EP1577492A1 - Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine - Google Patents

Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine Download PDF

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Publication number
EP1577492A1
EP1577492A1 EP04006256A EP04006256A EP1577492A1 EP 1577492 A1 EP1577492 A1 EP 1577492A1 EP 04006256 A EP04006256 A EP 04006256A EP 04006256 A EP04006256 A EP 04006256A EP 1577492 A1 EP1577492 A1 EP 1577492A1
Authority
EP
European Patent Office
Prior art keywords
rotor
turbomachine
defect
uncritical
during operation
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Withdrawn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
EP04006256A
Other languages
German (de)
English (en)
Inventor
Christian Dr. Hohmann
Reimar Dr. Schaal
Werner Dr. 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 EP04006256A priority Critical patent/EP1577492A1/fr
Priority to ES05715936T priority patent/ES2293543T3/es
Priority to PCT/EP2005/002560 priority patent/WO2005093220A1/fr
Priority to CNA2005800085009A priority patent/CN1985069A/zh
Priority to RU2006136383/06A priority patent/RU2377415C2/ru
Priority to DE502005001830T priority patent/DE502005001830D1/de
Priority to JP2007503244A priority patent/JP4447637B2/ja
Priority to EP05715936A priority patent/EP1727970B1/fr
Priority to US10/592,768 priority patent/US7568886B2/en
Publication of EP1577492A1 publication Critical patent/EP1577492A1/fr
Withdrawn legal-status Critical Current

