EP1727970B1 - Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine - Google Patents

Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine Download PDF

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Publication number
EP1727970B1
EP1727970B1 EP05715936A EP05715936A EP1727970B1 EP 1727970 B1 EP1727970 B1 EP 1727970B1 EP 05715936 A EP05715936 A EP 05715936A EP 05715936 A EP05715936 A EP 05715936A EP 1727970 B1 EP1727970 B1 EP 1727970B1
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EP
European Patent Office
Prior art keywords
rotor
turbomachine
uncritical
crack
inspection
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.)
Not-in-force
Application number
EP05715936A
Other languages
German (de)
English (en)
Other versions
EP1727970A1 (fr
Inventor
Christian Hohmann
Reimar Schaal
Werner Setz
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 EP05715936A priority Critical patent/EP1727970B1/fr
Publication of EP1727970A1 publication Critical patent/EP1727970A1/fr
Application granted granted Critical
Publication of EP1727970B1 publication Critical patent/EP1727970B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/06—Shutting-down
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Definitions

  • the invention relates to a rotor for a turbomachine, which has an externally visible control area in the uncovered state, in which a comparatively uncritical stress occurs during operation of the turbomachine and in the uncovered state has a monitoring area, not visible from the outside, in which during operation of the turbomachine a comparatively critical stress occurs, with a weak point arranged in the control area in the manner of a predetermined breaking point, which is designed as a notch. Furthermore, the invention relates to a turbomachine according to the preamble of claim 8 and a method for detecting the state of the rotor of a turbomachine according to the preamble of claim 10.
  • a method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage.
  • at least one test element is attached to a component to be monitored in an area in which comparable temperatures and operating loads occur.
  • the creep behavior of the test element is examined in order to derive therefrom the creep behavior of the component to be monitored.
  • the test element is designed as a partially tapered sheet metal strip, which is welded on the front side in the region of the holding grooves for turbine blades on a rotor disk.
  • the embodiment shown therein is considered to be disadvantageous because the metal strip break off during operation and then can cause damage in the gas turbine.
  • the components of the rotor of a gas turbine are inspected for defects even before their assembly in order to avoid damage that may occur in the operation of the gas turbine.
  • the rotor is made up of several adjoining rotor disks and a tie rod. In addition to the thermal stresses, it is particularly exposed to the mechanical stresses resulting from the centrifugal force, so that its components are examined for defects.
  • the rotor discs are by the known material tests such. As ultrasound, for defects that appear as ads, examined which may be present after the manufacture of the rotor discs. The indications indicate flaws, foreign material inclusions, inhomogeneities in the material structure or cracks. The after this initial test recognized as display rotor disks are then used for the construction of the rotor. Indication-free means that in fact there are no defects or that defects present in the component are so small that theoretically, according to a fracture mechanical calculation during operation of the gas turbine, no critical cracks can arise and grow from them.
  • the rotors must be unstacked for testing, that is, broken down into their rotor components in order to inspect for cracks the areas of the rotor disks which are not visible from the outside and thus can not be examined in the interior of the rotor.
  • the permissible number of starts of the gas turbine can be determined by means of a deterministic analysis, after which a check of the rotor components for defects is to be made.
  • the fracture mechanical boundary conditions and the assumed operating stresses are chosen so that the permissible number of starts is designed to be conservative, i. that the admissible starting number is estimated too low.
  • FIG. 5 shows a start number crack length diagram according to the prior art.
  • the characteristic curve 51 is determined according to the above-mentioned analysis. As the number of starts increases, the crack length a increases disproportionately. During operation, however, a crack may not exceed the calculated maximum allowable crack length a zul .
  • the solution of the task directed to the rotor provides that to limit the weak point a recess, in particular a relief hole is provided, in which the uncritical defect can leak.
