CN104458236A - Acceleration test verification method for strength of center of supercharger turbine - Google Patents
Acceleration test verification method for strength of center of supercharger turbine Download PDFInfo
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- CN104458236A CN104458236A CN201410765988.0A CN201410765988A CN104458236A CN 104458236 A CN104458236 A CN 104458236A CN 201410765988 A CN201410765988 A CN 201410765988A CN 104458236 A CN104458236 A CN 104458236A
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Abstract
The invention relates to an acceleration test verification method for the strength of the center of a supercharger turbine. The acceleration test verification method includes the steps of firstly determining a working state parameter variation course of an engine mission section corresponding to the supercharger turbine, then determining the efficacy losing risk portion of the center of the turbine and the fatigue stress of the center of the turbine, determining the relationship between the fatigue strength of the center of the turbine and the service life by designing a turbine center strength simulation test sample piece and carrying out fatigue performance testing, determining the highest rotation speed of a turbine center strength acceleration test and corresponding acceleration test stress, compiling a turbine center strength rack acceleration test section, then determining the number of cycle times of a turbine center strength acceleration verification test section, and finally carrying out acceleration test verification on the strength of the center of the turbine on a turbine super test rack. test verification of the strength of the center of the supercharger turbine can be achieved on the test rack in a short period of test time, the test efficiency can be remarkably improved, the test time can be shortened, the test cost can be saved, and the scientific basis can be provided for reliability assessment and reasonable use of the supercharger turbine.
Description
Technical field
The invention belongs to the evaluation of booster turbine structural reliability and verification experimental verification technology thereof, be specifically related to a kind of booster turbine heart portion intensity accelerated test verification method.
Background technology
Turbosupercharger is that vehicular engine realizes power density lifting and strengthens one of adaptive critical component of altitude environment, turbine is as the kernel component of turbosupercharger, and its reliability directly affects reliability and the serviceable life of turbosupercharger and whole engine.Maximum stress due to booster turbine is usually found in the heart portion of turbine, and the restriction turbine core portion intensity simultaneously by casting technique generally can lower than other positions, and therefore, turbine core portion determines one of turbine reliability and the key position in life-span.
Vehicle turbocharger is with engine in use, due to the polytrope of vehicular engine operating condition, the working status parameter such as the rotating speed of turbosupercharger change constantly, and the change of supercharger speed makes turbine core portion subject the effect of alternate load.Can there is fatigure failure in turbine core portion, and cause turbine to disperse under the effect of alternate load.Booster turbine, once fatigue occurs disperse, not only can make supercharger and engine work, and likely cause supercharger and the larger damage of engine.Therefore, in the development process of turbosupercharger, be extremely necessary to carry out sufficient theoretical analysis and effective verification experimental verification to the heart portion fatigue strength of turbine.
Although the mission profile by simulating turbosupercharger on test-bed carries out the heart portion intensity that long certification test can verify booster turbine effectively, but, designed life due to booster turbine is general all long, be put to the test the restriction of the factors such as time, test condition, experimentation cost, this method of according to turbosupercharger mission profile, turbine core portion intensity being carried out to verification experimental verification on test-bed, infeasible in engineering reality.
Summary of the invention
The present invention is directed to structural reliability evaluation and the verification experimental verification problem of booster turbine, a kind of booster turbine heart portion intensity accelerated test verification method is provided.On the basis determining turbo operating state Parameters variation course, turbine core portion inefficacy dangerous position and fatigue stress thereof, turbine core portion fatigue strength and Life Relation, determine the accumulated damage amount in turbine core portion inefficacy dangerous position corresponding regulation serviceable life; According to the maximum permissible revolution of turbocharger test rig ability and supercharger safe handling, determine turbine core portion intensity accelerated test stress, and determine booster turbine heart portion intensity stand accelerated test section and cycle index thereof further; Then, on supercharger stand, the intensity accelerated test checking of turbine core portion is carried out according to test profile and cycle index thereof.
