CN86103018A - Determine the method for remaining useful life of turbine components - Google Patents
Determine the method for remaining useful life of turbine components Download PDFInfo
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- CN86103018A CN86103018A CN86103018.4A CN86103018A CN86103018A CN 86103018 A CN86103018 A CN 86103018A CN 86103018 A CN86103018 A CN 86103018A CN 86103018 A CN86103018 A CN 86103018A
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Abstract
Interior at interval at the fixed time definite turbine part method of consumption life part is to utilize the creep strain cumulative speed that the indicating value of consumption life part is provided.
Description
The invention relates to a kind of remaining useful life of definite turbine part or the method for consumption life.More precisely turbine part is worked under quite high temperature, is the method for determining its remaining useful life under making the environment of material creep when working.And the material creep of forming turbine part becomes the principal element of determining this parts remaining useful life.
At present estimating of electric energy production between later two decades pointed out, obtain sufficient electric power, key is steam power plant and the relevant turbine that can surpass military service in 30 years thereof.Usually this generation utility power factory and relevant turbine thereof are will be eliminated and replace with new device.Yet modern environment has more increased public power plant to rely on the requirement to electric power output in future that these old factories meet their expectation that is intended to be that the life-span prolongs to the expensive price of the requirement that reduces load and new structure.It is to carry out under the level of the traditional validity of maintenance, Performance And Reliability that consideration actual and economically requires life-time dilatation.The situation that reaches the present existence that needs the crucial turbine part of estimation and the in the future possible performance of optimum balance between the recovery of the capital of risk capital and requirement, i.e. Xian Shi estimation is along with the danger of adopting various life-span prolongation methods to be brought.
Estimate the performance that present situation and definite turbine part are in the future possible, special its work of material for those component parts is the parts at creep range, a difficult problem has been proposed, this is the complicacy because of turbine part, various condition of work that parts stood and normally used remaining useful life or the intrinsic restriction of life consumed evaluation method.Parts are (greater than 900) work at high temperature, and the synergy of the creep of component parts material and heat fatigue herein is a first concern.For the evaluation method that obtains an acceptable remaining useful life is that special consideration is made in requirement.
Recent various technology is used for estimating the remaining useful life of power plant's parts.These technology can reduce two big classes: the destructiveness of physical unit and (or) non-destructive testing (NDT); The method of estimation that the history of the performance of Material Used and parts work performs an analysis.
Destruction of having adopted in the prior art or nondestructive inspection method are found, are restricted when it is applied to main turbine part.Failure test needs the material test specimen that is in the critical section in those parts, and this is very difficult usually, and by the also very difficult estimation that obtains many critical sections of turbine suitably in the non-breaking test.Consider to be subjected to the creep load just merely when some non--destructive technology that has earlier can provide the estimation of remaining useful life of parts in addition, the normal operating conditions of many turbine parts is to be subjected to the two synergy of creep and fatigue breakdown, and tired is crucial factor in the consumption life of determining parts or lifetime limitation.Creep is the function in the time interval, adds every middle stress during this time, and creep is inelastic or non-response (promptly there should be no return to its original shape and state) a kind of material distortion.Tired irrelevant but relevant with Cyclic Stress with the time, be a kind of plastic strain and can cause finally that parts rupture.The degree of damaging when up to the present, prior art also can not be estimated creep and tired synergy rightly.The another kind of technology that has adopted is to use the creep void level as the index that has consumed creep life, but it does not provide suitable result.Thereby these prior arts all can not provide the result with required precision, and accurate result is the foundation of various suggestions, and these suggestions are what to help to make to the decision process of the evaluation of the possible strategy of lengthening the life of turbine and comparison.
The estimation of the analysis of consumption life (deduct it and can get remaining useful life from the entire life of estimating) needs with the various updates with material with complex performance usually, damages detailed valency rule and actual (or desirable) past and following condition of work.The precision of any special analysis method depends on the ability of the method for handling the various uncertainties in the relevant real work parts.
