row cooling treatment.
Further, the cooling unit is included to provide the cooler bin of cooling medium, and the cooler bin is passed through with pump
Cooling medium stream siphunculus road be connected with blade fixture.
Further, the cooling unit further includes cooling medium recovery device, the cooling medium recovery device with it is cold
But case connects.
Compared with prior art, include the advantages of the utility model：Blade of aviation engine provided by the utility model is high
Warm high-cycle fatigue endurance testing device can make blade of aviation engine temperature fast lifting to operating temperature, and keep high herein
Under temperature, the fatigue life test under different vibration levels is carried out.
Brief description of the drawings
Fig. 1 is blade of aviation engine high-temperature high-frequency fatigue life test device in one exemplary embodiments of the utility model
Technical route structure diagram；
Description of reference numerals：1- blades, 2- high-temperature control units, 21- power governors, 22- infrared temperature measurement devices, 23- high
Frequency heater, 3- displacements and strain monitoring unit, 31- laser displacement sensors, 32- foil gauges, 33- acquisition modules, 4- vibrations
Generating unit, 41- blade fixtures, 42- shake tables, 43- power amplifiers, 44- signal generators, 5- cooling units, 51- water
Pump, 52- cooler bins.
Embodiment
In view of deficiency of the prior art, inventor is able to propose that this practicality is new through studying for a long period of time and largely putting into practice
The technical solution of type.The technical solution, its implementation process and principle etc. will be further explained as follows.
The utility model embodiment provides a kind of blade of aviation engine high-temperature high-frequency fatigue life test device, described
Test device includes：
At least to the high-temperature control unit that the temperature of blade is adjusted, it includes heating generator, the high frequency
Heater includes an at least induction coil, and the induction coil is non-contactly sheathed on blade, the induction coil and high frequency
Power electric connection simultaneously is used to make the blade spontaneous heating heat up,
Vibrate generating unit, at least to provide to the blade carry out testing fatigue needed for vibration frequency and vibratory output
Level,
Displacement monitoring unit, at least monitoring the vibration amplitude of the specified location on blade
Strain monitoring unit, at least to monitor the strain value of the specified location on blade,
The displacement monitoring unit is connected with strain monitoring unit and vibration generating unit respectively, and the blade is fixed on institute
On the work top for stating the shake table in vibration generating unit, the high-temperature control unit is connected with the blade.
Further, the high-temperature control unit further includes temperature measurement module and power governor, the heating generator with
Power governor connects, and the power governor is connected with temperature measurement module, and the temperature measurement module is at least used to monitor the blade
Temperature.
In some more specific embodiment, the temperature measurement module uses infrared temperature measurement device.
Further, the displacement monitoring unit includes acquisition module, laser displacement sensor, the laser displacement sensing
Device is used for the vibration amplitude for monitoring the specified location on the blade；The strain monitoring unit includes foil gauge, described to answer
Become the specified location that piece is installed on blade, the acquisition module is connected with laser displacement sensor and foil gauge respectively.
Further, the vibration generating unit includes shake table, blade fixture, power amplifier and signal generator,
The blade is fixed on by blade fixture on the work top of the shake table, the signal generator and the displacement monitoring
Unit is connected with power amplifier.
Further, described device further includes cooling unit, the cooling unit be at least used for the blade fixture into
Row cooling treatment.
Further, the cooling unit is included to provide the cooler bin of cooling medium, and the cooler bin is passed through with pump
Cooling medium stream siphunculus road be connected with blade fixture.
Further, the cooling unit further includes cooling medium recovery device, the cooling medium recovery device with it is cold
But case connects.
The technical solution, its implementation process and principle etc. will be further explained with reference to attached drawing as follows.
Referring to Fig. 1, a kind of blade of aviation engine high-temperature high-frequency fatigue life test device, including：
High-temperature control unit 2, including infrared temperature measurement device 21, power governor 22 and heating generator 23, high-frequency heating
Device 23 includes an at least induction coil, and induction coil is non-contacting to be set on blade, and induction coil is electrically connected with high frequency electric source
And for making blade carry out spontaneous heating heating, infrared temperature measurement device 21 can monitor the temperature of blade 1, and power governor 22 is according to red
The temperature value that outer thermal detector 21 obtains adjusts the output power of heating generator 23, and the host of heating generator is by common power
Become low-voltage high-frequency high current, induction coil around induction coil by that can form stronger height after low-voltage high-frequency high current
Frequency magnetic field, blade sensing electric current for producing under high frequency magnetic field effect, the magnetic hystersis loss in magnetic field draws in eddy-current loss and blade
Play blade self-heating and the temperature of blade is increased to operating temperature；
Displacement and strain monitoring unit 3, including displacement monitoring unit and strain monitoring unit, displacement monitoring unit include swashing
Optical displacement sensor 31 and acquisition module 33, strain monitoring unit include foil gauge 32, and foil gauge 32 is arranged at specifying for blade
At position, laser displacement sensor 31 can monitor the amplitude of blade specified location, and foil gauge 32 can monitor blade and specify
Strain at position, acquisition module 33 can obtain the monitoring information of laser displacement sensor 31 and foil gauge 32；
Generating unit 4 is vibrated, includes the blade fixture 41 of fixed blade 1, shake table 42, power amplifier 43 and signal
Generator 43, blade 1 are fixed on by blade fixture 41 on the work top of shake table 42, and signal generator 43 is put by power
Big device 42 controls the vibration frequency and vibration level of shake table 42；Signal generator 43 is also connected with acquisition module 33, collection
The amplitude for the blade specified location that module 33 obtains and strain just adjust the vibration frequency and vibration level of shake table；
Cooling unit 5, including to provide the cooling of cooling medium, 52, the cooler bin 52 is through the cooling with pump 51
Flow of media pipeline is connected with blade fixture 41.
