CN104458236B - A kind of booster turbine center portion intensity accelerated test verification method - Google Patents
A kind of booster turbine center portion intensity accelerated test verification method Download PDFInfo
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Abstract
The present invention relates to a kind of booster turbine center portion intensity accelerated test verification method, the working status parameter change course of booster turbine correspondence engine mission profile is determined first, it is then determined that turbine center portion failure dangerous position and its fatigue stress, turbine center portion fatigue strength and Life Relation are determined by designing turbine center portion strength simulation experiment exemplar and carrying out fatigue property test, determine turbine center portion intensity accelerated test maximum speed and corresponding accelerated test stress, work out turbine center portion intensity stand accelerated test section, then turbine center portion intensity acceleration checking test section cycle-index is determined, accelerated test checking finally is carried out to turbine center portion intensity on turbocharger test stand.Can be on test-bed using verification experimental verification of the shorter test period realization to booster turbine center portion intensity, test efficiency can be obviously improved, shortens test period, save experimentation cost, is that booster turbine reliability evaluation and reasonable employment provide scientific basis.
Description
Technical field
Evaluated the invention belongs to booster turbine structural reliability and its verification experimental verification technology, and in particular to a kind of booster
Turbine center portion intensity accelerated test verification method.
Background technology
Turbocharger is the critical component that vehicular engine realizes power density lifting and enhancing altitude environment adaptability
One of, turbine is as the kernel component of turbocharger, and its reliability directly affects turbocharger and whole engine
Reliability and service life.Because the maximum stress of booster turbine is usually found in the center portion of turbine, while being cast
The restriction turbine center portion intensity of technique can typically be less than other positions, therefore, and turbine center portion is to determine turbine reliability and life-span
One of key position.
Vehicle turbocharger with engine in use, due to the polytropy of vehicular engine operating condition,
The working status parameters such as the rotating speed of turbocharger bear turbine center portion being constantly occurring change, the change of supercharger speed
The effect of alternate load.Fatigue rupture can occur in the presence of alternate load for turbine center portion, and cause turbine to disperse.Supercharging
Device turbine disperses once occurring fatigue, booster and engine is not worked, and be possible to cause booster and
The bigger damage of engine.Therefore, in the development process of turbocharger, it is quite necessary to the center portion fatigue strength of turbine
Carry out sufficient theory analysis and effective verification experimental verification.
Although on test-bed by simulate the mission profile of turbocharger carry out prolonged certification test can be with
The center portion intensity of booster turbine is effectively verified, it is still, tested because the projected life of booster turbine is universal all long
The limitation of the factors such as time, experimental condition, experimentation cost is tested, it is this to be cutd open on test-bed according to turbocharger task
The method that verification experimental verification is carried out in face of turbine center portion intensity, it is in practice and infeasible in engineering.
The content of the invention
There is provided a kind of booster turbine with verification experimental verification problem for structural reliability evaluation of the invention for booster turbine
Center portion intensity accelerated test verification method.It is determined that turbo operating state Parameters variation course, turbine center portion failure dangerous position
And its on the basis of fatigue stress, turbine center portion fatigue strength and Life Relation, determine turbine center portion failure dangerous position correspondence
Provide the accumulated damage amount of service life；According to turbocharger test rig ability and the maximum permissible revolution of booster safe handling,
Determine turbine center portion intensity accelerated test stress, and further determine that booster turbine center portion intensity stand accelerated test section and
Its cycle-index；Then, turbine core portion intensity is carried out on booster stand according to test profile and its cycle-index and accelerates examination
Checking.
Technical solution of the present invention：
A kind of booster turbine center portion intensity accelerated test verification method, it is characterized in that comprising the following steps：
A, the working status parameter change course for determining booster turbine correspondence engine mission profile；
B, determine turbine center portion failure dangerous position and its fatigue stress；
C, the fatigue strength and Life Relation for determining turbine center portion；
D, the accumulated damage amount for determining turbine center portion failure dangerous position correspondence regulation service life；
E, the center portion intensity acceleration checking test stress for determining turbine；
F, determine booster turbine center portion intensity stand accelerated test section and its cycle-index；
G, the progress turbine core portion intensity accelerated test checking on turbocharger stand.