Technical solution of the present invention:
A kind of booster turbine heart portion intensity accelerated test verification method, is characterized in that comprising the following steps:
A, determine the working status parameter change course of the corresponding engine mission profile of booster turbine;
B, determine turbine core portion inefficacy dangerous position and fatigue stress thereof;
C, the fatigue strength determining turbine core portion and Life Relation;
D, determine the accumulated damage amount in turbine core portion inefficacy dangerous position corresponding regulation serviceable life;
E, determine the heart portion intensity acceleration checking test stress of turbine;
F, determine booster turbine heart portion intensity stand accelerated test section and cycle index thereof;
G, on turbosupercharger stand, carry out the checking of turbine core portion intensity accelerated test.
A kind of booster turbine heart portion intensity accelerated test verification method, is characterized in that comprising the following steps:
A, determine the working status parameter change course of the corresponding engine mission profile of booster turbine: binding engine mission profile, emulated computation method is used by testing method or according to turbosupercharger and engine performance matching relationship, determine the working status parameter change course of a booster turbine corresponding engine mission profile circulation, comprise the rotation speed change course of turbine, inlet temperature change course, outlet temperature change course, intake pressure change course, top hole pressure change course and gas flow change course;
B, determine turbine core portion inefficacy dangerous position and fatigue stress thereof: according to step a determined booster turbine working status parameter change course, utilize Finite Element Method to carry out stress analysis to turbine, determine the heart portion inefficacy dangerous position of turbine and the Simulating of Fatigue Stress Spectra of corresponding engine mission profile circulation time booster turbine heart portion's inefficacy dangerous position;
C, the fatigue strength determining turbine core portion and Life Relation: according to the turbine core portion inefficacy dangerous position determined in step b and stress thereof, determine turbine core portion strength simulation test exemplar sampling method, heart portion strength simulation test exemplar will comprise the inefficacy dangerous position in turbine core portion, sample along turbine radial direction, by carrying out fatigue property test according to pulsating cyclic load mode to turbine core portion strength simulation test exemplar on fatigue tester, determine such as formula the turbine core portion fatigue strength S shown in (1) and life-span N relational model
N＝F
S-N(S) (1)；
D, determine the accumulated damage amount in turbine core portion inefficacy dangerous position corresponding regulation serviceable life: according to turbosupercharger rated wear, determine the mission profile circulation total degree that turbosupercharger experiences within the guideline lives phase, further, the turbine core portion fatigue strength that the Simulating of Fatigue Stress Spectra of the turbine core portion inefficacy dangerous position that integrating step b determines and step c determine and Life Relation model, calculate the turbine core portion inefficacy dangerous position accumulated damage amount D within regulation serviceable life
t;
E, determine the heart portion intensity acceleration checking test stress of booster turbine: can the maximum permissible revolution n of safe handling on test-bed according to turbocharger test platform ability and supercharger
max, determine the highest test speed n of supercharger during turbine core portion intensity accelerated test
aT, the highest test speed n
aTthe most high workload rotating speed n of turbosupercharger under engine mission profile during normal work should be greater than
n, but supercharger maximum permissible revolution n must not be exceeded
max, determine the highest test speed n of corresponding supercharger further by stress analysis
aTtime turbine core portion intensity acceleration checking test stress s
aT;
F, the acceleration checking test section determining booster turbine heart portion intensity and cycle index thereof: the highest test speed n determined according to step e
aTwith acceptable test period, establishment booster turbine heart portion intensity stand accelerated test section, the single test circulation of test profile is " lowest continuous speed with load-the highest test speed n
aT-lowest continuous speed with load ", wherein, supercharger is that 0.2-5 divides, at the highest test speed n in the working time of lowest continuous speed with load
aTworking time be that 0.2-5 divides; Adopt the principle of accumulated damage equivalence, the accumulated damage amount D of the turbine core portion inefficacy dangerous position determined of the turbine core portion fatigue strength determined according to step c and Life Relation model, steps d within regulation serviceable life
tand the turbine core portion intensity acceleration checking test stress S that step e determines
aT, use formula (2) to determine turbine core portion intensity acceleration checking test section cycle index N
aT, namely
N
AT＝D
TF
S-N(s
AT) (2)；
G, on turbosupercharger stand, carry out the checking of turbine core portion intensity accelerated test.The booster turbine heart portion intensity stand accelerated test section determined according to step f and cycle index thereof, turbocharger test rig frame carries out the strength test checking of turbine core portion, booster turbine inlet temperature to be controlled in process of the test and must not exceed permissible value, and test cycle number of times is counted, when test cycle number of times reaches N
aTafter, reduction of speed parking is carried out to turbosupercharger, opens and inspect after supercharger cooling, as turbine stands intact, then can determine that booster turbine heart portion intensity can meet the request for utilization of regulation.
