CN105203310B - A kind of Axle Parts load calibration method and system of aero-engine - Google Patents
A kind of Axle Parts load calibration method and system of aero-engine Download PDFInfo
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- CN105203310B CN105203310B CN201510593205.XA CN201510593205A CN105203310B CN 105203310 B CN105203310 B CN 105203310B CN 201510593205 A CN201510593205 A CN 201510593205A CN 105203310 B CN105203310 B CN 105203310B
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Abstract
The invention discloses a kind of Axle Parts load calibration method and system of aero-engine.The Axle Parts load calibration method of the aero-engine includes：Step 1：Default test objective, and according to the default loaded load under the conditions of default test objective setting different loads；Step 2：Stress and strain value is obtained by test method and calculation and analysis methods respectively, and obtains Load correction factor；Step 3：Default loaded load is corrected, so as to obtain correcting loaded load；Step 4：The stress and strain value of Axle Parts to be measured is obtained, and the stress and strain value for judging to obtain is whether within default error；Step 5：Repeat step 2 to 4, until judging result is yes.In the Axle Parts load calibration system of the aero-engine of the present invention, the calibration of each separate loading is carried out first, then demarcate the calibration that each load loads jointly again, have it is workable, the degree of automation is high, improve aero-engine main shaft class experiment complex load loading accuracy.
Description
Technical field
The present invention relates to stryctyrak test technical field, more particularly to a kind of Axle Parts load of aero-engine
The Axle Parts load calibration system of scaling method and aero-engine.
Background technology
Engine shaft base part stress is complicated, and that is mainly examined in experiment has main moment of torsion, axial force, vibration moment of torsion and rotation
Bending load, test load are all applied indirectly on testpieces.Although from exerciser Machine Design angle, load is reduced to the greatest extent
Interfering with each other between lotus, but under the effect of high frequency load, it is subject to load and execution mechanism inertia force, exerciser fault in material not
Uniformly, assembler difference it is uneven and dead weight etc. factor influence, four kinds of load transmissions can not be obtained to each load on testpieces
Lotus actual value, and the relation of corresponding loading pressurized strut power output.This brings many problems to accurately loading for test load.
Thus, it is desirable to have a kind of technical solution is come at least one drawbacks described above for overcoming or at least mitigating the prior art.
The content of the invention
It is an object of the invention to provide a kind of Axle Parts load calibration system of aero-engine to overcome or at least
Mitigate at least one drawbacks described above in the prior art.
To achieve the above object, the present invention provides a kind of Axle Parts load calibration method of aero-engine, the boat
The Axle Parts load calibration method of empty engine includes：Step 1：Default test objective, and set according to default test objective
Default loaded load under the conditions of different loads；Step 2：Axis to be measured is obtained by test method and calculation and analysis methods respectively
Stress and strain value of the base part under the default loaded load of different loads condition, and pass through calculation and analysis methods and experiment
Stress and strain value under each load-up condition that method obtains tries to achieve the Load correction factor under corresponding load-up condition；Step
Rapid 3：Default loaded load under the conditions of different loads is corrected by each Load correction factor, so as to obtain different loads bar
Amendment loaded load under part；Step 4：Load the amendment loading load under the conditions of each different loads at the same time for Axle Parts to be measured
Lotus, obtains Axle Parts to be measured in each amendment loaded load collective effect by test method and calculation and analysis methods respectively
Under stress and strain value, and judge by test method obtain Axle Parts to be measured ess-strain value with it is described calculate divide
Whether the stress and strain value for the Axle Parts to be measured that analysis method obtains is in default error deltaΔWithin, if so, then terminating to demarcate；If
It is no, then carry out in next step；Step 5：Repeating said steps 2 are to the step 4, until the judging result in the step 4 is yes.
Preferably, the different loads condition in the step 1 specifically includes：Main torque load condition, axial force load bar
Part, vibration torque load condition and rotation bending load condition.
Preferably, the calculation and analysis methods include analytic method and FInite Element；Between the two with the following method into
Row method choice：Judge whether the geometry of the cross section of the Axle Parts to be measured regular, and the test method into
Whether there are various stress concentration factors in test point during row experiment, if it is not, then selecting analytic method；If so, then select finite element
Method.
Preferably, the different stress and strains obtained by calculation and analysis methods and test method in the step 2
The Load correction factor that value is tried to achieve under corresponding load-up condition is specially：
δk=εkFEA/εkTEST=σkFEA/σkTEST；
Wherein δkFor the Load correction factor of kth load-up condition；K=1,2,3,4 represent main torque load condition, axis respectively
To power load-up condition, vibration torque load condition and rotation bending load condition；σkFEAAnd εkFEARespectively load kth load bar
The stress and strain value that part is obtained by calculation and analysis methods；σkTESTAnd εkTESTRespectively loading kth load-up condition passes through experiment
The stress and strain value that method obtains.