A kind of booster turbine center portion intensity accelerated test verification method, it is characterized in that comprising the following steps：
A, the working status parameter change course for determining booster turbine correspondence engine mission profile：Appoint with reference to engine
Business section, emulated computation method is used by testing method or according to turbocharger and engine performance matching relationship,
The working status parameter change course of mission profile circulation of booster turbine correspondence engine is determined, includes turn of turbine
Fast change course, inlet temperature change course, outlet temperature change course, inlet pressure change course, outlet pressure change are gone through
Journey and gas flow change course；
B, determine turbine center portion failure dangerous position and its fatigue stress：The booster turbine work according to determined by step a
Make state parameter change course, stress analysis is carried out to turbine using finite element method, determine the center portion failure danger portion of turbine
The Simulating of Fatigue Stress Spectra of booster turbine center portion failure dangerous position during the mission profile circulation in position and correspondence engine；
C, the fatigue strength and Life Relation for determining turbine center portion：Failed according to the turbine center portion determined in step b dangerous
Position and its stress, determine that turbine center portion strength simulation tests exemplar sampling method, center portion strength simulation experiment exemplar will
Failure dangerous position comprising turbine center portion, along turbine radially be sampled, by fatigue tester according to pulsating cyclic
Load mode carries out fatigue property test to turbine center portion strength simulation experiment exemplar, determines the turbine core as shown in formula (1)
Portion fatigue strength S and life-span N relational model
N=FS-N(S) (1)；
D, the accumulated damage amount for determining turbine center portion failure dangerous position correspondence regulation service life：According to turbocharger
Defined service life, determines the mission profile circulation total degree that turbocharger is undergone within the guideline lives phase, enters one
Step, with reference to the Simulating of Fatigue Stress Spectra and the turbine center portion fatigue of step c determinations of the step b turbine center portion failure dangerous positions determined
Intensity and Life Relation model, calculate accumulated damage amount D of the turbine center portion failure dangerous position in regulation service lifeT；
E, the center portion intensity acceleration checking test stress for determining booster turbine：According to turbocharger test platform ability with
Booster is capable of the maximum permissible revolution n of safe handling on test-bedmax, determine to increase during turbine center portion intensity accelerated test
The highest test speed n of depressorAT, highest test speed nATIt should be greater than turbocharger normal work under engine mission profile
Highest working speed n when makingN, but must not exceed booster maximum permissible revolution nmax, further determined by stress analysis
Go out correspondence booster highest test speed nATWhen turbine center portion intensity acceleration checking test stress sAT；
F, the acceleration checking test section and its cycle-index for determining booster turbine center portion intensity：Determined according to step e
Highest test speed nATWith acceptable test period, booster turbine center portion intensity stand accelerated test section is worked out,
Test cycle of test profile is " lowest continuous speed with load-highest test speed nAT- lowest continuous speed with load ", its
In, booster is 0.2-5 points in the run time of lowest continuous speed with load, in highest test speed nATRun time be
0.2-5 points；Using the equivalent principle of accumulated damage, the turbine center portion fatigue strength determined according to step c and Life Relation model,
Accumulated damage amount D of the turbine center portion failure dangerous position that step d is determined in regulation service lifeTAnd step e determinations
Turbine center portion intensity acceleration checking test stress SAT, determine that turbine center portion intensity acceleration checking test section is circulated with formula (2)
Times NAT, i.e.,
NAT=DTFS-N(sAT) (2)；
G, the progress turbine core portion intensity accelerated test checking on turbocharger stand.The supercharging determined according to step f
Device turbine center portion intensity stand accelerated test section and its cycle-index, carry out turbine core portion intensity on turbocharger test rig frame
To control booster turbine inlet temperature to must not exceed permissible value in verification experimental verification, process of the test, and test cycle number of times is entered
Row is counted, when test cycle number of times reaches NATAfterwards, reduction of speed parking is carried out to turbocharger, torn open after after booster cooling
Inspection, such as turbine stand intact, then can determine that booster turbine center portion intensity disclosure satisfy that defined use requirement.