For example, in United States Patent (USP) 4046002, people such as Murphy invention, and transferred this assignee really rotor the method for life consumed be to have adopted the low-cycle fatigue damage, it is relevant with Cyclic Stress, rather than the creep rupture relevant with the time damages.Turbine in addition the range of stress curve of each round-robin range of stress of part and calculating to recently determining turbine part because the life consumed value that circulates and caused.Do not consider to adopt two peak-to-peak time intervals of local stress to determine cycle of stress.
In United States Patent (USP) 3950985, the linear accumulation of the damage assumption method based on Miner is adopted in people's such as Buchwald invention.The hypothesis of Miner can establish an equation down (a) represent:
T(σ herein is to be the time that σ and temperature rupture during for θ for stress θ).The hypothesis of Miner shows that destroying the integration that is created in formula (a) left-hand component equals 1.According to United States Patent (USP) 3950985, the t(σ in the formula (a), θ) value is to be determined by the curve among Fig. 1, thereby this is the method on stress basis, it does not consider the amount of creep strain accumulation.
Thereby the purpose of this invention is to provide a kind of accurately the determine remaining useful life of turbine components or the method for consumption life.
Another object of the present invention provides a kind of effect, the accumulation of creep strain and creep strain accumulation rate of accurately determining remaining useful life of turbine components or should including temperature stress during the method for consumption life.
Almost each turbine part is all at high temperature worked and promptly is higher than 900 °F, though condition of work (temperature for example, the power that adds) remain unchanged because creep makes the state of stress that variation take place, this is because the stress distribution heterogeneous in parts causes creep heterogeneous, wherein in the stressed zone of maximum creep maximum.Thereby cause the stress in parts to redistribute, and be transformed into inelastic strain by elastic strain in addition, because creep is caused, can cause the decline of stress as perhaps.These examples are included in area of stress concentration, as in the local heavily stressed relaxation of the thread root of screw and by the stress of displacement control, as the relaxation of thermal stress in screw and nominal axial stress.Because these stress change in time, be that stress determines accurately that with respect to the function of time of fracture the life-span of parts is very difficult by the constant duty disrupt data of routine.
Up to the present adopt to calculate always the accumulation of creep strain and accumulation strain and material strain ability to recently being definite failure criteria.And the present invention be with the creep strain accumulation rate estimate parts of under predetermined temperature, having worked thereby at the fixed time at interval in damage numerical value under the creep strain rate of being scheduled to.
Determine according to the present invention turbine part the method for consumption life comprise: determine one when turbine part is worked strain facies for the curve of time, determine a rate of change of the interior corresponding creep strain in interval at the fixed time, determine corresponding to following time of causing fracture of creep strain rate of change, and with the rupture time of preset time interval divided by generation damage value.This part life-span in this damages in the consumption life that value representation is total parts at the fixed time at interval.Rupture time and rate of change in several predetermined time intervals can be used to produce corresponding several destruction values, the total destruction value of parts when determining work with its accumulative total then.Characteristics of the present invention are be sure of to be novel, and more definite is illustrated in the appended claim of the present invention, and use of the inventive method and step and further purpose thereof and advantage can be situated between and can better understand with reference to corresponding figure.
Fig. 1 is a creep curve under the typical constant duty.Solid line is by the measurement data gained of a testpieces, and dotted line is that a turbine part is extrapolated under predetermined temperature and got.
Fig. 2 is a creep curve under one group of constant duty, and solid line is the measurement data gained by testpieces, dotted line be to turbine part under a predetermined temperature, during several predetermined load conditions extrapolation and get.
Fig. 3 be a testpieces in predetermined temperature range to when fracture mean creep rate to the function relation curve of rupture time.
Fig. 4 is the creep curve that turbine part calculates, and has represented according to part iterative process of the present invention.
Fig. 5 is the fragmentary, perspective view of the dovetail of a typical turbine tangential entry wheel.
Fig. 6 A and 6B are for name by name and the concentrated stress and the curve of creep strain at the typical turbine tangential entry wheel dovetail shown in Fig. 5 according to the present invention.