In some more specific embodiment, cooling unit further includes cooling medium recovery device, and cooling medium returns
Receiving apparatus is connected with cooler bin 52, and used coolant is recycled in cooler bin 52 and is recycled.
Blade of aviation engine high-temperature high-frequency fatigue life test device provided by the utility model can make aeroplane engine
Machine leaf temperature fast lifting is to operating temperature, and the fatigue life for keeping at these elevated temperatures, carrying out under different vibration levels surveys
Examination.
It should be appreciated that above-described embodiment is only the technical concepts and features for illustrating the utility model, it is ripe its object is to allow
The content of the utility model can be understood and implement according to this by knowing the personage of technique, can not limit the utility model with this
Protection domain.All equivalent change or modifications made according to the utility model Spirit Essence, should all cover in the utility model
Within protection domain.
Claims (8)
1. a kind of blade of aviation engine high-temperature high-frequency fatigue life test device, it is characterised in that the test device includes：
At least to the high-temperature control unit that the temperature of blade is adjusted, it includes heating generator, the high-frequency heating
Device includes an at least induction coil, and the induction coil is non-contactly sheathed on blade, the induction coil and high frequency electric source
It is electrically connected and is used to make the blade spontaneous heating heat up,
Generating unit is vibrated, at least to provide the vibration frequency and vibration level that are carried out to the blade needed for testing fatigue,
Displacement monitoring unit, at least monitoring the vibration amplitude of the specified location on blade
Strain monitoring unit, at least to monitor the strain value of the specified location on blade,
The displacement monitoring unit is connected with strain monitoring unit and vibration generating unit respectively, and the blade is fixed on described shake
On the work top of shake table in dynamic generating unit, the high-temperature control unit is connected with the blade.
2. blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 1, it is characterised in that：Institute
State high-temperature control unit and further include temperature measurement module and power governor, the heating generator is connected with power governor, described
Power governor is connected with temperature measurement module, and the temperature measurement module is at least used for the temperature for monitoring the blade.
3. blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 2, it is characterised in that：Institute
State temperature measurement module and use infrared temperature measurement device.
4. blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 1, it is characterised in that：Institute
Rheme, which moves monitoring unit, includes acquisition module, laser displacement sensor, and the laser displacement sensor is used to monitor the blade
On specified location vibration amplitude；The strain monitoring unit includes foil gauge, and the foil gauge is installed on blade
Specified location, the acquisition module are connected with laser displacement sensor and foil gauge respectively.
5. the blade of aviation engine high-temperature high-frequency fatigue life test device according to any one of claim 1-4, its
It is characterized in that：The vibration generating unit includes shake table, blade fixture, power amplifier and signal generator, the blade
It is fixed on by blade fixture on the work top of the shake table, the signal generator and the displacement monitoring unit and work(
Rate amplifier connects.
6. blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 5, it is characterised in that also
Including cooling unit, the cooling unit is at least used to carry out cooling treatment to the blade fixture.
7. blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 6, it is characterised in that：Institute
State cooling unit include to provide cooling medium cooler bin, the cooler bin pass through with pump cooling medium stream siphunculus road with
Blade fixture connects.
8. the blade of aviation engine high-temperature high-frequency fatigue life test device according to claim 6 or 7, its feature exist
In：The cooling unit further includes cooling medium recovery device, and the cooling medium recovery device is connected with cooler bin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721270769.0U CN207263431U (en) | 2017-09-29 | 2017-09-29 | Blade of aviation engine high-temperature high-frequency fatigue life test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721270769.0U CN207263431U (en) | 2017-09-29 | 2017-09-29 | Blade of aviation engine high-temperature high-frequency fatigue life test device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207263431U true CN207263431U (en) | 2018-04-20 |
Family
ID=61919459
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721270769.0U Active CN207263431U (en) | 2017-09-29 | 2017-09-29 | Blade of aviation engine high-temperature high-frequency fatigue life test device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110426208A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of high temperature strain gauge mounting process device for verifying reliability |
| WO2019227639A1 (en) * | 2018-06-01 | 2019-12-05 | 东北大学 | Reliability testing device for composite material propeller blade of rotor unmanned aerial vehicle in windy and sandy environments |
| CN113310700A (en) * | 2021-05-27 | 2021-08-27 | 北京航空航天大学 | System for testing fatigue life of cooling channel |
-
2017
- 2017-09-29 CN CN201721270769.0U patent/CN207263431U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019227639A1 (en) * | 2018-06-01 | 2019-12-05 | 东北大学 | Reliability testing device for composite material propeller blade of rotor unmanned aerial vehicle in windy and sandy environments |
| CN110426208A (en) * | 2019-08-13 | 2019-11-08 | 中国航发贵阳发动机设计研究所 | A kind of high temperature strain gauge mounting process device for verifying reliability |
| CN113310700A (en) * | 2021-05-27 | 2021-08-27 | 北京航空航天大学 | System for testing fatigue life of cooling channel |
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