Preferably, being added by each Load correction factor to correct presetting under the conditions of different loads in the step 3
Load is carried, so that the step of amendment loaded load under the conditions of obtaining different loads is specially：Fk IN=δk×Fk, wherein Fk INFor
Load the amendment loaded load of kth load-up condition；δkFor the Load correction factor of kth load-up condition；FkTo load kth load bar
The default loaded load of part；K=1,2,3,4 represent main torque load condition, axial force load-up condition, vibration torque load respectively
Condition and rotation bending load condition.
Preferably, the default error is specially：δΔ=(εeq FEA-εeq TEST)εeq FEA× 100%=(σeq FEA-σeq TEST)
σeq FEA× 100%, wherein δΔTo load the error under the conditions of each different loads at the same time；σeq FEAAnd εeq FEARespectively add at the same time
Carry the equivalent stress and equivalent strain value obtained under the conditions of each different loads by calculation and analysis methods；σeq TESTAnd εeq TESTPoint
The equivalent stress and equivalent strain value obtained under the conditions of each different loads by test method Wei not be loaded at the same time.
Present invention also offers a kind of Axle Parts load calibration system of aero-engine, the axis of the aero-engine
Base part load calibration system is used for the Axle Parts load calibration method of aero-engine as described above, the aeroplane engine
The Axle Parts load calibration system of machine includes：Loading device, the loading device are used to be loaded for Axle Parts to be measured
Load；Caliberating device, the caliberating device are connected with the loading device, the caliberating device be used for for Axle Parts to be measured into
The repetition calibration of row load, and loading device is fed back to, loading device is changed institute's loaded load；Measuring device, the measurement
Device is arranged on Axle Parts to be measured, and the measuring device is used to measure size of the loading in the load of Axle Parts to be measured.
Preferably, the caliberating device includes：Data acquisition unit, the data acquisition unit are filled with the loading respectively
Put and measuring device connection, the data acquisition unit are used to gather the loading device and the number of the measuring device
According to；Control unit, described control unit are connected with the data acquisition unit and loading device, and described control unit is used for root
According to the data that data acquisition unit is gathered action command is assigned to the loading device.
Preferably, the data acquisition unit includes：Signal receiving module, the signal receiving module are used to receive described
The data of loading device and the measuring device；Testing control module, the testing control module are used for real-time assumed (specified) load
Value, and by load value real-time delivery to control unit.
In the Axle Parts load calibration system of the aero-engine of the present invention, the mark of each separate loading is carried out first
It is fixed, the calibration that each load loads jointly is then demarcated again, so that relative to the prior art, there is workable, automation
Degree is high, versatile, improves the loading accuracy of aero-engine main shaft class experiment complex load.
Brief description of the drawings
Fig. 1 is the flow diagram of the Axle Parts load calibration method of the aero-engine of one embodiment of the invention.
Embodiment
To make the purpose, technical scheme and advantage that the present invention is implemented clearer, below in conjunction with the embodiment of the present invention
Attached drawing, the technical solution in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label represent same or similar element or there is same or like element.Described embodiment is the present invention
Part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to uses
It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiments of the present invention, ordinary skill people
Member's all other embodiments obtained without creative efforts, belong to the scope of protection of the invention.Under
Face is described in detail the embodiment of the present invention with reference to attached drawing.
In the description of the present invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on attached drawing institutes
The orientation or position relationship shown, is for only for ease of the description present invention and simplifies description, rather than instruction or the dress for implying meaning
Put or element there must be specific orientation, with specific azimuth configuration and operation, therefore it is not intended that the present invention is protected
The limitation of scope.
Fig. 1 is the flow diagram of the Axle Parts load calibration method of the aero-engine of one embodiment of the invention.
The Axle Parts load calibration method of aero-engine as shown in Figure 1 includes：
Step 1：Default test objective, and carried according to the default loading under the conditions of default test objective setting different loads
Lotus；Specifically, the different loads condition in step 1 specifically includes：Main torque load condition, axial force load-up condition, vibration are turned round
Square load-up condition and rotation bending load condition.
