EP1363248A1 - Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique - Google Patents

Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique Download PDF

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Publication number
EP1363248A1
EP1363248A1 EP02010774A EP02010774A EP1363248A1 EP 1363248 A1 EP1363248 A1 EP 1363248A1 EP 02010774 A EP02010774 A EP 02010774A EP 02010774 A EP02010774 A EP 02010774A EP 1363248 A1 EP1363248 A1 EP 1363248A1
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EP
European Patent Office
Prior art keywords
component
crack
computer
computer program
crack growth
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP02010774A
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German (de)
English (en)
Inventor
Günther Dr. Walz
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP02010774A priority Critical patent/EP1363248A1/fr
Priority to PCT/EP2003/004273 priority patent/WO2003096280A1/fr
Publication of EP1363248A1 publication Critical patent/EP1363248A1/fr
Withdrawn legal-status Critical Current

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    • G—PHYSICS
    • G07—CHECKING-DEVICES
    • G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
    • G07C3/00—Registering or indicating the condition or the working of machines or other apparatus, other than vehicles

Definitions

  • the invention relates to a method for status recognition of a mechanically stressed component and a computer system on which the process is running, a computer program with program code means and a computer program product.
  • JP2001153756-A discloses a method of calculation a crack, but not to calculate a crack growth.
  • the object according to the invention is achieved by a method according to claim 1, by using operating parameters, such as tempering parts, in order to be able to calculate the crack growth of existing errors, so that a parameter can be calculated which provides information as to whether the service life is still sufficiently long or soon to be finished.
  • operating parameters such as tempering parts
  • the procedure defines inspection intervals and the quantities to be tested.
  • the method takes into account both internal, i. embedded Errors as well as surface defects. Because inner mistakes up to an outer surface of a component can grow and until then do not lead to failure of the component, but As surface defects continue to grow, this will in the Procedure also taken into account. One speaks of the so-called Folding embedded errors into surface defects.
  • FIG. 1 shows schematically in a longitudinal section a gas turbine 1.
  • a gas turbine 1 is selected for a machine that consists of several components in which defects exist and can grow.
  • a compressor 7, a combustion chamber 10 and a turbine part 13 are arranged one behind the other.
  • the turbine part 13 has a hot gas channel 16.
  • gas turbine blades 20 are arranged in the hot gas duct 16 .
  • Guide vane and blade boundary are provided alternately successive.
  • the gas turbine blades 20 are cooled, for example via a combined air and / or steam cooling.
  • the compressor 7 compressor air removed and fed via an air supply 23 to the gas turbine blades 22.
  • a steam supply 26 the gas turbine blades 20, for example, also supplied steam.
  • FIG. 2 shows in a simplified representation a section of a turbine part 13 in a longitudinal section.
  • the turbine part 13 has a shaft 4 which extends along a rotation axis 41. Furthermore, the turbine part 13 has successively an inflow region 49, a blading region 51 and an outflow region 53 along the rotation axis 41.
  • Rotatable blades 20 'and fixed vanes 20 are disposed in the blading area 51.
  • the rotor blades 20 are fastened to the shaft 4, while the guide vanes 20 are arranged on a guide vane carrier 47 which bypasses the shaft 4.
  • the Beschaufelungs Scheme 51 and the vane support 47 is an annular flow channel for a flow medium A, eg superheated steam formed.
  • the inflow region 49 serving to supply the flow medium A is bounded in the radial direction by an inflow housing 55 arranged upstream of the guide blade carrier 47.
  • An outflow housing 57 is arranged downstream of the guide blade carrier 47 and limits the outflow region 53 in the radial direction, that is to say perpendicular to the axis of rotation 41.
  • the flow medium A flows from the inflow region 49 into the blading region 51, where the flow medium performs work under expansion, and then leaves via the outflow region 53, the gas turbine 1.
  • the flow medium A is then in the outflow housing 57 downstream in 2 not shown capacitor for a steam turbine collected.
  • FIG. 3 shows a perspective view of a blade 20 which extends along a radial axis 60.
  • the blade has along the Rädialachse 60 successively a mounting portion 63, an adjoining paddle platform 66 and an airfoil portion 69 on.
  • a blade root 72 is formed, which serves for fastening the blade 20 to the shaft 4 of a gas turbine 1.
  • the blade root 72 is designed, for example, as a hammer head.
  • Conventional blades 20 are used in all areas 63, 66, 69 used massive metallic materials.
  • the Blade 20 can in this case by a casting process, by a forging process, by a milling process or combinations made of it.
  • the component has multiple already on production immediately after production.
  • FIG. 4 shows a turbine blade 20 which has an internal defect 73, for example a pore, a gas trap (voids) or the like.
  • An internal defect 73 for example a pore, a gas trap (voids) or the like.
  • Surface defects are particularly critical for turbine blades. Due to mechanical stress, an internal crack 76 increases, which can continue to grow up to a surface 82 of the component 20 (FIG. 5). Depending on the size of the inner crack 76, there may already be a failure here.