The present invention has the advantages that compared with prior art：
Should by changing course, turbine center portion failure dangerous position and its fatigue to booster turbine working status parameter
Power, turbine center portion fatigue strength and Life Relation etc. are analyzed, and determine turbine center portion intensity accelerated test maximum speed and right
The acceleration checking test stress answered, works out booster turbine center portion intensity stand accelerated test section, equivalent using accumulated damage
Principle determines turbine center portion intensity acceleration checking test section cycle-index, is accelerated to try according to the turbine center portion intensity stand of determination
Section and its cycle-index are tested, on turbocharger test stand shorter test period can be used to realize to turbine center portion
The accelerated test checking of intensity, can be obviously improved the verification experimental verification efficiency of booster turbine center portion intensity, effectively shorten experiment
Time, and experimentation cost is reduced, provide scientific basis for the reliability evaluation and reasonable employment of booster turbine.
Brief description of the drawings
Fig. 1 is booster turbine center portion intensity accelerated test verification method flow.
Embodiment
A kind of booster turbine center portion intensity accelerated test verification method, comprises the following steps：
A, the working status parameter change course for determining booster turbine correspondence engine mission profile：Appoint with reference to engine
Business section, emulated computation method is used by testing method or according to turbocharger and engine performance matching relationship,
The working status parameter change course of mission profile circulation of booster turbine correspondence engine is determined, includes turn of turbine
Fast change course, inlet temperature change course, outlet temperature change course, inlet pressure change course, outlet pressure change are gone through
Journey and gas flow change course；
B, determine turbine center portion failure dangerous position and its fatigue stress：The booster turbine work according to determined by step a
Make state parameter change course, stress analysis is carried out to turbine using finite element method, determine the center portion failure danger portion of turbine
The Simulating of Fatigue Stress Spectra of booster turbine center portion failure dangerous position during the mission profile circulation in position and correspondence engine；
C, the fatigue strength and Life Relation for determining turbine center portion：Failed according to the turbine center portion determined in step b dangerous
Position and its stress, determine that turbine center portion strength simulation tests exemplar sampling method, center portion strength simulation experiment exemplar will
Failure dangerous position comprising turbine center portion, along turbine radially be sampled, by fatigue tester according to pulsating cyclic
Load mode carries out fatigue property test to turbine center portion strength simulation experiment exemplar, determines the turbine core as shown in formula (1)
Portion fatigue strength S and life-span N relational model
N=FS-N(S) (1)；
For example, the failure dangerous position of certain vehicle supercharger turbine center portion is located at hub centre, 15 increasings are randomly selected
Depressor turbine, radially and carries out turbine center portion strength simulation by center portion failure dangerous position and tests exemplar sampling；For 15
Individual turbine center portion strength simulation tests exemplar, according to pulsating cyclic is that the load mode that recycle ratio is 0 enters on fatigue tester
The fatigue property test gone under 5 different stress levels, according to experiment on fatigue properties result, can obtain the booster turbine
Center portion fatigue strength S and life-span N relational model is N=exp (72.84-9.818ln S)；
D, the accumulated damage amount for determining turbine center portion failure dangerous position correspondence regulation service life：According to turbocharger
Defined service life, determines the mission profile circulation total degree that turbocharger is undergone within the guideline lives phase, enters one