Step 2：Axle Parts to be measured are obtained in different loads condition by test method and calculation and analysis methods respectively
Default loaded load under stress and strain value, and pass through each load bar that calculation and analysis methods and test method obtain
Stress and strain value under part tries to achieve the Load correction factor under corresponding load-up condition；
Step 3：Default loaded load under the conditions of different loads is corrected by each Load correction factor, so as to obtain
Amendment loaded load under the conditions of different loads；
Step 4：Load the amendment loaded load under the conditions of each different loads at the same time for Axle Parts to be measured, pass through respectively
Test method and calculation and analysis methods obtain stress of the Axle Parts to be measured under each amendment loaded load collective effect and
Strain value, and the stress and strain value for the Axle Parts to be measured for judging to obtain by test method is obtained with the calculation and analysis methods
Whether the stress and strain value of the Axle Parts to be measured taken is in default error deltaΔWithin, if so, then terminating to demarcate；If it is not, then into
Row is in next step；
Step 5：Repeating said steps 2 are to the step 4, until the judging result in the step 4 is yes.
In above-mentioned, error delta is presetΔValue range between 3% to 10% value, its specific value can pass through examination
Test depending on the required accuracy and experiment specific requirement.
Specifically, the calculation and analysis methods in above-mentioned steps include analytic method and FInite Element；Between the two using such as
Lower method carries out method choice：
Judge whether the geometry of the cross section of Axle Parts to be measured is regular, and tested when test method is tested
Whether there are various stress concentration factors on point, if it is not, then selecting analytic method；If so, then select FInite Element.
The different stress and strain values obtained by calculation and analysis methods and test method in the step 2 try to achieve phase
Load correction factor under corresponding load-up condition is specially：
δk=εkFEA/εkTEST=σkFEA/σkTEST；
Wherein δkFor the Load correction factor of kth load-up condition；K=1,2,3,4 represent main torque load condition, axis respectively
To power load-up condition, vibration torque load condition and rotation bending load condition；σkFEAAnd εkFEARespectively load kth load bar
The stress and strain value that part is obtained by calculation and analysis methods；σkTESTAnd εkTESTRespectively loading kth load-up condition passes through experiment
The stress and strain value that method obtains.
The default loaded load under the conditions of different loads is corrected by each Load correction factor in the step 3,
So as to be specially the step of obtaining the amendment loaded load under the conditions of different loads：Fk IN=δk×Fk, wherein Fk INTo load kth
The amendment loaded load of load-up condition；δkFor the Load correction factor of kth load-up condition；FkFor the default of loading kth load-up condition
Loaded load；K=1,2,3,4 represent main torque load condition, axial force load-up condition, vibration torque load condition and rotation respectively
Turning square load-up condition.
The default error is specially：δΔ=(εeq FEA-εeq TEST)εeq FEA× 100%=(σeq FEA-σeq TEST)σeq FEA×
100%, wherein δΔTo load the error under the conditions of each different loads at the same time；σeq FEAAnd εeq FEARespectively load at the same time each
The equivalent stress and equivalent strain value obtained under the conditions of different loads by calculation and analysis methods；σeq TESTAnd εeq TESTIt is respectively same
When load the equivalent stress and equivalent strain value obtained by test method under the conditions of each different loads.
In the foregoing description, equivalent stress can be tried to achieve by stress by formula.It is understood that the formula is known
's.In order to describe conveniently, the formula listed here：
Equivalent stress：σeq=1/21/2×{(σx-σy)2+(σy-σz)2+(σx-σz)2+6(τ2 xy+τ2 yz+τ2 xz)}1/2
In the foregoing description, equivalent strain can be tried to achieve by straining by formula.It is understood that the formula is known
's.In order to describe conveniently, the formula listed here：
Equivalent strain：εeq=1/21/2×{(εx-εy)2+(εy-εz)2+(εx-εz)2+6(γ2 xy+γ2 yz+γ2 xz)}1/2。
The Axle Parts load calibration system of the aero-engine of the present invention, carries out the calibration of each separate loading first, after
And the calibration that each load loads jointly is demarcated again, so that relative to the prior art, there is workable, the degree of automation
It is high, versatile, improve the loading accuracy of aero-engine main shaft class experiment complex load.
A kind of modeling is additionally provided in the present invention, which is used for realization above-described embodiment and is preferable to carry out
Mode, had carried out repeating no more for explanation in above-mentioned.As used below, term " unit or module " is can be with
Realize the combination of the software and/or hardware of predetermined function.Although the described device of following embodiments is preferable to realize with software,
However, by hardware, or the implementation of the combination of software and hardware is also that may and be contemplated.