  • the method also takes into account existing surface defects.
  • the method does not consider plasticizing (creeping area) in the component.
  • FIG. 7 shows a monitor 85 as part of a computer system which detects at least one operating parameter 88, such as temperature T, pressure (expansions) p, number of cycles N and frequency f of various components.
  • the operating parameters 88 are detected via corresponding sensors on the components, for example 4, 7, 10, 13, 16, 20, 23, 26, 47, 55, 57, and forwarded for calculation to a computer (computer).
  • a computer computer
  • the method that calculates the life of the components is present as a computer program product (software) or is loaded from a computer-readable storage medium (floppy disk, CD-ROM, DVD).
  • On the monitor 85 also has a life indicator 91 is present, which indicates the status of the component / components to the operator or the service, ie whether the life of the or the monitored components is still sufficient or if investigations must be made or if the machine are turned off got to.
  • Figure 8 shows schematically the procedure of the method. For example, all components that are subjected to mechanical stress are detected and known errors are included in the lifetime calculation.
  • the operating parameters 88 with which a crack growth calculation is made, change to this crack growth.
  • the parameters are continuously or regularly interrogated and the crack length or life is also calculated. If the service life is still sufficiently long, ie it lasts, for example, until the next regular service, the interrogation of the operating parameters and the calculation of the crack growth are repeated.
  • new errors can be discovered, which are taken into account in the calculation of the life with the inventive method.
  • the crack length of known cracks from the calculation can be adapted to the crack length determined in the service, so that a kind of self-learning effect takes place.
  • the current status of a tear can be called up at any time. For example, the status is set to 0% for the given initial length. It is known or calculable for the location of the crack in the component as long as this crack is allowed to grow without already leading to a component failure. This maximum length would then correspond to 100%, so that the status of the crack lies between 0 and 100%.
  • the interaction of cracks can be taken into account.
  • the dependence of a distance of the crack to a surface in the crack growth can also be taken into account.
  • this is for example the monitor 85 by displaying a parameter of "lifetime sufficient "to” life ended "in the life indicator is set.
  • the method can be run on a computer system, the one central computer, networked computers, screen monitors, other hardware and measuring leads for data acquisition of operating parameters and the like includes.
  • the method can be used in any programming language as Computer program to be written, for example, on the computer system is compiled to produce program code means to perform all the steps of the procedure if that Program running on a computer / computer system.
  • the invention further relates to a computer program product with program code means residing on a computer readable medium (Floppy disks, CD-Rom's) are stored to the procedure perform when the program product on a computer is stored.
  • a computer readable medium Floppy disks, CD-Rom's
  • the stress intensity factor K K ( ⁇ , a) and the calculated value ⁇ K of importance, where ⁇ is the mechanical load and a the Crack length is.
  • the crack growth per cycle da / dN is shown in FIG. From a certain threshold Ak thr crack growth takes place until it comes to complete failure of the component.
  • ⁇ K is the difference between K max - K min .
  • the meaning of these two values is shown in FIG. 10, in which a mechanical load of a component is plotted over the number of cycles N, ie over time.
  • K max is the maximum value for the stress intensity factor K, where K min represents the minimum stress, ie the smallest value for the stress intensity factor.
  • the parameter R is given by K min / K max .
  • the material parameters are determined experimentally from the curve da / dN by these parameters optimally fitting the function to the measured values (interpolation).
  • the value .DELTA.K s results in double logarithmic plot of the curve from FIG. 9 from the intersection of two straight lines.
  • Below a certain value for the stress intensity factor K no crack growth takes place.
  • the values for ⁇ K below the threshold value represent a high-frequency portion of the mechanical load, in which usually no errors grow. In the case of the low-frequency component of the mechanical stress, the threshold value is exceeded and crack growth according to the above-mentioned formula takes place.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
EP02010774A 2002-05-14 2002-05-14 Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique Withdrawn EP1363248A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP02010774A EP1363248A1 (fr) 2002-05-14 2002-05-14 Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique
PCT/EP2003/004273 WO2003096280A1 (fr) 2002-05-14 2003-04-24 Procede de reconnaissance d'etat d'un composant sollicite mecaniquement, systeme d'ordinateur sur lequel le procede est applique, programme d'ordinateur dote de moyens code programme et produit programme d'ordinateur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP02010774A EP1363248A1 (fr) 2002-05-14 2002-05-14 Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique

