EP2762678A1 - Procédé de désaccordage d'une matrice d'aube directrice - Google Patents

Procédé de désaccordage d'une matrice d'aube directrice Download PDF

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Publication number
EP2762678A1
EP2762678A1 EP13153956.1A EP13153956A EP2762678A1 EP 2762678 A1 EP2762678 A1 EP 2762678A1 EP 13153956 A EP13153956 A EP 13153956A EP 2762678 A1 EP2762678 A1 EP 2762678A1
Authority
EP
European Patent Office
Prior art keywords
blade
values
natural frequency
centrifugal force
measured
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Withdrawn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
EP13153956.1A
Other languages
German (de)
English (en)
Inventor
Thomas Grönsfelder
Jan Walkenhorst
Armin De Lazzer
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP13153956.1A priority Critical patent/EP2762678A1/fr
Priority to CN201480007356.6A priority patent/CN104968894B/zh
Priority to KR1020157020876A priority patent/KR20150112989A/ko
Priority to JP2015555656A priority patent/JP6054550B2/ja
Priority to PCT/EP2014/051322 priority patent/WO2014122028A1/fr
Priority to EP14702486.3A priority patent/EP2912272B1/fr
Priority to PL14702486T priority patent/PL2912272T3/pl
Priority to US14/764,062 priority patent/US9835034B2/en
Publication of EP2762678A1 publication Critical patent/EP2762678A1/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Definitions

