EP1217170A2 - Méthode pour influencer la fréquence propre des aubes de turbine par l'orientation des axes secondaires - Google Patents

Méthode pour influencer la fréquence propre des aubes de turbine par l'orientation des axes secondaires Download PDF

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Publication number
EP1217170A2
EP1217170A2 EP01306925A EP01306925A EP1217170A2 EP 1217170 A2 EP1217170 A2 EP 1217170A2 EP 01306925 A EP01306925 A EP 01306925A EP 01306925 A EP01306925 A EP 01306925A EP 1217170 A2 EP1217170 A2 EP 1217170A2
Authority
EP
European Patent Office
Prior art keywords
turbine bucket
tuning
frequencies
natural frequency
bucket
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Withdrawn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
EP01306925A
Other languages
German (de)
English (en)
Other versions
EP1217170A3 (fr
Inventor
John Zhiqiang Wang
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP1217170A2 publication Critical patent/EP1217170A2/fr
Publication of EP1217170A3 publication Critical patent/EP1217170A3/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Withdrawn legal-status Critical Current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
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
    • B22D27/045—Directionally solidified castings
    • 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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/607—Monocrystallinity

Definitions

  • This invention relates to gas turbine bucket construction and, more particularly, to using secondary orientation to tune turbine bucket natural frequencies.
  • the turbine blade or turbine bucket experiences different dynamic stimuli due to the aerodynamic disturbances from, for example, the up- and down-stream nozzles, the combustor cans, the tip shrouds, etc.
  • any of these stimulus frequencies is close enough to the natural frequency of the rotational turbine bucket, resonance may occur that will likely cause failures, usually catastrophic, to the bucket due to high cycle fatigue. Indeed, a large number of engine failures in the field can be traced back to the root cause of vibration related failures. Thus, it is important in bucket design to avoid resonance during operation by a sufficient margin.
  • a method of manufacturing a turbine bucket includes (a) investment casting the turbine bucket with a single crystal alloy, and (b) tuning a natural frequency of the turbine bucket without modifying physical features of the turbine bucket.
  • Step (b) may be practiced by tuning the natural frequency of the turbine bucket without affecting turbine bucket weight or turbine bucket shape.
  • Step (b) may also be practiced by tuning torsional and stripe mode frequencies without affecting flexure mode frequencies of the turbine bucket.
  • step (b) is preferably practiced by, prior to step (a), placing the crystal seed along a desired direction according to an orientation relative to the engine axial direction.
  • a method of tuning turbine bucket natural frequency includes (a) placing the crystal seed along a desired orientation relative to the engine axial direction, and (b) investment casting the turbine bucket with a single crystal alloy, wherein the desired orientation is selected to tune torsional frequencies without affecting flexure frequencies.
  • the material directions along the X' and Y' axes are termed secondary orientation, while that along the Z' direction is termed as the primary orientation.
  • the secondary orientation is defined by the angle ⁇ s between the engine axial direction X and the material direction X, which is the same as the angle between the engine tangential direction Y and the material direction Y.
  • Operating frequencies of turbine buckets can be determined in the design phase using engineering models and the like as would be apparent to those of ordinary skill in the art.
  • the data for FIGURES 2 and 3 is based on known Finite Element (FE) Analyses (known as ANSYS code) and is validated through engine tests. Similar engineering models by FE analyses can be used to determine bucket natural frequencies. As noted, it is important to avoid resonance by a sufficient margin to improve operating efficiency, and it thus may be necessary to "tune" the natural frequencies of a turbine bucket.
  • FE Finite Element
  • the shear modulus that determines the torsional frequencies is dependent on the secondary orientation ⁇ s .
  • the tensile modulus along the radial direction that determines the flexure frequencies is insensitive to the secondary orientation.
  • the secondary orientation can be used to tune the torsional frequencies without affecting the flexure frequencies.
  • FIGURE 2 shows the change of 1T and 2T frequencies as a function of the secondary orientation.
  • FIGURE 3 shows the change of 1-2S and 1-3S frequencies as a function of the secondary orientation. It is known that changes in the secondary orientation will not affect the flexure frequencies (such as 1 F, 2F, etc.). Moreover, the change in secondary orientation does not entail changes in turbine bucket weight and shape. To implement certain preferred secondary orientation in an investment casting process is a relatively easy operation, thus the impact is minimal on manufacturing cost.
  • FIGURES 2 and 3 the data for FIGURES 2 and 3 is derived from FE analyses. First analyses are conducted by incorporating the secondary orientation in the engineering model, then the results are correlated with the engine test results. Subsequently, the secondary orientation is varied, and the curves are completed.
  • the secondary orientation is controlled by placing the crystal seed along a desired direction. Placing of the crystal seed in the investment casting process does not affect the physical features of the turbine bucket, such as the bucket weight or shape, and does not entail any additional manufacturing operation or cost. As shown in FIGURES 2 and 3, the desired direction of the crystal seed or secondary orientation is selected to effect a desired percentage change in turbine bucket natural frequencies.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP01306925A 2000-12-14 2001-08-14 Méthode pour influencer la fréquence propre des aubes de turbine par l'orientation des axes secondaires Withdrawn EP1217170A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US735503 2000-12-14
US09/735,503 US20020074102A1 (en) 2000-12-14 2000-12-14 Method using secondary orientation to tune bucket natural frequency