Step, with reference to the Simulating of Fatigue Stress Spectra and the turbine center portion fatigue of step c determinations of the step b turbine center portion failure dangerous positions determined
Intensity and Life Relation model, calculate accumulated damage amount D of the turbine center portion failure dangerous position in regulation service lifeT；
E, the center portion intensity acceleration checking test stress for determining booster turbine：According to turbocharger test platform ability with
Booster is capable of the maximum permissible revolution n of safe handling on test-bedmax, determine to increase during turbine center portion intensity accelerated test
The highest test speed n of depressorAT, highest test speed nATIt should be greater than turbocharger normal work under engine mission profile
Highest working speed n when makingN, but must not exceed booster maximum permissible revolution nmax, further determined by stress analysis
Go out correspondence booster highest test speed nATWhen turbine center portion intensity accelerated test stress sAT；
For example, certain vehicle turbocharger is capable of the maximum permissible revolution n of safe handling on test-bedmaxFor 150,000
Rev/min, highest working speed n of the booster under engine mission profile during normal workNFor 100,000 revs/min, it is determined that whirlpool
Booster highest test speed n when taking turns center portion intensity accelerated testATFor 13.5 ten thousand revs/min, further, determined by stress analysis
Go out correspondence booster highest test speed nATTurbine center portion intensity accelerated test stress sATFor 765MPa；
F, the acceleration checking test section and its cycle-index for determining booster turbine center portion intensity：Determined according to step e
Highest test speed nATWith acceptable test period, booster turbine center portion intensity stand accelerated test section is worked out,
Test cycle of test profile is " lowest continuous speed with load-highest test speed nAT- lowest continuous speed with load ", its
In, booster is 0.2-5 points in the run time of lowest continuous speed with load, in highest test speed nATRun time be
0.2-5 points；The turbine center portion fatigue strength determined according to step c fails with Life Relation model, step d the turbine center portion determined
Accumulated damage amount D of the dangerous position in regulation service lifeTAnd the turbine center portion intensity accelerated test stress that step e is determined
sAT, using the equivalent principle of accumulated damage, turbine center portion intensity acceleration checking test section cycle-index is determined with formula (2)
NAT, i.e.,
NAT=DTFS-N(sAT) (2)；
For example, the highest test speed n of certain type booster turbineATFor 13.5 ten thousand revs/min, acceptable test period is
Within 150 hours, lowest continuous speed with load of the booster on test-bed is 30,000 revs/min, works out booster turbine center portion
Test cycle of intensity stand accelerated test section is " 30,000 rev/min -13.5 ten thousand revs/min -3 ten thousand revs/min ", wherein, supercharging
Device run time under 30,000 revs/min of operating modes is 1.5 points, and run time is 1 point under 13.5 ten thousand revs/min of operating modes.Booster turbine
Accumulated damage amount D of the center portion failure dangerous position in regulation service lifeTFor 0.85, turbine center portion fatigue strength S and life-span N
Relation is N=exp (72.84-9.818ln S), turbine center portion intensity accelerated test stress sAT, can with formula (2) for 765MPa
Turbine core portion intensity acceleration checking test section cycle-index N is obtained to calculateATFor 1785 times；
G, the progress turbine core portion intensity accelerated test checking on turbocharger stand.The supercharging determined according to step f
Device turbine center portion intensity stand accelerated test section and its cycle-index, carry out turbine core portion intensity on turbocharger test rig frame
To control booster turbine inlet temperature to must not exceed permissible value in verification experimental verification, process of the test, and test cycle number of times is entered
Row is counted, when test cycle number of times reaches NATAfterwards, reduction of speed parking is carried out to turbocharger, torn open after after booster cooling
Inspection, such as turbine stand intact, then illustrate that booster turbine center portion intensity disclosure satisfy that defined use requirement.