  • the invention relates to a method for detuning a blade lattice.
  • a turbomachine has rotor blades arranged in the rotor blades, which can be regarded as firmly clamped at their blade roots and can oscillate during operation of the turbomachine. Depending on the operating state of the turbomachine, this can lead to oscillation processes in which oscillation states occur with high and critical stresses in the rotor blade. When the blade is stressed for a long time due to critical stress conditions, material fatigue occurs, which can ultimately lead to a reduction in the service life of the blade, which necessitates replacement of the rotor blade.
  • the object of the invention is to provide a method for detuning a blade lattice of a turbomachine, wherein the blades have a long life in the operation of the turbomachine.
  • the inventive method for detuning, in particular the rotor-dynamic detuning, of a turbine blade having a plurality of blades has the steps of: a) setting for each of the blades of the blade grid at least one desired natural frequency ⁇ F, S , which the blade for at least one predetermined vibration mode in normal operation of the turbomachine under a centrifugal force has such that the vibration load of the blade lattice under the centrifugal force is below a tolerance limit; b) establishing a table of values ⁇ F (m, r S ) with selected discrete mass values m and radial centroid r s , resulting from variations of the nominal geometry of the blade, and determining the respective natural frequency ⁇ F under centrifugal force for each selected pair of values m and r S ; c) measuring the mass m I and the radial center of gravity position r S, I of one of the moving blades; d) determining an actual natural frequency ⁇ F, I of the blade under the
  • the natural frequency ⁇ F, I under the centrifugal force can advantageously be determined with high accuracy.
  • the method according to the invention it is also advantageously possible to set this natural frequency ⁇ F, I with a high accuracy and to the specified desired natural frequency ⁇ F, S approximate.
  • the vibration load of the blade during operation of the turbomachine can be reduced, thereby extending the life of the blade.
  • the method is simple to perform because, for a precise determination of the actual natural frequency ⁇ F, I, surprisingly enough, it is sufficient to measure m I and r S, I of the blade without their complete geometry.
  • m I and r S, I are easily measured variables, for example, m I can be determined by means of a balance.
  • the predetermined vibration modes are preferably selected such that the natural frequencies ⁇ F, S associated with the vibration modes are equal to or lower than a multiple harmonic of the rotor rotational frequency, in particular eight times the harmonic, one value table ⁇ F (m, r s ) for a plurality or for all of the vibration modes is set up, the actual natural frequency ⁇ F, I is determined for each table of values and the value pair m S and r S, S is selected such that the determined ⁇ F, I to the set ⁇ F, S at least approximate.
  • the inventive method for detuning, in particular the rotor-dynamic detuning, of a turbine blade having a plurality of blades has the steps of: a) setting for each of the blades of the blade grid at least one desired natural frequency ⁇ F, S , which the blade for at least one predetermined vibration mode in normal operation of the turbomachine under a centrifugal force has such that the vibration load of the blade lattice under the centrifugal force is below a tolerance limit; b) establishing a value table ⁇ F (m, r S ) and a table of values ⁇ S (m, r S ) with selected discrete mass values m and radial centroid r s , resulting from variations of the nominal geometry of the blade, and determining the respective natural frequency ⁇ F under the centrifugal force and the respective natural frequency ⁇ S at the standstill of the blade for each selected value pair m and r S ; c) measuring the mass m I and the radial center of gravity r
  • the actual natural frequency ⁇ F, I under the centrifugal force can advantageously be determined with an even higher accuracy. It is also possible to use only the measurement of the natural frequency ⁇ S, I at standstill to control the ablation, without repeating the measurement of m I and r S, I.
  • the predetermined oscillation modes are preferably selected such that the natural frequencies ⁇ F, S associated with the oscillation modes are equal to or lower than a multiple harmonic of the rotor rotational frequency, in particular the eightfold harmonics, one value table ⁇ F (m, r s ) and one each Value table ⁇ S (m, r S ) is set up for a majority or all of the vibration modes, the actual natural frequency ⁇ F, I and the actual natural frequency ⁇ S, I is determined for each table of values, the value pair m S and r S , S is selected such that the determined ⁇ F, I approach the fixed ⁇ F, S at least and the natural frequencies ⁇ S, I are measured for the predetermined vibration modes.
  • the variations in nominal geometry preferably include thickening and / or thinning of the blade in each radial Section or in radial sections. It is preferred that the variations in the nominal geometry have a linear variation in the thickness of the blade over the radius. It is advantageously possible to set up the value table by thickening and thinning the nominal geometry with an accuracy sufficient for determining the natural frequencies ⁇ F and ⁇ S.
  • the desired natural frequencies ⁇ F, S are preferably set such that adjacent blades arranged in the blade lattice have unequal nominal natural frequencies ⁇ F, S and that the desired natural frequencies ⁇ F, S are different from the rotor rotational frequency during normal operation of the turbomachine up to and including a multiple harmonic of the rotor rotational frequency, in particular the eightfold harmonics of the rotor rotational frequency.
  • the measurement of the mass m 1 and the radial center of gravity position r S, I takes place relative to a reference blade, which has been measured three-dimensionally, in particular by means of a coordinate measuring machine and / or by means of an optical method.
  • the accuracy of a measurement depends on the size of the measuring range, with a larger measuring range resulting in a lower accuracy.
  • the value pair m S and r S, S is selected such that the imbalance of the rotor is reduced and / or that the effort for removal is minimal.
  • the knowledge of the value pair m S and r S, S is sufficient for a balancing of the rotor, so that advantageous by the removal of the material can be done detuning and balancing of the blade grid in a common process step.