The present invention compared with prior art has following beneficial effect:
By changing course to booster turbine working status parameter, turbine core portion inefficacy dangerous position and fatigue stress thereof, turbine core portion fatigue strength and Life Relation etc. are analyzed, determine the acceleration checking test stress of turbine core portion intensity accelerated test maximum speed and correspondence, establishment booster turbine heart portion intensity stand accelerated test section, adopt accumulated damage equivalence principle determination turbine core portion intensity acceleration checking test section cycle index, according to the turbine core portion intensity stand accelerated test section determined and cycle index thereof, shorter test period can be adopted on turbocharger test stand to realize verifying the accelerated test of turbine core portion intensity, significantly can promote the verification experimental verification efficiency of booster turbine heart portion intensity, effective shortening test period, and reduce experimentation cost, for the reliability evaluation of booster turbine and reasonable employment provide scientific basis.
Accompanying drawing explanation
Fig. 1 is booster turbine heart portion intensity accelerated test verification method flow process.
Embodiment
A kind of booster turbine heart portion intensity accelerated test verification method, comprises the following steps:
A, determine the working status parameter change course of the corresponding engine mission profile of booster turbine: binding engine mission profile, emulated computation method is used by testing method or according to turbosupercharger and engine performance matching relationship, determine the working status parameter change course of a booster turbine corresponding engine mission profile circulation, comprise the rotation speed change course of turbine, inlet temperature change course, outlet temperature change course, intake pressure change course, top hole pressure change course and gas flow change course;
B, determine turbine core portion inefficacy dangerous position and fatigue stress thereof: according to step a determined booster turbine working status parameter change course, utilize Finite Element Method to carry out stress analysis to turbine, determine the heart portion inefficacy dangerous position of turbine and the Simulating of Fatigue Stress Spectra of corresponding engine mission profile circulation time booster turbine heart portion's inefficacy dangerous position;
C, the fatigue strength determining turbine core portion and Life Relation: according to the turbine core portion inefficacy dangerous position determined in step b and stress thereof, determine turbine core portion strength simulation test exemplar sampling method, heart portion strength simulation test exemplar will comprise the inefficacy dangerous position in turbine core portion, sample along turbine radial direction, by carrying out fatigue property test according to pulsating cyclic load mode to turbine core portion strength simulation test exemplar on fatigue tester, determine such as formula the turbine core portion fatigue strength S shown in (1) and life-span N relational model
N＝F
S-N(S) (1)；
Such as, the inefficacy dangerous position in certain vehicle supercharger turbine heart portion is positioned at hub centre, random selecting 15 these booster turbines, radially and carry out the sampling of turbine core portion strength simulation test exemplar by heart portion inefficacy dangerous position; For 15 turbine core portion strength simulation test exemplars, the load mode that fatigue tester is 0 according to pulsating cyclic and recycle ratio has carried out the fatigue property test under 5 different stress levels, according to experiment on fatigue properties result, the relational model that can obtain this booster turbine heart portion fatigue strength S and life-span N is N=exp (72.84-9.818ln S);
D, determine the accumulated damage amount in turbine core portion inefficacy dangerous position corresponding regulation serviceable life: according to turbosupercharger rated wear, determine the mission profile circulation total degree that turbosupercharger experiences within the guideline lives phase, further, the turbine core portion fatigue strength that the Simulating of Fatigue Stress Spectra of the turbine core portion inefficacy dangerous position that integrating step b determines and step c determine and Life Relation model, calculate the turbine core portion inefficacy dangerous position accumulated damage amount D within regulation serviceable life
t;
E, determine the heart portion intensity acceleration checking test stress of booster turbine: can the maximum permissible revolution n of safe handling on test-bed according to turbocharger test platform ability and supercharger