Typical creep is with respect to the curve of time under permanent load with reference to the visible testpieces of Fig. 1, and it is first district by three creep stages that solid line is represented testpieces, the measured creep strain in second district and the 3rd district.Its terminal point is to destroy (being breakaway poing) point, and its time is t
rAnd extensibility is ε
LIs to approach very much formula (1) according to the present invention at the solid line in the first and second creep zones
＝Ae
Bσ（1+Cε
F）
ε=creep strain herein
σ=stress
A, B, C and F are material constant, they can be soon by as deriving in one group of represented data of the curve among Fig. 2.
Formula (1) is made up of two parts, the Ae of first
B σRepresented second district's creep rate, and second portion (1+C ε
F) be that a correction term is the predetermined creep rate of first district creep of selecting to simulate.Do not attempt to simulate the creep in the 3rd district, it have small test chamber test specimen be shrunk to neck shape (promptly having reduced basal area) thus characteristics cause the increase of creep rate, to the extrapolation of second district creep with extend as among Fig. 1 shown in the dotted line, the applicant be sure of to represent preferably the accumulation of actual turbine part creep strain, because parts generally do not enter the 3rd creep areas, even total enter into the very little part of component life that this zone also only accounts for.For consistent with model, adaptability to changes ε r is defined as second creep areas is extrapolated to rupture time t
rThe time gained creep strain, t
rCan determine by a test specimen.
With reference to Fig. 2, it has represented that several constant dutys (being constant compelling force) are added on the testpieces result of gained in the tearing test under the predetermined temperature.Curve σ
1, σ
2, σ
3And σ
4Represent the result of the predetermined constant duty that descends gradually separately.Can see each adaptability to changes ε r
1, ε r
2, ε r
3With ε r
4Be along with corresponding rupture time t
R1, t
R2, t
R3And t
R4Increase descend.Also can see with the test specimen of high strain rate accumulation creep strain σ for example
1Will be at short period t
RnIn time, destroy, but it has higher adaptability to changes ε
Rn, n is an integer herein, this speed that shows the absolute value of not only strain accumulation but also its accumulation is for being very important as the failure criteria based on strain.Use these notions, a performance of material is the average creep rate ε when destroying
Avg, it is defined as:
The applicant be sure of that the material that these principles and phenomenon can directly apply to valuably at building block is in the turbine part of working under the creep state, in order to obtain to represent more accurately the residue useful life longevity of parts life consumed or parts, adopting above-mentioned technology so is of great use, and this method than the past is more accurate.
Fig. 3 adopts logarithmic coordinate (10g-10g) the expression test specimen creep rate ε that on average ruptures
AvgWith rupture time t
rChange, test specimen is the typical material that the turbine high-temperature area adopts.The data of drawing usefulness are obtained by tearing test, carry out under the variant expection fixed temperature of test in the hot operation scope of turbine part parts expections and finish, promptly from about 900 °F to about 1100 °F, and rupture failure was taken place from the relatively short time in long time, promptly about 90 hours to about 60,000 hours.Several important observed results have been obtained by the test figure of drawing Fig. 3, in big like this rupture time scope, promptly about 90 hours to about 60,000 hour, the dispersion train of data is narrow comparatively speaking, (promptly make us being in satisfactorily two deviation ranges in), and temperature do not had obvious dependence, in the temperature range of this test employing, be so at least.Do not consider dependence, just can avoid the complicacy of many analyses temperature.Curve shown in Figure 3 has also confirmed the extension phenomenon, and (being the distortion of object when not cracking) or adaptability to changes grow with time, and as expecting, can be extended to long service time, promptly greater than 100,000 hours.Because of test figure shows, 10g(
Avg) and 10g(t
r) between linear, so just can easily derive a mathematic(al) representation.Rupture time t
rWith average fracture creep rate
AvgBetween relation can be represented by the formula:
10g（t
r）＝10g（P）+Q10g（
avg） （3a）
Or
P and Q are coefficients in the formula, are determined by Fig. 3 curve.As require, also determine easily the statistics dispersion train, it is used to refer to the limit of the anticipatory data of predetermined confidence level.