  • the removal of the material can also be done so that the amount of material to be removed is minimized.
  • the predetermined vibration mode is preferably selected such that the natural frequency ⁇ F, S of the predetermined vibration mode is equal to or lower than the multiple harmonic of the rotor rotational frequency, in particular the eightfold harmonic of the rotor rotational frequency.
  • the natural frequencies ⁇ F and / or ⁇ I are preferably determined by calculation, in particular by means of a finite element method.
  • the blade when measuring the natural frequency ⁇ S, I, the blade is clamped to its blade root, the vibration of the blade is excited and the vibration is measured.
  • the vibration is preferably measured by means of vibration sensors, acceleration sensors, strain gauges, piezoelectric sensors and / or optical methods. This is a simple method for determining the natural frequency.
  • FIG. 1 shows three blades 1 of a turbomachine, wherein the first blade in its nominal geometry 5, the second blade both in its nominal geometry 5 and in a first variation 6 and a second variation 7 and the third blade both in their nominal geometry 5 and in a third Variation 8 and a fourth variation 9 are shown.
  • the rotor blades 1 have a blade root 2, which is fixedly mounted on a rotor shaft 4 of the turbomachine, and a blade tip 3 facing away from the blade root 2.
  • a vibration node is arranged on the blade root 2.
  • the radius r of the blade 1 is directed from the blade root 2 to the blade tip 3.
  • the second blade shows variations 6, 7 of the nominal geometry 5, in which, starting from the nominal geometry 5, the mass m is not changed, however, the radial center of gravity position r S of the blade.
  • the mass m is increased by uniformly thickening the second blade at each radial distance r from the rotation axis, and in the second variation 7, the mass m is reduced by uniformly thinning the second blade at each radial distance r.
  • the thickness of the blade in the circumferential direction and / or the axial direction is varied linearly over the radius r.
  • the blade is thickened at its blade root 2 and thinned at its blade tip 3
  • the blade is thinned at its blade root 2 and thickened at its blade tip 3.
  • the variations 8, 9 can also be carried out such that both the mass m and the radial center of gravity r S are changed.
  • a multiplicity of variations of the nominal geometry 5 are carried out and for each variation a natural frequency ⁇ S of the lowest frequency bending vibration of the blade 1 clamped at its blade root 2 and at a standstill is calculated by means of a finite element method. Furthermore, the natural frequency ⁇ F of the same bending vibration is calculated for each variation, taking into account the centrifugal force acting on the moving blade 1 during normal operation of the turbomachine. Optionally, when calculating ⁇ F , an increased temperature and thus changing material properties can also be taken into account. For a given blade lattice, it is advantageously only necessary to perform the variations of the nominal geometry once.
  • FIG. 3 the method according to the invention is shown in a flow chart. It is set for each of the blades 1 of the blade lattice a nominal natural frequency ⁇ F, S 14, which has the blade 1 for the lowest frequency bending vibration of the blade 2 fixedly clamped blade 1 during normal operation of the turbomachine under a centrifugal force, such that the Vibration load of the blade lattice below the centrifugal force is below a tolerance limit.
  • This is achieved by having rotor blades adjacently arranged in the blade lattice having unequal nominal natural frequencies ⁇ F, S and that the nominal natural frequencies ⁇ F, S are different from the rotor rotational frequency during normal operation of the turbomachine up to and including 8 times the rotor rotational frequency.
  • ⁇ S a corresponding desired natural frequency ⁇ S, S is determined 15, which has the blade 1 for the lowest-frequency bending vibration of the blade 1 firmly clamped to its blade root 2 at standstill.
  • the value table ⁇ S (m, r S ) and the value table ⁇ F (m, r S ) are set 16.
  • An actual target adjustment 21 is performed by comparing ⁇ F, I with ⁇ F, S.
  • a value pair m S and r S, S is selected from the value table ⁇ F (m, r S ) such that ⁇ F, I an ⁇ F, S is at least approximated, and material is removed from the blade 1 such that m I and r S, I correspond to the value pair m S and r S, S.
  • a plurality of value pairs m S and r S, S are generally available in order to achieve a certain natural frequency ⁇ F, S. From the plurality of value pairs, a pair of values m S and r S, S can be selected such that the rotor of the turbomachine is balanced and / or that the effort for removal is minimal.
  • the removal 24 can be done for example by grinding.
  • the natural frequency ⁇ S, I of the blade 1 can be measured 20 at a standstill.
  • the blade 1 is clamped to its blade root 2, the vibration of the blade 1 is excited, for example by a beat, and the sound emitted by the blade 1 is measured.
  • the mass m and radial center of gravity r S of the blade 1 can be measured 19. With a particularly high accuracy, the control can be performed by both the natural frequency ⁇ S, I 20 and the mass m and radial Center of gravity r S 19 are measured.
  • optional process steps 22 may be performed on the blade 1, such as applying a coating. Subsequently, the blade 1 is installed in the blade grid 23.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13153956.1A 2013-02-05 2013-02-05 Procédé de désaccordage d'une matrice d'aube directrice Withdrawn EP2762678A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP13153956.1A EP2762678A1 (fr) 2013-02-05 2013-02-05 Procédé de désaccordage d'une matrice d'aube directrice
CN201480007356.6A CN104968894B (zh) 2013-02-05 2014-01-23 用于解谐工作叶栅的方法
KR1020157020876A KR20150112989A (ko) 2013-02-05 2014-01-23 로터 블레이드 캐스케이드를 디튜닝하기 위한 방법
JP2015555656A JP6054550B2 (ja) 2013-02-05 2014-01-23 ロータブレード列の離調方法
PCT/EP2014/051322 WO2014122028A1 (fr) 2013-02-05 2014-01-23 Procédé permettant de modifier les fréquences au sein d'un ensemble d'aubes mobiles
EP14702486.3A EP2912272B1 (fr) 2013-02-05 2014-01-23 Procédé de désaccordage d'une matrice d'aube directrice
PL14702486T PL2912272T3 (pl) 2013-02-05 2014-01-23 Sposób przestrajania kratki łopat wirnika
US14/764,062 US9835034B2 (en) 2013-02-05 2014-01-23 Method for detuning a rotor-blade cascade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13153956.1A EP2762678A1 (fr) 2013-02-05 2013-02-05 Procédé de désaccordage d'une matrice d'aube directrice

