EP1727970A1 - 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

Info

Publication number
EP1727970A1
EP1727970A1 EP05715936A EP05715936A EP1727970A1 EP 1727970 A1 EP1727970 A1 EP 1727970A1 EP 05715936 A EP05715936 A EP 05715936A EP 05715936 A EP05715936 A EP 05715936A EP 1727970 A1 EP1727970 A1 EP 1727970A1
Authority
EP
European Patent Office
Prior art keywords
rotor
turbomachine
control area
uncritical
crack
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.)
Granted
Application number
EP05715936A
Other languages
German (de)
English (en)
Other versions
EP1727970B1 (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

Links

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, in the uncovered state, has a control area which is visible from the outside, in which a comparatively uncritical stress occurs during operation of the turbomachine and which in the uncovered state has a monitoring region which is not visible from the outside, in the 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.
  • the invention further relates to a turbomachine according to the preamble of claim 8 and a method for recognizing 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 is known.
  • 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 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 end face of a rotor disk in the region of the holding grooves for turbine blades.
  • the embodiment shown therein is felt to be disadvantageous because the sheet metal strip breaks off during operation and can then lead to damage in the gas turbine.
  • the components of the rotor of a gas turbine are inspected for defects before they are assembled, in order to avoid damage that can occur during operation of the gas turbine.
  • the rotor is made up of several rotor disks lying next to each other and a tie rod. In addition to the thermal stresses, it is particularly exposed to the mechanical stresses caused by the centrifugal force, so that its components are examined for defects.
  • the rotor disks are through the known material tests such.
  • B. ultrasound examined for defects that appear as displays, which may be present after the manufacture of the rotor disks.
  • the displays indicate defects, foreign material inclusions, inhomogeneities in the material structure or cracks.
  • the rotor disks recognized as free of display after this initial test are then used for the construction of the rotor.
  • Ad-free means that there are actually no imperfections or that the imperfections present in the component are so small that theoretically, according to a fracture mechanical calculation, no critical cracks can arise and grow from them during operation of the gas turbine.
  • the rotors have to be unstacked for testing, that is to say disassembled into their rotor components, in order to examine the areas of the rotor disks which are not visible from the outside and therefore cannot be examined for cracks.
  • the previously known methods are used repeatedly.
  • the permissible starting number of the gas turbine can be determined by means of a deterministic analysis, after which the rotor components must be checked for defects.
  • the fracture mechanical boundary conditions and the assumed operating stresses are selected so that the permissible number of starts is conservative, i.e. that the permissible number of starts is underestimated.
  • the growth behavior of a crack in a rotor disk is shown.
  • the characteristic curve 51 is determined in accordance with the above-mentioned analysis. With an increasing number of starts, the crack length a increases disproportionately. During operation, however, a crack must not exceed the calculated maximum permissible crack length a 2Ul .
  • the task aimed at the rotor is characterized by the features of claim 1, the task directed at the turbomachine by the features of claim 8 and the
  • the solution to the problem directed at the rotor provides that a recess, in particular a relief bore, is provided to limit the weak point, into which the uncritical defect can leak.
  • the invention is based on the knowledge that the defects which are not detected or tolerated during the initial test can trigger crack growth during the operation of the turbomachine.
  • a flaw is deliberately introduced into the control area visible from the outside.
  • An uncritical defect caused by the stress collective can then grow from the weak point.
  • the condition of the rotor is recognized as "to be checked” only if an uncritical defect, whose length exceeds a limit value, is found in the control area while the turbomachine is open and the rotor is still assembled. Only then is the rotor disassembled and the in-depth check is carried out Rotor components necessary.
  • the previous method was turned away, in which the criteria for deciding on the disassembly of the rotor were derived from a deterministic analysis using a conservative boundary condition. If it was found during a check of the dismantled rotor components that there was no defect inside the rotor, the rotor has so far been unnecessarily dismantled and the rotor components have thus been checked unnecessarily.