According to the present invention, can adopt rupture time t
rWith average fracture creep rate
AvgBetween this relational expression, determine turbine part life consumed together with the method for calculating creep strain, certainly, it is similar to work in the material for test that the material of creep zone turbine part should adopt with obtaining drafting Fig. 3 curve data.
Referring to Fig. 4, the figure shows the typical turbine part creep strain of adopting equation (1) to calculate
N over time.This figure has also represented and strain rate
1,
2,
3With
4Relevant many time interval △ t
1, △ t
2, △ t
3With △ t
4For time interval △ t
1, can with
1Replace equation (3a) or (3b) in
Avg, determine rupture time t
R1In view of the above, rupture time
At △ t
1Consumed the mark of rupture life in the time interval, or fracture damage △ D
1Can calculate by following formula:
△D
n= (△t)/(t
rn) （4）
The damage strain rate of Dn=interval n in the formula, wherein n is an integer,
Working time under the predetermined strain rate of △ t=,
t
RnThe rupture time of the predetermined strain rate of=interval n.
For each remaining time interval, indicated strain rate
2,
3With
4Be inequality, this will produce different rupture time t
R2, t
R3And t
R4And different damage increment D
2, D
3And D
4
As shown in Figure 4, preferably begin a new interval like this, (and finish at previous interval) is can make each segment strain rate ε among Fig. 4
nBe considered as straight line curve approximation, so, turbine part by n at interval total amount of damage or life consumed be each every damage increment △ D
nSum.With under establish an equation (5) expression:
D in the formula
T=total accumulated damage amount,
The n=space-number.
Total accumulated damage amount D
TOr parts life consumed can in the device that can carry out additive operation, add up, as microprocessor.In calculating the scope that limits, device can make the time interval arbitrarily small as far as possible.
With reference to figure 5, it has represented the partial perspective view of typical turbine tangential entry wheel dovetail 20.For example adopt one of hot charging press fit and suitable key and keyway or both, dovetail 20 can be fixed firmly on the turning axle 10, turning axle has axis 15.Another kind method can be processed into an integral body to dovetail 20 coaxial 10.Dovetail 20 comprises the rib 22,23 and 24 of a plurality of extending axially (with respect to axle 10), and rib is made of the grooving on dovetail 20 sidewalls 15,16 and 17.Rib 22, the part of 23 and 24 alignment is placed in a predetermined garden on week, form otch 25 is installed, be used to lay the blade dovetail (not shown), blade dovetail has good structure, make it with rib 22,23,24 and otch 15,16 and 17 wringing fits, but also having pneumatic paddle or blade (not shown), they are fixed to the outside of corresponding blade dovetail radially.Blade dovetail can be assembled around axle 10 along garden Zhou Fangxiang with relevant blade with turning round.A kind of like this structure with slightly different shape dovetail is at United States Patent (USP) 14,415, and in 266, Rice is described, and transfers the assignee.
The acting force on wheel dovetail 20 and the stress of generation thereof mainly are blade dovetail and the function of three parameters of working temperature of the rotational speed of the quality that radially is fixed on wheel dovetail 20 outside associated components, axle 10 and impeller dovetail 20.Can adopt arbitrary method easily to determine this quality, temperature and rotational speed (angular velocity).For example location detector can be used to provide angular velocity in the turbine apparatus that drives generator, can adopt United States Patent (USP) 4,046, the 002 instrument detecting temperature of announcing, and quality can be obtained by the turbine design data.Although quality and angular velocity should be by suitable curves of selection in the family of curves, curve for example shown in Figure 2, and, still might simplify calculating by which family of curves of temperature decision employing.Many turbines, example turns round with a Constant Angular Velocity basically with the general turbine that drives generator, i.e. 3600 rev/mins (U.S.) or 3000 rev/mins (Europe), and substantial constant ground input fuel gas temperature.In addition, shown in Figure 3 as the front, the creep rate that on average ruptures does not present obvious dependence to temperature at about 900 °F with the variation of rupture time to about 1100 temperature ranges.Many steam turbines have the input temp of this scope.Thereby such turbine with the operation of the gas input temp in 900 to 1100 scopes, as a kind of approximate processing preferably, only need know that the time is just passable.And Temperature Distribution or thermograde in the turbine can be by above-mentioned measuring methods, and design standards or operating experience determines, and do not need extra test.