  • the invention is based on the finding that the imperfections not covered or tolerated during the initial test during operation of the turbomachine can cause crack growth.
  • inventively provided vulnerability targeted a defect in the externally visible control area is introduced. From the weak point, an uncritical defect caused by the stress collective can then grow. Only when an uncritical defect arranged in the control area is detected with the turbomachine open and the rotor still assembled, the length of which exceeds a limit, then the condition of the rotor is recognized as "to be checked”. Only then is the dismantling of the rotor and a thorough inspection of the rotor components necessary.
  • a recess in particular a relief hole is provided to limit the vulnerability, in which the uncritical defect can leak. An increase of the defect to a supercritical length and / or beyond the control range is thus prevented.
  • the weak point is formed on an annular balcony so that at this attack loads directed in the circumferential direction during operation of the turbomachine.
  • the weak point is formed on an annular balcony so that at this attack loads directed in the circumferential direction during operation of the turbomachine.
  • the rotor comprises a plurality of rotor disks and at least one tie rod clamping the rotor disks. If at least one of the rotor discs in the control area has a critical defect during the inspection, the rotor must be disassembled and at least the relevant component checked for defects.
  • the invention is applicable to welded or one-piece rotors, since in these decomposition is not possible, but the state of the rotor can be determined with respect to internal critical defects, which could possibly lead to failure of the rotor.
  • a weak point is provided at least on one of the rotor disks.
  • each rotor disk has a weak point.
  • a part of the control areas covers a first inspection interval, according to which a destacking of the rotor and a checking of the rotor disks should be computationally required.
  • For each further inspection interval further control areas with further weak points and associated recesses may be provided, which cause a crack growth for the previous mode of operation.
  • the entire stress collective can act on the associated weak point, in order then to be able to draw conclusions when checking the control area for the entire rotor.
  • control area could be designed such that the vulnerability with its associated relief opening covers all revision intervals. Consequently, with each revision, the actual crack length must be detected and compared with a given allowable crack length associated with each revision to determine the state of the rotor.
  • the monitoring area adjoins a hub of the rotor disk, since higher stresses may occur at this point during operation of the turbomachine. Since fracture mechanical damage first occur in this area, its monitoring makes sense.
  • the solution of the object directed to the method proposes to detect the condition of the exposed rotor of a turbomachine by first examining the control range of the rotor for an uncritical defect and, in the absence of a defect in the control region, determining the condition as "not to be checked” or, if there is a defect, it is concluded that there is another defect arranged in the monitoring area, from which the state of the rotor is subsequently determined.
  • Figure 6 shows a gas turbine 1, a compressor 5 for combustion air, a combustion chamber 6 and a turbine 8 for driving both the compressor 5 as well as a working machine, for.
  • the turbine 8 and the compressor 5 are arranged on a common rotor 3, also referred to as a turbine rotor, with which the working machine is also connected, and which is rotatably mounted about its longitudinal axis.
  • the combustion chamber 6 is equipped with burners 7 for the combustion of a liquid or gaseous fuel.
  • the gas turbine 1 has a rotationally fixed lower housing half 12, in which during assembly of the gas turbine 1, the assembled rotor 3 is put into it. Subsequently, an upper casing half 13 is mounted to close the gas turbine 1.
  • the rotor 3 has a central tie rod 10, which clamps a plurality of juxtaposed rotor disks 19 with each other.
  • the compressor 5 as well as the turbine 8 each have a number of rotatable blades 16 connected to the rotor 3.
  • the blades 16 are annularly disposed on the annular rotor discs 19 and thus form a number of rows of blades 15.
  • both the compressor 5 and the turbine 8 comprise a number of fixed vanes 14 which are also annular with the formation of rows of vanes 17 on an inner wall of the housing of compressor 5 and turbine 8 are fastened.
  • FIG. 1 shows the section through the rotor disk 19 of a gas turbine 1 along its radius.
  • the rotor disk 19 which may be formed as a compressor disk or as a turbine disk, the axis of rotation 2 of the rotor 3 extends.