Claims (1)
1. a kind of booster turbine center portion intensity accelerated test verification method, comprises the following steps：
A, the working status parameter change course for determining booster turbine correspondence engine mission profile；
B, determine turbine center portion failure dangerous position and its fatigue stress；
C, the fatigue strength and Life Relation for determining turbine center portion；
D, the accumulated damage amount for determining turbine center portion failure dangerous position correspondence regulation service life；
E, the center portion intensity acceleration checking test stress for determining turbine；
F, determine booster turbine center portion intensity stand accelerated test section and its cycle-index；
G, the progress turbine core portion intensity accelerated test checking on turbocharger stand,
Wherein：
In step a, with reference to engine mission profile, by testing method or according to turbocharger and engine performance
Matching relationship uses emulated computation method, determines the working condition of a booster turbine correspondence mission profile circulation of engine
Parameters variation course, including rotation speed change course, inlet temperature change course, the outlet temperature of turbine change course, inlet-pressure
Power change course, outlet pressure change course and gas flow change course；
In stepb, using finite element method to turbine carry out stress analysis, determine turbine center portion failure dangerous position and
The Simulating of Fatigue Stress Spectra of booster turbine center portion failure dangerous position during the mission profile circulation of correspondence engine；In step c,
According to turbine center portion failure dangerous position and its stress, determine that turbine center portion strength simulation tests exemplar sampling method, the heart
Portion's strength simulation experiment exemplar will include the failure dangerous position of turbine center portion, be radially sampled along turbine, by fatigue
Fatigue property test is carried out to turbine center portion strength simulation experiment exemplar according to pulsating cyclic load mode on testing machine, determined
Turbine center portion fatigue strength S and life-span N relational model as shown in formula (1)：
N=FS-N(S) (1)；
In step c, turbine center portion strength simulation experiment exemplar is on fatigue tester according to pulsating cyclic load mode to it
Carry out fatigue property test；
In step d, the service life according to as defined in turbocharger determines that turbocharger is passed through within the guideline lives phase
The mission profile circulation total degree gone through, and combine the turbine center portion failure dangerous position that step b is determined Simulating of Fatigue Stress Spectra and
The turbine center portion fatigue strength that step c is determined and Life Relation model, calculate turbine center portion failure dangerous position and are used in regulation
Accumulated damage amount D in life-spanT；
In step e, it is capable of the highest of safe handling on test-bed according to turbocharger test platform ability and booster
Allow rotating speed nmax, determine the highest test speed n of booster during turbine center portion intensity accelerated testAT, highest test speed nAT
It must not exceed the maximum permissible revolution n of boostermax, correspondence booster highest test speed n is determined by stress analysisATWhen
Turbine center portion intensity acceleration checking test stress sAT；
In step f, the highest test speed n determined according to step eATWith acceptable test period, establishment booster whirlpool
Center portion intensity stand accelerated test section is taken turns, a test cycle of test profile is " lowest continuous speed with load-highest experiment
Rotating speed nAT- lowest continuous speed with load ", wherein, booster is 0.2-5 points in the run time of lowest continuous speed with load,
Highest test speed nATRun time be 0.2-5 point；
It is characterized in that：In step f, using the equivalent principle of accumulated damage, the turbine center portion fatigue strength determined according to step c
Accumulated damage amount D of the turbine center portion failure dangerous position determined with Life Relation model, step d in regulation service lifeT
And the turbine center portion intensity acceleration checking test stress s that step e is determinedAT, determine that turbine center portion intensity accelerates to test with formula (2)
Confirmatory test section cycle-index NAT, i.e.,
NAT=DTFS-N(sAT) (2)。
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| CN105547679B (en) * | 2016-01-08 | 2018-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of cooling turbine unit acceleration service life test method |
| CN107228761A (en) * | 2017-06-02 | 2017-10-03 | 中国科学院金属研究所 | A kind of component's life Forecasting Methodology under complex load and environment |
| CN107941481A (en) * | 2017-09-30 | 2018-04-20 | 中国北方发动机研究所(天津) | A kind of high-temperature duration life assessment method of vehicle supercharger turbine |
| CN109684697B (en) * | 2018-12-14 | 2023-04-07 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining equivalent damage model |
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