With reference to figure 6A and 6B, they represent the nominal stress and the creep strain figure of dovetail 20 shown in Figure 5 respectively.Nominal stress σ (NOM) or nominal creep strain ε (NOM) be the wideest part of dovetail 20 or claim substrate 21 on mean stress or average creep strain.Concentrated stress σ (CONC) or concentrated creep strain ε (CONC) are maximum stress or the maximum creep strains in the dovetail groove 20, and most typical is to appear in the zone of otch 15,16 in the dovetail groove 20 and 17.Relation is the function of dovetail 20 geometrical properties basically between name and the concentrated stress, can be by R.E.Peterson, and the factor of stress concentration of John Wiley and Sons (1974) is united with following Stowell ' s equation and is tried to achieve:
K
σ=1+(K
T-1) (S)/(S
N)
K σ=inelastic stress coefficient of concentration wherein
K
T=elastic stress coefficient of concentration
S=concentrated stress secant modulus
S
n=nominal stress secant modulus
K
σAlso be defined as concentrated stress coefficient divided by nominal stress.Can concentrate the creep strain curve with utilizing Fig. 6 B like Fig. 4 class of a curve.
Therefore, every at high temperature promptly greater than about 900 situations that are subjected to stress for predetermined time interval, the method for calculating turbine part fracture creep impairment according to the present invention comprises creep strain cumulative speed in definite parts.The damage strain rate can be tried to achieve by equation (6):
D wherein
TBe parts accumulated damage strain rate, △ t
nBe in predetermined creep strain speed
nThe lower member working time, t
RnBe predetermined creep strain speed
nThe rupture time of following turbine part.Because of accumulated damage strain rate D
TThe expression turbine part is accumulated the mark of consumption life, works as D
TEqual at 1 o'clock, estimate that parts will produce destruction, so remaining useful life of turbine components equals T.T. (promptly from the parts D that starts working
TEqualed for 1 time of experiencing) deduct T.T. of the actual use of parts.For example, be same situation basically because parts will continue to work until in the future, so just can determine to descend at any one time D with the above-mentioned duty of hypothesis
TEqual for 1 time.
Equation (6) can be applicable to arbitrary load condition, or duty, and for this situation, the tensile creep strain property is maybe can finding out, maybe can determining of can estimating.Particularly it can be used for the situation that stress does not keep constant, because of working stress in the working time normally changes, this situation make existing technology estimate parts the method for consumption life or remaining useful life lost efficacy, or produce unallowable error.The place of concentrated stress greater than nominal stress for example originally occur, because the influence of creep process, concentrated stress is tending towards weakening or reducing, thereby working condition has but changed stress may not change the time.
Therefore illustrated and set forth the method in the life-span accurately determining remaining useful life of turbine components or consumed, wherein parts stand the effect of creep impairment, and also comprise simultaneously the effect of creep cumulative speed.
Simultaneously, some concrete characteristic of the inventive method have just been expressed in above-mentioned explanation, certainly can make some improvement and change for the people who is familiar with this area. Be understood that additional claim means all like this some improvement and variations that comprise in Spirit Essence of the present invention and the scope.
Errata
Errata
Claims (7)
1, determine the turbine part method of consumption life, its feature comprises:
Determine turbine service part creep strain curve over time;
Determine the corresponding rate of change of creep strain in first predetermined time interval;
Determine the corresponding rupture time of creep strain rate of change;
Predetermined time interval produces impairment value divided by rupture time, and impairment value is illustrated in the interior service part of predetermined time interval consumption life part.
2, by the described method of claim 1, it is characterized in that: for many predetermined time intervals, repeat to determine the step of corresponding creep strain rate of change, rupture time and cut apart effect, but also comprise respectively organizing and determine the service part accumulating injuring value of consumption life part in the predetermined time interval.