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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, in the uncovered state visible from the outside Has control area, in which during operation of the turbomachine a comparatively uncritical stress occurs and the one in the uncovered state one from the outside has visible monitoring area in the operation the turbomachine a comparatively critical stress occurs. Furthermore, the invention relates to a turbomachine according to the preamble of claim 11 and a Method for detecting the state of the rotor of a turbomachine according to the preamble of claim 13.
  • the rotor is made up of several juxtaposed rotor disks and a tie rod constructed. In addition to the thermal stresses, it is special the mechanical stresses resulting from the centrifugal force exposed, leaving its components on defects to be examined.
  • the rotor discs are by the known material tests such as B. Ultrasound on defects that appear as ads, examining which after manufacture the rotor disks can be present. The ads indicate flaws, foreign material inclusions, inhomogeneities in the material structure or cracks. The After this initial test as rotor discs recognized as display-free are then used for the construction of the rotor. ad quality means that actually there are no defects or that in the component existing defects in such a way are small, that theoretically according to a fracture mechanical Calculation during operation of the gas turbine from them no critical cracks can arise and grow.
  • the rotors must be destacked for testing, that is in their Rotor components are decomposed to the inside of the rotor from the outside invisible and therefore not examined areas rotor disks for cracks.
  • the permissible number of starts of the gas turbine can be determined can, after checking the rotor components for defects is to be made.
  • FIG. 5 shows a start number crack length diagram after State of the 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 task directed to the rotor is characterized by the features of claim 1, which directed to the turbomachine Task by the features of claim 11 and on the Method directed task by the features of the claim 13 solved.
  • Advantageous embodiments are in the subclaims specified.
  • the solution of the task directed to the rotor provides that in the control area of the rotor a weak point after Type of predetermined breaking point is provided and that at the Operation of turbomachine in monitoring area may be occurring damage to the rotor by a forcibly occurring in the area of the vulnerability and of this point of growing for the rotor disc uncritical Defect is recognizable.
  • the invention is based on the finding that the at the initial inspection does not cover or tolerate defects Crack growth during operation of the turbomachine can trigger. With the inventively provided Vulnerability is targeted a flaw in the outside visible control area. From the vulnerability then one can evoke from the stress collective uncritical defect grow. Only if open Turbomachine and still assembled rotor discovered an uncritical defect located in the control area whose length exceeds a limit, so the condition of the rotor is recognized as 'to be checked'. First then the disassembly of the rotor and an in-depth review the rotor components necessary.
  • the weak point formed by a material weakening which is simple and is inexpensive to produce.
  • this notch out in the control area as a defect grow a crack.
  • the weak point designed so that during operation of the turbomachine this site is caused an uncritical defect, the with another, in the surveillance area by a defect triggered defect is proportionally comparable. Thereby ensures that in the uncritical control area Defects can arise, which can be traced back to im critical monitoring area defects that may occur allow.
  • the weak point is in size and shape chosen so that they are unrecognized or tolerated Defect in the surveillance area corresponds.
  • the rotor comprises a plurality of rotor disks and at least one spanning the rotor disks Tie rods. Indicates at least one of the rotor disks in the control area at revision a critical defect on, so is disassemble the rotor and at least the component in question to check for defects.
  • each rotor disk is a weak point having.
  • Part of the control areas covers an initial revision interval from, after the arithmetic a destacking of the Rotor and a review of the rotor discs required should be.
  • For each additional revision interval can more Control areas with other vulnerabilities and associated Recesses should be provided for the previous operation cause a crack growth.
  • the entire Claim collective acting on the associated vulnerability, to then check the control area for the entire rotor can draw conclusions.
  • control area could be formed in this way be that of the vulnerability with its associated discharge port covers all revision intervals. consequently For each revision, the actual crack length must be recorded and with a predefined assigned to the respective revision permissible crack length compared to the state to determine the rotor.
  • the monitoring area is adjacent at a hub of the rotor disk, because at this point during operation of the turbomachine higher loads may occur. Damage can thus comparatively occur early in this area, allowing its monitoring makes sense.
  • the solution of the task directed to the method proposes for detecting the state of the exposed rotor Turbomachine ago that first the control area of Rotor is examined for a non-critical defect and in the absence of a defect in the control area, the condition is determined as 'not to be checked' or if present one defect on another in the surveillance area ordered defect is closed back, from the subsequent the condition of the rotor is determined.
  • FIG. 6 shows a gas turbine 1 for a compressor 5 Combustion air, a combustion chamber 6 and a turbine 8 for Drive both the compressor 5 and a working machine, z.
  • the turbine 8 and the Compressors 5 are on a common, as a turbine rotor designated rotor 3, with which also the working machine is connected, and which rotatable about its longitudinal axis is stored.
  • the combustion chamber 6 is provided with burners 7 for Combustion of a liquid or gaseous fuel equipped.
  • the gas turbine 1 has a rotationally fixed lower housing half 12, in which in the assembly of the gas turbine 1 of the assembled Rotor 3 is inserted. Subsequently, an upper Housing half 13 mounted to the gas turbine 1 to shut down.
  • the rotor 3 has a central tie rod 10, which several juxtaposed rotor discs 19 clamped together.
  • the compressor 5 as well as the turbine 8 respectively a number of connected to the rotor 3, rotatable Blades 16 on.
  • the blades 16 are annular arranged on the annular rotor discs 19 and form thus a number of blade rows 15.
  • FIG. 1 shows the section through the rotor disk 19 of FIG Gas turbine 1 along its radius.
  • the rotor disk 19 which as a compressor disk or may be formed as a turbine disk runs the rotation axis 2 of the rotor 3.
  • the rotor disk 19 has blade holding grooves 23 for receiving blades 16 at its radially outer end 21.
  • On a front side 25 of the Rotor disk 19 is a freely projecting balcony 27 is provided.
  • the balcony 27 has a control area 29, which in the uncovered state of the assembled rotor 3 is visible from the outside.
  • the rotor 3 is then in the lower Housing half 12 of the gas turbine 1 and the upper half of the housing 13 is decreased.
  • 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 a Kerber zul equivalent.
  • the weak point 31, in the for the function of the rotor 3 uncritical control area 29 is arranged with a in the monitoring area 37 assumed defect 41 in size and effect proportionally comparable. Furthermore, the im Control area 29 occurring stresses with the im Monitoring range 37 occurring loads proportional comparable.
  • the vulnerability 31 be dimensioned so that there is more likely to grow a crack than 40 from an undetected defect 41.
  • the discharge opening could be so far from the Notch, which allows crack growth which extends over several inspection intervals.
  • the one Revision interval respectively assigned permissible crack length, which indicates the condition 'to check' must then always with the actually existing, measured crack length be compared. Accordingly, an evaluation of the Crack growth possible, which by the operation of the gas turbine between two subsequent revisions.
  • FIG. 4 shows a start number crack length diagram which is shown in FIG the invention is applied. On the abscissa is the Start 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 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 as 'check' is classified.
  • 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
  • a second point 61 is defined as the origin of another characteristic 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 determine an intersection 59 with the maximum permissible crack length a notch .
  • 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 vulnerability 31 one up to this point the actual load collective exposed crack growth indicator in the manner of a Predetermined breaking point created, with the conclusions regarding Defects 43 on areas of the rotor disks that are not visible from the outside 19 are 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)
EP04006256A 2004-03-16 2004-03-16 Méthode et appareil permettant d'établir l'état d'un rotor de turbomachine Withdrawn EP1577492A1 (fr)