Publications (1)

Publication Number Publication Date
EP1363248A1 true EP1363248A1 (fr) 2003-11-19

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EP02010774A Withdrawn EP1363248A1 (fr) 2002-05-14 2002-05-14 Méthode d'identification de la condition d'un élement sous contrainte mécanique, système informatique pour mettre en oeuvre la méthode, programme informatique mun de moyens de programmation et produit de programme informatique

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EP (1) EP1363248A1 (fr)
WO (1) WO2003096280A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1562033A1 (fr) * 2004-01-27 2005-08-10 Abb Research Ltd. Estimation d'un comportement de vieillissement irréversible
EP1835149A1 (fr) * 2006-03-17 2007-09-19 Siemens Aktiengesellschaft Dispositif et méthode de surveillance du fonctionnement d'une turbine à gaz

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104842085B (zh) * 2015-04-24 2017-01-25 中国航空工业集团公司北京航空材料研究院 一种高温合金薄壁管材表面气孔缺陷的模拟及实验方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4875170A (en) * 1986-04-10 1989-10-17 Hitachi, Ltd. Method and apparatus for estimating life expectancy of mechanical structures
US5140528A (en) * 1988-06-13 1992-08-18 Westinghouse Electric Corp. Method for evaluating relationship between the size of discontinuity indications from non-destructive examination of a turbine rotor, stress applied to the rotor and remaining life of the rotor
US5654500A (en) * 1996-04-17 1997-08-05 General Electric Co. Method for determining cyclic service life for rotational parts of a rotary machine
US20020013643A1 (en) * 2000-04-14 2002-01-31 Fumiharu Ishii Method and equipment for assessing the life of members put under high in-service temperature environment for long period

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4875170A (en) * 1986-04-10 1989-10-17 Hitachi, Ltd. Method and apparatus for estimating life expectancy of mechanical structures
US5140528A (en) * 1988-06-13 1992-08-18 Westinghouse Electric Corp. Method for evaluating relationship between the size of discontinuity indications from non-destructive examination of a turbine rotor, stress applied to the rotor and remaining life of the rotor
US5654500A (en) * 1996-04-17 1997-08-05 General Electric Co. Method for determining cyclic service life for rotational parts of a rotary machine
US20020013643A1 (en) * 2000-04-14 2002-01-31 Fumiharu Ishii Method and equipment for assessing the life of members put under high in-service temperature environment for long period

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1562033A1 (fr) * 2004-01-27 2005-08-10 Abb Research Ltd. Estimation d'un comportement de vieillissement irréversible
EP1835149A1 (fr) * 2006-03-17 2007-09-19 Siemens Aktiengesellschaft Dispositif et méthode de surveillance du fonctionnement d'une turbine à gaz

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WO2003096280A1 (fr) 2003-11-20

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