3, by the described method of claim 2, it is characterized in that: every parts are subjected to name and concentrated effects of strain, determine creep strain in time change curve comprise and determine concentrated creep strain change curve in time.
4, by the described method of claim 1, it is characterized in that: determine that corresponding rupture time comprises from the creep strain of second creep areas by the 3rd creep areas extension change curve in time.
5,, it is characterized in that by the described method of claim 2: determine creep strain in time the step of change curve comprise and determine the parts working temperature and select corresponding to the change curve in time of creep under the temperature of determining.
6, by the described method of claim 2, it is characterized in that: the step of determining corresponding rupture time comprises to be determined in the rated designs duty lower member working time, wherein respectively organized the predetermined time interval summation and equaled working time under the rated designs duty.
7, by the described method of claim 2, it is characterized in that: can select in many predetermined time intervals each enough for a short time, corresponding creep strain rate of change can linearly be similar to, and promptly for the corresponding time interval, creep strain change curve in time is a straight line.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US74751485A | 1985-06-21 | 1985-06-21 | |
| US747,514 | 1985-06-21 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN86103018A true CN86103018A (en) | 1986-12-17 |
| CN1010130B CN1010130B (en) | 1990-10-24 |
Family
ID=25005384
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 86103018 Expired CN1010130B (en) | 1985-06-21 | 1986-05-02 | Method for determining remaining useful life of turbine components |
Country Status (4)
| Country | Link |
|---|---|
| JP (1) | JPS6285839A (en) |
| CN (1) | CN1010130B (en) |
| DE (1) | DE3620355A1 (en) |
| FR (1) | FR2583875B1 (en) |
Cited By (5)
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|---|---|---|---|---|
| CN101858799A (en) * | 2009-04-10 | 2010-10-13 | 宝理塑料株式会社 | The method of predicted stresses and creep fracture life prediction method |
| CN1979112B (en) * | 2005-11-21 | 2012-04-04 | 通用电气公司 | Method and system for assessing life of cracked dovetail in turbine |
| CN103765192A (en) * | 2011-09-13 | 2014-04-30 | 三菱重工业株式会社 | Damage evaluation method and maintenance evaluation index policy |
| CN105658911A (en) * | 2013-10-11 | 2016-06-08 | 索拉透平公司 | Single crystal turbine blade life determination process and system |
| CN109030196A (en) * | 2018-08-18 | 2018-12-18 | 深圳阿尔泰克轻合金技术有限公司 | A kind of metal material single shaft creep resistant test sample, fixture and method |
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| US4525763A (en) * | 1983-11-30 | 1985-06-25 | General Electric Company | Apparatus and method to protect motors and to protect motor life |
| JP2658553B2 (en) * | 1990-10-26 | 1997-09-30 | 日立工機株式会社 | Life management method of rotating body for centrifuge |
| DE4203035C2 (en) * | 1992-02-04 | 1993-11-18 | Forschungszentrum Juelich Gmbh | Method for determining the remaining service life of small components using small-angle neutron scattering |
| DE19714789B4 (en) * | 1997-04-10 | 2010-08-12 | Dwa Deutsche Waggonbau Gmbh | Drive design in traction vehicles for low-floor vehicles, in particular for trams in urban transport |
| DE19944435B4 (en) * | 1999-09-16 | 2009-12-24 | Volkswagen Ag | Evaluation method for determining the degree of damage of a machine or machine component |
| JP4310197B2 (en) | 2003-01-22 | 2009-08-05 | 三菱重工業株式会社 | Turbine blade life evaluation method and turbine blade creep elongation strain measuring apparatus |
| US7448853B2 (en) * | 2005-04-12 | 2008-11-11 | Sundyne Corporation | System and method of determining centrifugal turbomachinery remaining life |