  • a recess in particular a relief bore, is provided to limit the weak point, into which the uncritical defect can leak. This prevents the defect from growing to a supercritical length and / or beyond the control area.
  • the weak point on an annular balcony is designed so that on this attack circumferential loads when operating the turbomachine.
  • the load acting in the circumferential direction can achieve an above-average improvement in the comparability of the loads of the control area and the monitoring area.
  • the rotor comprises a plurality of rotor disks and at least one tie rod that clamps the rotor disks. If at least one of the rotor disks in the control area has a critical defect during inspection, the rotor must be dismantled and at least the component in question checked for defects.
  • the invention is particularly advantageously applicable to welded or one-piece rotors, since disassembly is not possible with them, but the condition of the rotor can be determined in relation to internal critical defects which could possibly lead to failure of the rotor.
  • a weak point is expediently provided at least on one of the rotor disks.
  • the configuration in which each rotor disk has a weak point is particularly advantageous.
  • Some of the control areas cover a first revision interval, after which it should be necessary to mathematically unstack the rotor and check the rotor disks.
  • further control areas with further weak points and associated recesses can be provided, which cause crack growth for the previous mode of operation.
  • the entire stress spectrum can thus act on the associated weak point, so that conclusions can be drawn for the entire rotor when checking the control area.
  • the control area could be designed such that the weak point with its associated relief opening covers all revision intervals. Consequently, the actual crack length must be recorded for each revision and compared with a predetermined permissible crack length assigned to the respective revision in order to determine the condition of the rotor.
  • the monitoring area borders on a hub of the rotor disk, since higher stresses can occur at this point during operation of the turbomachine. Since breakage damage occurs first in this area, it makes sense to monitor it.
  • the solution to the problem addressed by the method suggests that the control area of the rotor is first examined for an uncritical defect and if there is no defect in the control area the state is determined as “not to be checked” or in the event of a defect, a conclusion can be drawn about a further defect arranged in the monitoring area, from which the condition of the rotor is subsequently determined.
  • FIG. 1 shows a section through a rotor disk with a weak point
  • FIG. 2 shows the side view of the rotor disk according to FIG. 1,
  • FIG. 3 shows the top view of the circumference of the rotor disk according to FIG. 1,
  • FIG. 4 shows a starting number-crack length diagram according to the invention
  • Figure 5 is a starting number-crack length diagram according to the prior art.
  • Figure 6 is a partial longitudinal section through a gas turbine.
  • a gas turbine and its mode of operation is generally known.
  • 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 and a working machine, e.g. B. a generator.
  • the turbine 8 and the compressor 5 are arranged on a common rotor 3, also referred to as a turbine rotor, to 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 burning a liquid or gaseous fuel.
  • the gas turbine 1 has a non-rotatable lower housing half 12, in which the assembled rotor 3 is placed when the gas turbine 1 is assembled. An upper housing half 13 is then mounted in order to close the gas turbine 1.
  • the rotor 3 has a central tie rod 10, which braces a plurality of rotor disks 19 lying against one another.
  • the compressor 5 and the turbine 8 each have a number of rotatable rotor blades 16 connected to the rotor 3.
  • the rotor blades 16 are arranged in a ring-shaped manner on the annular rotor disks 19 and thus form a number of rotor blade rows 15.
  • both the compressor 5 and the turbine 8 comprise a number of stationary guide blades 14, which are also ring-shaped to form guide blade rows 17 an inner wall of the housing of compressor 5 or turbine 8 are attached.
  • FIG. 1 shows the section through the rotor disk 19 of a gas turbine 1 along its radius.
  • the axis of rotation 2 of the rotor 3 runs through the center of the annular rotor disk 19, which can be designed as a compressor disk or also as a turbine disk.
  • the rotor disk 19 has rotor blade retaining grooves 23 for receiving rotor blades 16 at its radially outer end 21.
  • a freely projecting balcony 27 is provided on an end face 25 of the rotor disk 19.
  • the balcony 27 has a control area 29 which is visible from the outside when the assembled rotor 3 is exposed.
  • the rotor 3 is then in the lower housing half 12 of the gas turbine 1 and the upper housing half 13 is removed.
  • FIG. 3 shows the control area 29 with a weak point 31, which is designed as a notch 32 with a notch length a notch .
  • the notch 32 is provided on an axial edge 33 of the balcony 27, with a recess 34 being arranged opposite as a relief opening 35.