  • the rotor disk 19 has blade receiving grooves 23 for receiving rotor blades 16 at its radially outer end 21.
  • the balcony 27 has a control area 29, which is visible in the uncovered state of the assembled rotor 3 from the outside.
  • the rotor 3 is then in the lower half of the housing 12 of the gas turbine 1 and the upper housing half 13 is removed.
  • FIG. 3 shows the control region 29 with a weak point 31, which as a notch 32 with a notch length a notch 0 is trained.
  • the notch 32 is provided at an axial edge 33 of the balcony 27, wherein a recess 34 is arranged opposite as a relief opening 35 opposite.
  • the relief opening 35 is spaced from the edge 33 such that the amount of the distance of a later-mentioned maximum allowable crack length ⁇ notch zul equivalent.
  • Radially inside a on the hub 36 of the rotor disk 19 adjacent monitoring area 37 is arranged in the at Operation of the gas turbine 1 critical stresses can occur.
  • stresses and stress collective can occur at the weak point 31, and possibly in the presence of a defect 41, which can each lead to crack growth at these locations.
  • the weak point 31 must be dimensioned such that a crack 40 grows there rather than from an undiscovered defect 41.
  • At least one control region 29 of one of the rotor disks 19 has a crack 40 as a defect 39, ending in the relief opening 35 starting from the weak point 31, it can be assumed that in the monitoring region 37 in the presence of a defect 41 a comparable crack 45 is formed, so that the state of the rotor 3 and the rotor disk 19 is to be classified as "to check”. Then the uncritical defect 39 having turbine disk 19 is to be checked by a closer examination, to which the rotor 3 is to be disassembled.
  • the relief opening could be so far away from the notch as to allow crack growth that extends over multiple revision intervals.
  • the permissible crack length assigned to a revision interval which indicates the condition to be checked, must be then always compared with the actually existing, measured crack length. Accordingly, an evaluation of the crack growth is possible, which occurs through the operation of the gas turbine between two subsequent revisions.
  • Figure 4 shows a starting number crack length diagram used in the invention.
  • the starting number N of the gas turbine 1 is plotted on the abscissa and the crack length a of cracks 40 of rotor disks 19 is plotted on the ordinate.
  • a curve 53 drawn in solid line shows the conservatively calculated course of the crack length a of the crack 40 in the control region 29 as a function of the starting number N of the gas turbine 1.
  • a maximum permissible crack length a notch as the limit value zul is the maximum crack length a of the crack 40 including the length a notch 0 the notch 32 predetermined, with which the rotor disk 29 can be operated without their condition and that of the rotor 3 is to be classified as "to check”.
  • the characteristic 53 intersects the maximum permissible crack length a notch zul at point 55. From this, the permissible starting number N Ber calculated under conservative assumption can then be calculated zul determine.
  • the externally visible control region 29 then optionally shows a crack 40 originating from the notch 32 and having the actual length a tat , which is denoted as point 63 P ( N Ber zul , a tat ) is entered in the diagram.
  • point 63 P N Ber zul , a tat
  • Point 61 is defined as the origin of another characteristic curve 57, so that in the abscissa interval of [0, N Ber zul ] the characteristic curve 57 can be determined on the basis of the fracture mechanical properties of the material of the rotor disk 19.
  • the dash-dotted line 57 thus shows the crack growth, which has occurred by the actual stress collective.
  • the further course 65 of the characteristic curve 57 is then determined by extrapolation, in order then to have an intersection point 59 with the maximum permissible crack length a notch zul to determine.
  • the actually allowed starting number N tat zul determines according to which the rotor 3 to disassemble and check in the critical monitoring area 37 for defects 43.
  • a comparatively accurate determination of the remaining service life of the rotor disks 19 takes place.
  • the difference ⁇ n between the actually allowed starting number N tat zul and the calculated number of starts N Ber zul is the gain achieved by the invention at Starts N of the gas turbine 1. Only after reaching the actual allowable starting number N tat zul the rotor 3 is to be disassembled and the rotor disks 19 and other rotor components examined for defects 43 in the critical monitoring area 37.
  • the weak point 31 creates a crack growth indicator exposed to the actual stress collective in the manner of a predetermined breaking point with which conclusions regarding defects 43 on regions of the rotor disks 19 not visible from the outside are made possible.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