Present invention also offers a kind of Axle Parts load calibration system of aero-engine, the axis of the aero-engine
Base part load calibration system is used for the Axle Parts load calibration method of aero-engine as described above, the aeroplane engine
The Axle Parts load calibration system of machine includes：
Loading device, the loading device are used to carry out loaded load for Axle Parts to be measured；
Caliberating device, the caliberating device are connected with the loading device, and it is axis class portion to be measured that the caliberating device, which is used for,
Part carries out the repetition calibration of load, and feeds back to loading device, loading device is changed institute's loaded load；
Measuring device, the measuring device are arranged on Axle Parts to be measured, and the measuring device is used to measure to load and exists
The size of the load of Axle Parts to be measured.
In the present embodiment, the caliberating device includes：Data acquisition unit and control unit, the data acquisition list
Member be connected respectively with the loading device and measuring device, the data acquisition unit for gather the loading device and
The data of the measuring device；Described control unit is connected with the data acquisition unit and loading device, and the control is single
Member is used to assign action command to the loading device according to the data that data acquisition unit is gathered.
In the present embodiment, the data acquisition unit includes：Signal receiving module and testing control module, the letter
Number receiving module is used for the data for receiving the loading device and the measuring device；The testing control module is used for real-time
Assumed (specified) load value, and by load value real-time delivery to control unit.
In embodiment provided by the present invention, it should be understood that disclosed relevant apparatus and method, can pass through it
His mode is realized.For example, device described above is only schematical, for example, the division of the module and unit, only
Only a kind of division of logic function, can there is other dividing mode when actually realizing, such as multiple units or component can be tied
Another system is closed or is desirably integrated into, or some features can be ignored, or do not perform.It is another, it is shown or discussed
Mutual coupling, direct-coupling or communication connection can be the INDIRECT COUPLING or logical by some interfaces, device or unit
Believe overlooking, can be electrical, mechanical or other forms.
The unit illustrated as separating component may or may not be physically separate, be shown as unit
The component shown may or may not be physical location, you can with positioned at a place, or can also be distributed to multiple network unit
On.Some or all of unit therein can be selected to realize the purpose of this embodiment scheme according to the actual needs.
In addition, each functional unit in an embodiment of the present invention can be integrated in a processing unit or
Unit is individually physically present, can also two or more units integrate in a unit.Above-mentioned integrated unit
Both it can be realized, can also be realized in the form of SFU software functional unit in the form of hardware.
If the integrated unit is realized in the form of SFU software functional unit and is used as independent production marketing or use
When, it can be stored in a computer read/write memory medium, based on such understanding, technical scheme is substantially
The part to contribute in other words to the prior art or all or part of the technical solution can be in the form of software products
Embody, which is stored in a storage medium, including some instructions are making computer processor
Perform all or part of step of each embodiment the method for the present invention.And foregoing storage medium includes USB flash disk, movement firmly
Disk, read-only storage, random access memory, magnetic disc or CD etc. are various can be with the medium of store program codes.
It is last it is to be noted that：The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations.To the greatest extent
Pipe is with reference to the foregoing embodiments described in detail the present invention, it will be understood by those of ordinary skill in the art that：It is still
It can modify to the technical solution described in foregoing embodiments, or which part technical characteristic is equally replaced
Change；And these modifications or replacement, the essence of appropriate technical solution is departed from the essence of various embodiments of the present invention technical solution
God and scope.
Claims (9)
1. a kind of Axle Parts load calibration method of aero-engine, it is characterised in that the axis class portion of the aero-engine
Part load calibration method includes：
Step 1：Default test objective, and according to the default loaded load under the conditions of default test objective setting different loads；
Step 2：Axle Parts to be measured are obtained in the pre- of different loads condition by test method and calculation and analysis methods respectively
If the stress and strain value under loaded load, and by under calculation and analysis methods and each load-up condition of test method acquisition
Stress and strain value try to achieve Load correction factor under corresponding load-up condition；
Step 3：Default loaded load under the conditions of different loads is corrected by each Load correction factor, so as to obtain difference
Amendment loaded load under load-up condition；
Step 4：Load the amendment loaded load under the conditions of each different loads at the same time for Axle Parts to be measured, pass through experiment respectively
Method and calculation and analysis methods obtain stress and strain of the Axle Parts to be measured under each amendment loaded load collective effect
Value, and the ess-strain value for the Axle Parts to be measured for judging to obtain by test method is treated with what the calculation and analysis methods obtained
The stress and strain value of Axle Parts is surveyed whether in default error deltaΔWithin, if so, then terminating to demarcate；If it is not, then carry out next
Step；
Step 5：Repeating said steps 2 are to the step 4, until the judging result in the step 4 is yes.