max, determine the highest test speed n of supercharger during turbine core portion intensity accelerated test
aT, the highest test speed n
aTthe most high workload rotating speed n of turbosupercharger under engine mission profile during normal work should be greater than
n, but supercharger maximum permissible revolution n must not be exceeded
max, determine the highest test speed n of corresponding supercharger further by stress analysis
aTtime turbine core portion intensity accelerated test stress s
aT;
Such as, certain vehicle turbocharger can the maximum permissible revolution n of safe handling on test-bed
maxbe 150,000 revs/min, the most high workload rotating speed n of supercharger under engine mission profile during normal work
nbe 100,000 revs/min, supercharger the highest test speed n during the turbine core portion intensity accelerated test determined
aTbe 13.5 ten thousand revs/min, further, determine the highest test speed n of corresponding supercharger by stress analysis
aTturbine core portion intensity accelerated test stress s
aTfor 765MPa;
F, the acceleration checking test section determining booster turbine heart portion intensity and cycle index thereof: the highest test speed n determined according to step e
aTwith acceptable test period, establishment booster turbine heart portion intensity stand accelerated test section, the single test circulation of test profile is " lowest continuous speed with load-the highest test speed n
aT-lowest continuous speed with load ", wherein, supercharger is that 0.2-5 divides, at the highest test speed n in the working time of lowest continuous speed with load
aTworking time be that 0.2-5 divides; The accumulated damage amount D of the turbine core portion inefficacy dangerous position determined of the turbine core portion fatigue strength determined according to step c and Life Relation model, steps d within regulation serviceable life
tand the turbine core portion intensity accelerated test stress s that step e determines
aT, adopt the principle of accumulated damage equivalence, use formula (2) to determine turbine core portion intensity acceleration checking test section cycle index N
aT, namely
N
AT＝D
TF
S-N(s
AT) (2)；
Such as, the highest test speed n of certain type booster turbine
aTit is 13.5 ten thousand revs/min, acceptable test period is within 150 hours, the lowest continuous speed with load of supercharger on test-bed is 30,000 revs/min, the single test circulation of establishment booster turbine heart portion intensity stand accelerated test section is " 30,000 rev/min-13.5 ten thousand revs/min-3 ten thousand revs/min ", wherein, supercharger working time under 30,000 revs/min of operating modes is 1.5 points, and under 13.5 ten thousand revs/min of operating modes, working time is 1 point.Booster turbine heart portion's inefficacy dangerous position regulation serviceable life in accumulated damage amount D
tbe 0.85, it is N=exp (72.84-9.818ln S) that turbine core portion fatigue strength S and life-span N closes, turbine core portion intensity accelerated test stress s
aTfor 765MPa, use formula (2) that turbine core portion intensity acceleration checking test section cycle index N can be calculated
aTit is 1785 times;
G, on turbosupercharger stand, carry out the checking of turbine core portion intensity accelerated test.The booster turbine heart portion intensity stand accelerated test section determined according to step f and cycle index thereof, turbocharger test rig frame carries out the strength test checking of turbine core portion, booster turbine inlet temperature to be controlled in process of the test and must not exceed permissible value, and test cycle number of times is counted, when test cycle number of times reaches N
aTafter, reduction of speed parking is carried out to turbosupercharger, opens and inspect after supercharger cooling, as turbine stands intact, then illustrate that booster turbine heart portion intensity can meet the request for utilization of regulation.
Claims (10)
1. a booster turbine heart portion intensity accelerated test verification method, is characterized in that comprising the following steps:
A, determine the working status parameter change course of the corresponding engine mission profile of booster turbine;
B, determine turbine core portion inefficacy dangerous position and fatigue stress thereof;
C, the fatigue strength determining turbine core portion and Life Relation;
D, determine the accumulated damage amount in turbine core portion inefficacy dangerous position corresponding regulation serviceable life;
E, determine the heart portion intensity acceleration checking test stress of turbine;
F, determine booster turbine heart portion intensity stand accelerated test section and cycle index thereof;
G, on turbosupercharger stand, carry out the checking of turbine core portion intensity accelerated test.
2. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in step a, binding engine mission profile, emulated computation method is used by testing method or according to turbosupercharger and engine performance matching relationship, determine the working status parameter change course of a booster turbine corresponding engine mission profile circulation, comprise the rotation speed change course of turbine, inlet temperature change course, outlet temperature change course, intake pressure change course, top hole pressure change course and gas flow change course.
3. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in stepb, utilize Finite Element Method to carry out stress analysis to turbine, determine the heart portion inefficacy dangerous position of turbine and the Simulating of Fatigue Stress Spectra of corresponding engine mission profile circulation time booster turbine heart portion's inefficacy dangerous position.
4. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in step c, according to turbine core portion inefficacy dangerous position and stress thereof, determine turbine core portion strength simulation test exemplar sampling method, turbine core portion strength simulation test exemplar will comprise the inefficacy dangerous position in turbine core portion, and sample along turbine radial direction, by carrying out fatigue property test according to pulsating cyclic load mode to turbine core portion strength simulation test exemplar on fatigue tester, determine such as formula the turbine core portion fatigue strength S shown in (1) and life-span N relational model
N＝F
S-N(S) (1)。
5. booster turbine heart portion according to claim 1 intensity accelerated test verification method, is characterized in that: in step c, and turbine core portion strength simulation test exemplar carries out fatigue property test according to pulsating cyclic load mode to it on fatigue tester.
6. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in steps d, according to turbosupercharger rated wear, determine the mission profile circulation total degree that turbosupercharger experiences within the guideline lives phase, and the turbine core portion fatigue strength determined of the Simulating of Fatigue Stress Spectra of turbine core portion inefficacy dangerous position determined of integrating step b and step c and Life Relation model, calculate the accumulated damage amount D of inefficacy dangerous position in turbine core portion within regulation serviceable life
t.
7. booster turbine heart portion according to claim 1 intensity accelerated test verification method, is characterized in that: in step e, can the maximum permissible revolution n of safe handling on test-bed according to turbocharger test platform ability and supercharger
max, determine the highest test speed n of supercharger during turbine core portion intensity accelerated test
aT, the highest test speed n
aTthe most high workload rotating speed n of turbosupercharger under engine mission profile during normal work should be greater than
n, but supercharger maximum permissible revolution n must not be exceeded
max, determine the highest test speed n of corresponding supercharger by stress analysis
aTtime turbine core portion intensity acceleration checking test stress s
aT.
8. booster turbine heart portion according to claim 1 intensity accelerated test verification method, is characterized in that: in step f, the highest test speed n determined according to step e
aTwith acceptable test period, establishment turbine core portion intensity stand accelerated test section, the single test circulation of test profile is " lowest continuous speed with load-the highest test speed n
aT-lowest continuous speed with load ", wherein, supercharger is that 0.2-5 divides, at the highest test speed n in the working time of lowest continuous speed with load
aTworking time be that 0.2-5 divides.
9. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in step f, adopt the principle of accumulated damage equivalence, the accumulated damage amount D of the turbine core portion inefficacy dangerous position determined of the turbine core portion fatigue strength determined according to step c and Life Relation model, steps d within regulation serviceable life
tand the turbine core portion intensity acceleration checking test stress s that step e determines
aT, utilization formula (
2) determine turbine core portion intensity acceleration checking test section cycle index N
aT, namely
N
AT＝D
TF
S-N(s
AT) (2)
10. booster turbine heart portion according to claim 1 intensity accelerated test verification method, it is characterized in that: in step g, the booster turbine heart portion intensity stand accelerated test section determined according to step f and cycle index thereof, turbocharger test rig frame carries out the strength test checking of turbine core portion, booster turbine inlet temperature to be controlled in process of the test and must not exceed permissible value, and test cycle number of times is counted, when test cycle number of times reaches N
aTafter, reduction of speed parking is carried out to turbosupercharger, opens and inspect after supercharger cooling, as turbine stands intact, then can determine that turbine core portion intensity can meet the request for utilization of regulation.
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