L'invention concerne un rotor (3) de turbomachine, qui présente, lorsqu'il est dégagé, une zone de contrôle (29) visible depuis l'extérieur, dans laquelle s'exerce une sollicitation comparativement non critique lorsque la turbomachine est en service et qui présente, à l'état dégagé, une zone de surveillance (37) non visible de l'extérieur, dans laquelle s'exerce une sollicitation comparativement critique, lorsque la turbomachine est en service. Ledit rotor comporte un point faible (31) sous forme de point de rupture, disposé dans la zone de contrôle (29) et conçu sous forme d'encoche (32). L'invention vise à renforcer le fonctionnement fiable de la turbomachine. A cet effet, il est prévu, pour limiter le point faible (31), de former une cavité (34), en particulier un trou d'évacuation (35), dans lequel la défaillance non critique (39) peut passer.

Claims (12)

  1. Rotor (3) pour une turbomachine qui, à l'état découvert, a une partie (29) témoin qui est visible de l'extérieur et dans laquelle se produit, lorsque la turbomachine fonctionne, une sollicitation relativement non critique et qui, à l'état dégagé, a une partie (37) à contrôler qui n'est pas visible de l'extérieur et dans laquelle il se produit, lorsque la turbomachine fonctionne, une sollicitation relativement critique,
    comprenant un point (31) faible à la façon d'un point destiné à se rompre, qui est disposé dans la partie (29) témoin et qui est constitué sous la forme d'une encoche (32),
    caractérisé
    en ce que pour délimiter le point (31) faible il est prévu un évidement (34), notamment un trou (35) de soulagement, dans lequel le défaut (39) non critique peut se propager.
  2. Rotor (3) suivant la revendication 1,
    caractérisé
    en ce que le point (31) faible est constitué sur un balcon annulaire, de manière à ce qu'il soit attaqué par des sollicitations dirigées, lorsque la turbomachine fonctionne, dans la direction périphérique.
  3. Rotor (3) suivant la revendication 1 ou 2,
    caractérisé
    en ce que le rotor (3) comprend plusieurs disques (19) de rotor et au moins un tirant (10) serrant les disques (19) de rotor.
  4. Rotor (3) suivant la revendication 1, 2 ou 3,
    caractérisé
    en ce que le rotor (3) est d'un seul tenant en étant, notamment, soudé.
  5. Rotor (3) suivant la revendication 4,
    caractérisé
    en ce que le au moins un point (31) faible est prévu du côté frontal sur au moins l'un des disques (19 de rotor.
  6. Rotor (3) suivant la revendication 5,
    caractérisé
    en ce que le rotor (3) a plusieurs points (31) faibles répartis sur un disque (19) de rotor ou sur plusieurs disques (19) de rotor et
    en ce que, pour l'échelonnement des révisions, les points (31) faibles sont, avec leurs évidements (34) associés, constitués différemment, de manière à ce que pour chaque révision la sollicitation collective cumulée jusqu'à l'instant respectif de révision provoque une croissance de fissure comparable dans la partie témoin.
  7. Rotor (3) suivant la revendication 6,
    caractérisé
    en ce que la partie (37) à contrôler est voisine d'un moyeu (36) du disque (19) de rotor.
  8. Turbomachine ayant un rotor (3),
    caractérisée
    en ce que le rotor (3) est constitué suivant l'une des revendications 1 à 7.
  9. Turbomachine suivant la revendication 8,
    caractérisée
    en ce que la turbomachine est constituée en compresseur (5), en turbine (1) à gaz ou en turbine à vapeur.
  10. Procédé d'établissement de l'état du rotor (3) dégagé d'une turbomachine,
    qui, à l'état dégagé, a une partie (29) témoin qui est visible de l'extérieur et dans laquelle se produit, lorsque la turbomachine fonctionne, une sollicitation relativement non critique et
    qui, à l'état dégagé, a une partie (37) à contrôler qui n'est pas visible de l'extérieur et dans laquelle il se produit, lorsque la turbomachine fonctionne, une sollicitation relativement critique,
    caractérisé
    en ce que l'on étudie d'abord la partie (29) témoin du rotor (3) sur un défaut (39) non critique constitué sous la forme d'une fissure (40) et, en présence d'un défaut (39) non critique, on établit l'état du rotor comme étant à contrôler si la fissure (40) créée dans la partie (29) témoin a une longueur qui dépasse une valeur limite.
  11. Procédé suivant la revendication 10,
    caractérisé
    en ce qu'après avoir établi l'état à contrôler, on désassemble le rotor (3).
  12. Procédé suivant la revendication 10 à 11,
    avec un rotor suivant les revendications 1 à 7.
EP05715936A 2004-03-16 2005-03-10 Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine Not-in-force EP1727970B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05715936A EP1727970B1 (fr) 2004-03-16 2005-03-10 Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP04006256A EP1577492A1 (fr) 2004-03-16 2004-03-16 Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine
PCT/EP2005/002560 WO2005093220A1 (fr) 2004-03-16 2005-03-10 Procede et dispositif d'identification de l'etat du rotor d'une turbomachine
EP05715936A EP1727970B1 (fr) 2004-03-16 2005-03-10 Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP1727970A1 EP1727970A1 (fr) 2006-12-06
EP1727970B1 true EP1727970B1 (fr) 2007-10-31