| JP4694327B2 (en) * | 2005-09-16 | 2011-06-08 | ポリプラスチックス株式会社 | Creep rupture life estimation method, material selection method, design method and manufacturing method of metal insert resin molded product |
| AT504028B1 (en) * | 2007-11-02 | 2009-03-15 | Avl List Gmbh | METHOD FOR THE DAMAGE PRESENTATION OF COMPONENTS OF A MOTOR VEHICLE |
| DE102010010932A1 (en) * | 2010-02-12 | 2011-08-18 | Evonik Energy Services GmbH, 45128 | Method and device for determining the creep behavior of a mechanically loaded component |
| JP5295992B2 (en) * | 2010-02-16 | 2013-09-18 | ポリプラスチックス株式会社 | Prediction method of creep fracture life of metal composite molded products |
| DE102015011763A1 (en) * | 2015-09-15 | 2017-03-16 | Jörn GmbH | An aircraft with at least one elastically deformable component and method for determining the onset of a wear-related component remaining service life on an aircraft |
| DE102015011760A1 (en) * | 2015-09-15 | 2017-03-16 | Jörn GmbH | Device having at least one elastically deformable component and method for determining the onset of a wear-related component remaining service life |
| DE102015011762B4 (en) * | 2015-09-15 | 2021-02-11 | Jörn GmbH | Rail vehicle with at least one elastically deformable component and method for determining the start of a component remaining useful life on a rail vehicle due to wear |
| DE102015011764A1 (en) * | 2015-09-15 | 2017-03-16 | Jörn GmbH | Vessel with at least one elastically deformable component and method for determining the onset of a wear-related component remaining service life on a watercraft |
| JP6673053B2 (en) * | 2016-06-28 | 2020-03-25 | 株式会社島津製作所 | Rotor life estimation device and vacuum pump |
| JP6729317B2 (en) * | 2016-11-15 | 2020-07-22 | 株式会社島津製作所 | Pump state estimation device and turbo molecular pump |
| EP4012160A1 (en) * | 2020-12-11 | 2022-06-15 | Ansaldo Energia Switzerland AG | Method for estimating the consumed life of a rotating component |
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1986
- 1986-05-02 CN CN 86103018 patent/CN1010130B/en not_active Expired
- 1986-05-30 FR FR8607774A patent/FR2583875B1/en not_active Expired - Fee Related
- 1986-06-18 DE DE19863620355 patent/DE3620355A1/en not_active Ceased
- 1986-06-20 JP JP61143135A patent/JPS6285839A/en active Pending
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1979112B (en) * | 2005-11-21 | 2012-04-04 | 通用电气公司 | Method and system for assessing life of cracked dovetail in turbine |
| CN101858799A (en) * | 2009-04-10 | 2010-10-13 | 宝理塑料株式会社 | The method of predicted stresses and creep fracture life prediction method |
| CN101858799B (en) * | 2009-04-10 | 2013-09-25 | 宝理塑料株式会社 | Method for predicting stress and method for predicting creep rupture life |
| CN103765192A (en) * | 2011-09-13 | 2014-04-30 | 三菱重工业株式会社 | Damage evaluation method and maintenance evaluation index policy |
| CN103765192B (en) * | 2011-09-13 | 2016-08-17 | 三菱日立电力***株式会社 | Damage evaluation method and safeguard the formulating method of evaluation index |
| US9689789B2 (en) | 2011-09-13 | 2017-06-27 | Mitsubishi Hitachi Power Systems, Ltd. | Damage evaluation method and maintenance evaluation index decision method |
| CN105658911A (en) * | 2013-10-11 | 2016-06-08 | 索拉透平公司 | Single crystal turbine blade life determination process and system |
| CN109030196A (en) * | 2018-08-18 | 2018-12-18 | 深圳阿尔泰克轻合金技术有限公司 | A kind of metal material single shaft creep resistant test sample, fixture and method |
| CN109030196B (en) * | 2018-08-18 | 2021-10-29 | 深圳阿尔泰克轻合金技术有限公司 | Metal material uniaxial creep resistance test sample, clamp and method |
Also Published As
| Publication number | Publication date |
|---|---|
| DE3620355A1 (en) | 1987-01-02 |
| JPS6285839A (en) | 1987-04-20 |
| FR2583875B1 (en) | 1991-09-20 |
| FR2583875A1 (en) | 1986-12-26 |
| CN1010130B (en) | 1990-10-24 |
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