Publications (1)

Publication Number Publication Date
EP2762678A1 true EP2762678A1 (fr) 2014-08-06

Family

ID=47789964

Family Applications (2)

Application Number Title Priority Date Filing Date
EP13153956.1A Withdrawn EP2762678A1 (fr) 2013-02-05 2013-02-05 Procédé de désaccordage d'une matrice d'aube directrice
EP14702486.3A Not-in-force EP2912272B1 (fr) 2013-02-05 2014-01-23 Procédé de désaccordage d'une matrice d'aube directrice

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP14702486.3A Not-in-force EP2912272B1 (fr) 2013-02-05 2014-01-23 Procédé de désaccordage d'une matrice d'aube directrice

Country Status (7)

Country Link
US (1) US9835034B2 (fr)
EP (2) EP2762678A1 (fr)
JP (1) JP6054550B2 (fr)
KR (1) KR20150112989A (fr)
CN (1) CN104968894B (fr)
PL (1) PL2912272T3 (fr)
WO (1) WO2014122028A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017113998A1 (de) 2017-06-23 2018-12-27 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Erzeugung und Auswahl eines Verstimmungsmusters eines eine Mehrzahl von Laufschaufeln aufweisenden Laufrads einer Strömungsmaschine

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3043131B1 (fr) * 2015-10-28 2017-11-03 Snecma Procede pour introduire un desaccordage volontaire dans une roue aubagee de turbomachine
EP3187685A1 (fr) * 2015-12-28 2017-07-05 Siemens Aktiengesellschaft Procede de fabrication d'un corps de base d'un aube de turbine
EP3239460A1 (fr) * 2016-04-27 2017-11-01 Siemens Aktiengesellschaft Procede de profilage d'aubes d'une turbomachine axiale

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US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
EP1589191A1 (fr) * 2004-04-20 2005-10-26 Snecma Procédé pour introduire un désaccordage volontaire sur une roue aubagée de turbomachine. Roue aubagée présentant un désaccordage volontaire
EP1640562A1 (fr) * 2004-09-23 2006-03-29 Siemens Aktiengesellschaft Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine
DE102009033618A1 (de) * 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine

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US4108573A (en) 1977-01-26 1978-08-22 Westinghouse Electric Corp. Vibratory tuning of rotatable blades for elastic fluid machines
JPS54114619A (en) 1978-02-28 1979-09-06 Toshiba Corp Natural frequency adjusting method of turbine blade
JPS5993901A (ja) * 1982-11-17 1984-05-30 Toshiba Corp 蒸気タ−ビン動翼
JPS59150903A (ja) 1983-02-09 1984-08-29 Toshiba Corp 回転機械の翼配列構造
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JP3637284B2 (ja) * 2001-03-01 2005-04-13 三菱重工業株式会社 動翼振動数の推定装置、及び、その推定方法
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EP2434098A1 (fr) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Agencement d'aubes et turbine à gaz associée
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Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6042338A (en) * 1998-04-08 2000-03-28 Alliedsignal Inc. Detuned fan blade apparatus and method
EP1589191A1 (fr) * 2004-04-20 2005-10-26 Snecma Procédé pour introduire un désaccordage volontaire sur une roue aubagée de turbomachine. Roue aubagée présentant un désaccordage volontaire
EP1640562A1 (fr) * 2004-09-23 2006-03-29 Siemens Aktiengesellschaft Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine
DE102009033618A1 (de) * 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017113998A1 (de) 2017-06-23 2018-12-27 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Erzeugung und Auswahl eines Verstimmungsmusters eines eine Mehrzahl von Laufschaufeln aufweisenden Laufrads einer Strömungsmaschine

Also Published As

Publication number Publication date
CN104968894A (zh) 2015-10-07
JP6054550B2 (ja) 2016-12-27
CN104968894B (zh) 2016-11-09
EP2912272A1 (fr) 2015-09-02
EP2912272B1 (fr) 2016-11-02
PL2912272T3 (pl) 2017-04-28
WO2014122028A1 (fr) 2014-08-14
US20160010461A1 (en) 2016-01-14
US9835034B2 (en) 2017-12-05
JP2016507023A (ja) 2016-03-07
KR20150112989A (ko) 2015-10-07

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