Family

ID=34833612

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04006256A Withdrawn EP1577492A1 (fr) 2004-03-16 2004-03-16 Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine
EP05715936A Not-in-force EP1727970B1 (fr) 2004-03-16 2005-03-10 Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP04006256A Withdrawn EP1577492A1 (fr) 2004-03-16 2004-03-16 Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine

Country Status (8)

Country Link
US (1) US7568886B2 (fr)
EP (2) EP1577492A1 (fr)
JP (1) JP4447637B2 (fr)
CN (1) CN1985069A (fr)
DE (1) DE502005001830D1 (fr)
ES (1) ES2293543T3 (fr)
RU (1) RU2377415C2 (fr)
WO (1) WO2005093220A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9103741B2 (en) 2010-08-27 2015-08-11 General Electric Company Methods and systems for assessing residual life of turbomachine airfoils
GB201216787D0 (en) * 2012-09-20 2012-11-07 Rolls Royce Plc Method and system for predicting the serviceable life of a component
GB201402597D0 (en) 2014-02-14 2014-04-02 Rolls Royce Plc Method and system for predicting the serviceable life of a component
EP3088661A1 (fr) * 2015-04-28 2016-11-02 Siemens Aktiengesellschaft Surveillance de la fatigue de rotor de turbine à vapeur

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3490748A (en) * 1968-05-14 1970-01-20 Gen Motors Corp Fragmentation brake for turbines
CH573151A5 (fr) * 1974-06-28 1976-02-27 Bbc Sulzer Turbomaschinen
US4796465A (en) * 1987-04-28 1989-01-10 General Electric Company Method and apparatus for monitoring turbomachine material
DE19650260A1 (de) 1996-12-04 1998-06-10 Asea Brown Boveri Rotor für Turbomaschinen
DE19962735A1 (de) 1999-12-23 2001-06-28 Alstom Power Schweiz Ag Baden Verfahren zur Überwachung des Kriechverhaltens rotierender Komponenten einer Verdichter- oder Turbinenstufe
JP2003021093A (ja) * 2001-07-05 2003-01-24 Boc Edwards Technologies Ltd 真空ポンプ

Also Published As

Publication number Publication date
RU2006136383A (ru) 2008-04-27
JP4447637B2 (ja) 2010-04-07
EP1727970A1 (fr) 2006-12-06
WO2005093220A1 (fr) 2005-10-06
RU2377415C2 (ru) 2009-12-27
US7568886B2 (en) 2009-08-04
JP2007529669A (ja) 2007-10-25
EP1577492A1 (fr) 2005-09-21
CN1985069A (zh) 2007-06-20
US20080145223A1 (en) 2008-06-19
ES2293543T3 (es) 2008-03-16
DE502005001830D1 (de) 2007-12-13

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