2. the Axle Parts load calibration method of aero-engine as claimed in claim 1, it is characterised in that the step 1
In different loads condition specifically include：Main torque load condition, axial force load-up condition, vibration torque load condition and rotation
Bending load condition.
3. the Axle Parts load calibration method of aero-engine as claimed in claim 1, it is characterised in that described calculate is divided
Analysis method includes analytic method and FInite Element；Carry out method choice with the following method between the two：
Judge whether the geometry of the cross section of the Axle Parts to be measured is regular, and when the test method is tested
Whether there are various stress concentration factors in test point, if it is not, then selecting analytic method；If so, then select FInite Element.
4. the Axle Parts load calibration method of aero-engine as claimed in claim 1, it is characterised in that the step 2
In the different stress and strain values obtained by calculation and analysis methods and test method try to achieve under corresponding load-up condition
Load correction factor be specially：
δk=εkFEA/εkTEST=σkFEA/σkTEST；
Wherein δkFor the Load correction factor of kth load-up condition；K=1,2,3,4 represent main torque load condition, axial force respectively
Load-up condition, vibration torque load condition and rotation bending load condition；σkFEAAnd εkFEARespectively loading kth load-up condition leads to
Cross the stress and strain value of calculation and analysis methods acquisition；σkTESTAnd εkTESTRespectively loading kth load-up condition passes through test method
The stress and strain value of acquisition.
5. the Axle Parts load calibration method of aero-engine as claimed in claim 1, it is characterised in that the step 3
In the default loaded load under the conditions of different loads is corrected by each Load correction factor, so as to obtain different loads bar
The step of amendment loaded load under part is specially：Fk IN=δk×Fk, wherein Fk INTo load the amendment of kth load-up condition loading
Load；δkFor the Load correction factor of kth load-up condition；FkTo load the default loaded load of kth load-up condition；K=1,2,3,
4 represent main torque load condition, axial force load-up condition, vibration torque load condition and rotation bending load condition respectively.
6. the Axle Parts load calibration method of aero-engine as claimed in claim 1, it is characterised in that the default mistake
Difference is specially：δΔ=(εeq FEA-εeq TEST)εeq FEA× 100%=(σeq FEA-σeq TEST)σeq FEA× 100%, wherein δΔTo add at the same time
Carry the error under the conditions of each different loads；σeq FEAAnd εeq FEARespectively load at the same time under the conditions of each different loads and pass through meter
Calculate equivalent stress and equivalent strain value that analysis method obtains；σeq TESTAnd εeq TESTRespectively load each different loads bar at the same time
The equivalent stress and equivalent strain value obtained under part by test method.
A kind of 7. Axle Parts load calibration system of aero-engine, it is characterised in that the axis class portion of the aero-engine
Part load calibration system is used for the Axle Parts load calibration of the aero-engine as described in any one in claim 1 to 6
Method, the Axle Parts load calibration system of the aero-engine include：
Loading device, the loading device are used to carry out loaded load for Axle Parts to be measured；
Caliberating device, the caliberating device are connected with the loading device, the caliberating device be used for for Axle Parts to be measured into
The repetition calibration of row load, and loading device is fed back to, loading device is changed institute's loaded load；
Measuring device, the measuring device are arranged on Axle Parts to be measured, and the measuring device is used to measure loading to be measured
The size of the load of Axle Parts.
8. the Axle Parts load calibration system of aero-engine as claimed in claim 7, it is characterised in that the calibration dress
Put including：
Data acquisition unit, the data acquisition unit are connected with the loading device and measuring device respectively, the data
Collecting unit is used for the data for gathering the loading device and the measuring device；
Control unit, described control unit are connected with the data acquisition unit and loading device, and described control unit is used for
According to the data that data acquisition unit is gathered action command is assigned to the loading device.
9. the Axle Parts load calibration system of aero-engine as claimed in claim 8, it is characterised in that the data are adopted
Collection unit includes：
Signal receiving module, the signal receiving module are used for the data for receiving the loading device and the measuring device；
Testing control module, the testing control module are used for real-time assumed (specified) load value, and by load value real-time delivery to control
Unit.
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| CN108133075A (en) * | 2017-11-29 | 2018-06-08 | 中国飞机强度研究所 | A kind of aero-engine Axle Parts support stiffness simulator |
| CN110135044B (en) * | 2019-05-09 | 2023-05-26 | 中国飞机强度研究所 | Method for calculating test load of aircraft fuselage curved plate |
| CN110920930B (en) * | 2019-12-04 | 2022-09-13 | 中国直升机设计研究所 | Helicopter horizontal tail load calibration method |
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