Priority Applications (9)

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
ES05715936T ES2293543T3 (es) 2004-03-16 2005-03-10 Procedimiento y dispositivo para identificar el estado del rotor de una turbomaquina.
PCT/EP2005/002560 WO2005093220A1 (fr) 2004-03-16 2005-03-10 Procede et dispositif d'identification de l'etat du rotor d'une turbomachine
CNA2005800085009A CN1985069A (zh) 2004-03-16 2005-03-10 用于识别涡轮机转子的状态的方法和装置
RU2006136383/06A RU2377415C2 (ru) 2004-03-16 2005-03-10 Способ и устройство для распознавания состояния ротора машины для превращения кинетической энергии потока в механическую энергию
DE502005001830T DE502005001830D1 (de) 2004-03-16 2005-03-10 Verfahren und vorrichtung zum erkennen des zustands des rotors einer strömungsmaschine
JP2007503244A JP4447637B2 (ja) 2004-03-16 2005-03-10 流体機械の回転子の状態を検知する方法および装置
EP05715936A EP1727970B1 (fr) 2004-03-16 2005-03-10 Methode et appareil permettant d'etablir l'etat d'un rotor de turbomachine
US10/592,768 US7568886B2 (en) 2004-03-16 2005-03-10 Method and device for identifying the state of the rotor of a non-positive-displacement machine

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP1577492A1 true EP1577492A1 (fr) 2005-09-21

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 After (1)

Application Number Title Priority Date Filing Date
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

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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3088661A1 (fr) * 2015-04-28 2016-11-02 Siemens Aktiengesellschaft Surveillance de la fatigue de rotor de turbine à vapeur

Families Citing this family (3)

* 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

Citations (4)

* 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
GB1499550A (en) * 1974-06-28 1978-02-01 Bbc Sulzer Turbomaschinen Apparatus and method for monitoring erosive wear of gas turbine blades
US20020019708A1 (en) * 1999-12-23 2002-02-14 Jorg Pross Method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage
EP1273803A2 (fr) * 2001-07-05 2003-01-08 BOC Edwards Technologies, Limited Pompe à vide

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (4)

* 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
GB1499550A (en) * 1974-06-28 1978-02-01 Bbc Sulzer Turbomaschinen Apparatus and method for monitoring erosive wear of gas turbine blades
US20020019708A1 (en) * 1999-12-23 2002-02-14 Jorg Pross Method for monitoring the creep behavior of rotating components of a compressor stage or turbine stage
EP1273803A2 (fr) * 2001-07-05 2003-01-08 BOC Edwards Technologies, Limited Pompe à vide

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3088661A1 (fr) * 2015-04-28 2016-11-02 Siemens Aktiengesellschaft Surveillance de la fatigue de rotor de turbine à vapeur

Also Published As

Publication number Publication date
EP1727970B1 (fr) 2007-10-31
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
CN1985069A (zh) 2007-06-20
US20080145223A1 (en) 2008-06-19
ES2293543T3 (es) 2008-03-16
DE502005001830D1 (de) 2007-12-13

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