  • the relief opening 35 is spaced from the edge 33 in such a way that the amount of the distance corresponds to a maximum permissible crack length a notch explained later.
  • a monitoring area 37 which is adjacent to the hub 36 of the rotor disk 19, is arranged radially on the inside Operation of the gas turbine 1 critical stresses can occur.
  • the weak point 31, which is arranged in the control area 29 which is uncritical for the function of the rotor 3, is proportionally comparable in size and effect to a flaw 41 to be assumed in the monitoring area 37. Furthermore, the stresses occurring in the control area 29 can be compared proportionally with the stresses occurring in the monitoring area 37.
  • stresses and stress collectives can occur at the weak point 31, and possibly in the presence of a fault 41, which can lead to crack growth at these points.
  • the weak point 31 must be dimensioned such that a crack 40 grows there rather than from an undetected fault point 41.
  • At least one control area 29 of one of the rotor disks 19 has a crack 40 as a defect 39 which ends in the relief opening 35 starting from the weak point 31, it can be assumed that a comparable crack 45 in the monitoring area 37 if a defect 41 is present has arisen, so that the state of the rotor 3 or the rotor disk 19 is to be classified as “to be checked”. Then the turbine disk 19, which has the non-critical defect 39, has to be checked by means of a more precise examination, for which purpose the rotor 3 has to be dismantled.
  • the relief opening could be so far away from the notch that crack growth is possible, which extends over several inspection intervals.
  • the permissible crack length assigned to a revision interval which indicates the state “to be checked”, must then always be compared with the actually existing, measured crack length. Accordingly, it is possible to evaluate the crack growth that occurs due to the operation of the gas turbine between two subsequent revisions.
  • FIG. 4 shows a starting number-crack length diagram which is used in the invention.
  • the abscissa is the
  • the starting number N of the gas turbine 1 is plotted and on the ordinate the crack length a of cracks 40 of rotor disks 19.
  • a characteristic curve 53 drawn in full line shows the conservatively calculated course of the crack length a of the crack 40 im
  • Control area 29 as a function of the starting number N of
  • the maximum crack length a of the crack 40 including the length a notch of the notch 32, with which the rotor disk 29 can be operated without the latter being specified with a maximum permissible crack length a notch
  • the condition and that of the rotor 3 is to be classified as "to be checked”.
  • the characteristic curve 53 intersects the maximum permissible crack length a notch at point 55. From this, the permissible starting number N Ber calculated using a conservative assumption can then be determined.
  • the gas turbine 1 is disassembled for revision purposes.
  • point 63 P N Ber , a ⁇ l
  • a two- ter point 61 is determined as the origin of a further characteristic curve 57, so that the characteristic curve 57 can be determined in the abscissa interval of [0, N Ber ] on the basis of the fracture mechanical properties of the material of the rotor disk 19.
  • the dash-dotted curve 57 consequently shows the crack growth that has occurred as a result of the actual stress spectrum.
  • the further course 65 of the characteristic curve 57 is then determined by extrapolation, in order then to determine an intersection point 59 with the maximum permissible crack length a notch ( as a result of which the actually permissible starting number N, “, is determined, according to which the rotor 3 is to be dismantled and to check for defects 43 in the critical monitoring area 37. A comparatively precise determination of the remaining service life of the rotor disks 19 is thus carried out.
  • the difference ⁇ n between the actually permissible number of starts N lal and the calculated permissible number of starts N Ber is the gain in starts N of the gas turbine 1 achieved by the invention. Only after the actually permissible number of starts N lal has been reached can the rotor 3 be disassembled and to examine the rotor disks 19 and other rotor components for defects 43 in the critical monitoring area 37.
  • the weak point 31 creates a crack growth indicator up to this point in time, which is exposed to the actual stress collective, in the manner of a predetermined breaking point, with which conclusions regarding defects 43 on areas of the rotor disks 19 which are not visible from the outside are made possible.

Landscapes

  • 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.
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 true EP1727970A1 (fr) 2006-12-06
EP1727970B1 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

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005093220A1 *

Also Published As

Publication number Publication date
EP1727970B1 (fr) 2007-10-31
RU2006136383A (ru) 2008-04-27
JP4447637B2 (ja) 2010-04-07
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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