Publications (2)

Publication Number Publication Date
EP1217170A2 true EP1217170A2 (fr) 2002-06-26
EP1217170A3 EP1217170A3 (fr) 2003-10-15

Family

ID=24956083

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01306925A Withdrawn EP1217170A3 (fr) 2000-12-14 2001-08-14 Méthode pour influencer la fréquence propre des aubes de turbine par l'orientation des axes secondaires

Country Status (5)

Country Link
US (1) US20020074102A1 (fr)
EP (1) EP1217170A3 (fr)
JP (1) JP2002201902A (fr)
KR (1) KR20020046909A (fr)
CZ (1) CZ20012940A3 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7338259B2 (en) 2004-03-02 2008-03-04 United Technologies Corporation High modulus metallic component for high vibratory operation
EP1584871A3 (fr) * 2004-04-08 2008-11-19 United Technologies Corporation Articles monocrystalines avec orientation cristallographique contrôlée
CN102451619A (zh) * 2010-10-15 2012-05-16 中国石油化工股份有限公司 Y型分子筛膜及二氯甲烷中水分的脱除方法
EP2884050A1 (fr) * 2013-12-16 2015-06-17 MTU Aero Engines GmbH Grille d'aube et procédé associé
DE102018202725A1 (de) 2018-02-22 2019-08-22 MTU Aero Engines AG Anordnung von Schaufeln in einem Schaufelkranz auf Grundlage einer primären Kristallorientierung

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7988412B2 (en) * 2007-08-24 2011-08-02 General Electric Company Structures for damping of turbine components
US20120101792A1 (en) * 2010-10-25 2012-04-26 Alexander Staroselsky Turbine component and method for developing a component
ES2583756T3 (es) * 2011-04-01 2016-09-22 MTU Aero Engines AG Disposición de álabes para una turbomáquina
DE102014214270A1 (de) * 2014-07-22 2016-02-18 MTU Aero Engines AG Schaufelgitter für eine Turbomaschine
FR3038341B1 (fr) * 2015-07-03 2017-07-28 Snecma Procede d'alteration de la loi de vrillage de la surface aerodynamique d'une pale de soufflante de moteur a turbine a gaz
CN109269745B (zh) * 2018-10-30 2021-01-19 湖南科技大学 基于托辊激振法的大型斗轮机悬臂低频振动测试方法
US11499431B2 (en) 2021-01-06 2022-11-15 General Electric Company Engine component with structural segment

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3044746A (en) * 1960-05-18 1962-07-17 Gen Electric Fluid-flow machinery blading
US4605452A (en) * 1981-12-14 1986-08-12 United Technologies Corporation Single crystal articles having controlled secondary crystallographic orientation
US4804311A (en) * 1981-12-14 1989-02-14 United Technologies Corporation Transverse directional solidification of metal single crystal articles
US4919593A (en) * 1988-08-30 1990-04-24 Westinghouse Electric Corp. Retrofitted rotor blades for steam turbines and method of making the same
US5292385A (en) * 1991-12-18 1994-03-08 Alliedsignal Inc. Turbine rotor having improved rim durability
JPH0633701A (ja) * 1992-07-16 1994-02-08 Hitachi Ltd ガスタービン用単結晶動翼及びその製造法
US5682747A (en) * 1996-04-10 1997-11-04 General Electric Company Gas turbine combustor heat shield of casted super alloy
JPH1136805A (ja) * 1997-07-14 1999-02-09 Hitachi Ltd タービン翼

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7338259B2 (en) 2004-03-02 2008-03-04 United Technologies Corporation High modulus metallic component for high vibratory operation
US7871247B2 (en) 2004-03-02 2011-01-18 United Technologies Corporation High modulus metallic component for high vibratory operation
EP1584871A3 (fr) * 2004-04-08 2008-11-19 United Technologies Corporation Articles monocrystalines avec orientation cristallographique contrôlée
CN102451619A (zh) * 2010-10-15 2012-05-16 中国石油化工股份有限公司 Y型分子筛膜及二氯甲烷中水分的脱除方法
CN102451619B (zh) * 2010-10-15 2013-11-20 中国石油化工股份有限公司 Y型分子筛膜及二氯甲烷中水分的脱除方法
EP2884050A1 (fr) * 2013-12-16 2015-06-17 MTU Aero Engines GmbH Grille d'aube et procédé associé
EP2891767A1 (fr) * 2013-12-16 2015-07-08 MTU Aero Engines GmbH Grille d'aube et procédé associé
US9765633B2 (en) 2013-12-16 2017-09-19 MTU Aero Engines AG Blade cascade
US9850766B2 (en) 2013-12-16 2017-12-26 MTU Aero Engines AG Blade cascade
DE102018202725A1 (de) 2018-02-22 2019-08-22 MTU Aero Engines AG Anordnung von Schaufeln in einem Schaufelkranz auf Grundlage einer primären Kristallorientierung

Also Published As

Publication number Publication date
CZ20012940A3 (cs) 2002-07-17
US20020074102A1 (en) 2002-06-20
KR20020046909A (ko) 2002-06-21
EP1217170A3 (fr) 2003-10-15
JP2002201902A (ja) 2002-07-19

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