EP1640562A1 - Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine - Google Patents

Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine Download PDF

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Publication number
EP1640562A1
EP1640562A1 EP04022725A EP04022725A EP1640562A1 EP 1640562 A1 EP1640562 A1 EP 1640562A1 EP 04022725 A EP04022725 A EP 04022725A EP 04022725 A EP04022725 A EP 04022725A EP 1640562 A1 EP1640562 A1 EP 1640562A1
Authority
EP
European Patent Office
Prior art keywords
blade
component
base material
recess
edge
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Withdrawn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
EP04022725A
Other languages
German (de)
English (en)
Inventor
Walter David
Christoph Dr. Richter
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 EP04022725A priority Critical patent/EP1640562A1/fr
Publication of EP1640562A1 publication Critical patent/EP1640562A1/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Withdrawn legal-status Critical Current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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
    • F05C2201/00—Metals
    • F05C2201/90—Alloys not otherwise provided for
    • 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
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
    • F05D2300/133—Titanium
    • 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
    • F05D2300/50—Intrinsic material properties or characteristics
    • F05D2300/501—Elasticity

Definitions

  • the invention relates to a method for producing a blade made of a base material with a blade side having a suction side, a pressure side, an inlet edge, an outlet edge and a blade tip and with a blade root.
  • the invention further relates to a blade of a base material having a suction side, a pressure side, an inlet edge, an outlet edge and a blade tip having blade and a blade root.
  • a turbine blade as an embodiment of a blade is used in turbomachines.
  • a turbomachine is e.g. a steam turbine or a gas turbine.
  • the following statements relate to a turbine blade in a steam turbine. However, the statements can generally be related to blades and turbomachinery.
  • a flow medium flows in on the input side and flows out of the steam turbine via outlet nozzles.
  • the temperature and pressure of the flow medium change within the steam turbine.
  • the energy of the flow medium is converted into rotational energy.
  • the blades and the vanes must be made elongated.
  • the last turbine blades of a low-pressure steam turbine are so long that they get into vibration during operation.
  • the natural frequencies of the blades can also be reduced by the incorporation of vibration reducing components, e.g. Cover plates or support wings, change.
  • the cover plates are in this case formed such that a swing is prevented by a touch of two adjacent cover plates.
  • Support wings lead by mutual jamming to a suppression of disturbing vibrations.
  • a modification of the airfoil can cause vibrations to be suppressed.
  • modification of the airfoil that is optimized with regard to a frequency change results in that the aerodynamics of the airfoil are no longer optimal. This is due to the compromise between mechanics and aerodynamics.
  • the present invention has for its object a method for producing a blade made of a base material with a suction side, a pressure side, an inlet edge, a trailing edge and a blade tip having blade and specify a blade root, with which it is possible further modifications to blades for influencing to perform the natural frequency.
  • Another object of the invention is to provide a blade with variable natural frequencies.
  • the object directed to the method is achieved by a method for producing a blade from a base material having a suction side, a pressure side, an inlet edge, an outlet edge and a blade tip having a blade root and with a blade root, wherein a recess is provided in the region of the blade tip and in this recess a component for frequency detuning from a material not identical to the base material is attached.
  • the task directed towards the blade is achieved by a blade made of a base material with a blade side having a suction side, an inlet edge, an outlet edge and a blade tip and having a blade root, wherein a recess is provided in the region of the blade tip and in this Recess a component for changing the frequency of the blade is mounted, wherein the component consists of a material that is not identical to the base material.
  • the component is welded to the base material. In a further advantageous embodiment, the component is soldered to the base material.
  • the component which consists of a material that is not identical to the base material, very quickly and easily attached to the base material.
  • vibration shapes of the blade have a deformation along the blade root, it is advantageous to arrange the component in a longitudinal direction of the blade.
  • the density of the material of the component is selected such that this density is higher than the density of the base material.
  • the material of the component is chosen such that the Modulus of elasticity is greater than the elastic modulus of the base material.
  • the blade is formed from a base material of a titanium alloy.
  • the material of the component is a beta titanium alloy.
  • Titanium offers high strength at low weight.
  • the disadvantage is that a titanium alloy is expensive.
  • a beta-titanium alloy has a higher density and a higher modulus of elasticity compared to a titanium alloy and therefore lends itself to being used as a component, in particular because of its metallurgically similar properties.
  • the component has a length (1) which is at least 1/3 of the total length (L) of the blade. It is also advantageous if the component has a width (b) which is at least 1/3 of the overall width (B) of the blade, measured on an upper blade edge.
  • the flow medium transfers its momentum predominantly at the leading edge of the blade. Vibration of the blade is effectively avoided if the pulse hits directly on the component, which is designed such that it does not come to a vibration at a certain momentum transfer. The resulting stress can be reduced as much as possible.
  • the component is arranged on the suction side. Since the suction side is particularly influenced by the inflowing flow medium, vibrations are prevented by a stiffening in the form of a component.
  • the blade is designed as a turbine blade for use in a steam turbine. In a further advantageous embodiment, the blade is designed as a turbine blade for use in a gas turbine.
  • the steam turbine 1 shown in FIG. 1 has an inflow opening 2 and an outflow opening 3.
  • the steam turbine 1 has an outer housing 4, in which an inner housing 5 is arranged. On the inner housing 5 more vanes 6 are arranged.
  • a rotor 7 is about an axis of rotation 8 rotatably mounted. The rotor 7 carries moving blades 9. The moving blades 9 engage in the guide vanes 6.
  • a flow medium flows through the inlet opening 2 through the individual guide vanes 6 and rotor blades 9.
  • the rotor 7 is hereby set in a rotary motion.
  • the blades 9 and the guide vanes 6 in a last stage 10 are comparatively long.
  • the length of the blades 9 and the guide vanes 6 leads due to the impinging particles of the flow medium to an undesirable swing.
  • the blade 9 as an embodiment of a blade 9 is made of a base material and is formed with a suction side 11, a not shown pressure side, an inlet edge 12, a trailing edge 13 having blade 15. Furthermore, the blade 9 has a blade tip 14.
  • the thus formed airfoil 15 forms together with a blade root 16, the blade 9.
  • a recess 17 is provided on the south side (11).
  • a component 18 is mounted for frequency detuning, the component 18 is made of a material that is not identical to the base material. The component 18 is either welded or soldered to the base material. Other mounting options are conceivable.
  • the length of the recess 17 or of the component 18 is approximately one third of the total length of the entire blade 15.
  • the length of the component 18 can be either shorter or longer, depending on which frequencies of the blade Shovel 9 should be changed.
  • the component 18 is formed of a material whose density is higher than the density of the base material.
  • the material of the component 18 may also be made of a material whose modulus of elasticity is higher than the elastic modulus of the base material.
  • the base material of the blade 9 is formed of a titanium alloy and the material of the component 18 is a beta-titanium alloy.
  • FIG. 3 shows a perspective view of the blade 9 shown in FIG.
  • the component 18 is in this case mounted on a surface of the blade 9 in the recess 17.
  • the component 18 can also be attached continuously to the opposite pressure side.
  • the component 18 is arranged from the pressure side 11 to the opposite suction side.
  • the recess 17 can thereby be made particularly easy.
  • Another parameter for influencing the frequency of the blades 9 is the length of the frequency-tuning component 18.
  • the length (1) of the component 18 is about one third as long as the total length (L) of the blade 9. Depending on the frequency to be changed, the length of the component 18 must be varied.
  • the component 18 is arranged in a longitudinal direction of the blade 9.
  • the component 18 has a width (b) which is at least one third of the total width (B) of the blade 9, measured at an upper blade edge 19.
  • the blade 9 can be used as a turbine blade in a steam turbine or in a gas turbine. The use in other flow machines, such as pumps or compressors, is also possible.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04022725A 2004-09-23 2004-09-23 Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine Withdrawn EP1640562A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP04022725A EP1640562A1 (fr) 2004-09-23 2004-09-23 Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04022725A EP1640562A1 (fr) 2004-09-23 2004-09-23 Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine

Publications (1)

Publication Number Publication Date
EP1640562A1 true EP1640562A1 (fr) 2006-03-29

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ID=34926689

Family Applications (1)

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EP04022725A Withdrawn EP1640562A1 (fr) 2004-09-23 2004-09-23 Procédé de syntonisation de fréquence d'une aube de turbine et aube de turbine

Country Status (1)

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EP (1) EP1640562A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1985803A1 (fr) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Procédé pour la fabrication des aubes de turbine avec revêtement
DE102009033618A1 (de) 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine
EP2762678A1 (fr) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Procédé de désaccordage d'une matrice d'aube directrice
FR3008185A1 (fr) * 2013-07-03 2015-01-09 Snecma Insert comprenant une surface externe faisant partie d'au moins un profil aerodynamique d'une aube de test de turbomachine
US9752441B2 (en) 2012-01-31 2017-09-05 United Technologies Corporation Gas turbine rotary blade with tip insert
US20210123347A1 (en) * 2019-10-23 2021-04-29 Rolls-Royce Corporation Gas turbine engine blades with airfoil plugs for selected tuning
US11015462B2 (en) * 2018-05-22 2021-05-25 Safran Aircraft Engines Blade body and a blade made of composite material having fiber reinforcement made up both of three-dimensional weaving and also of short fibers, and method of fabrication
CN113606189A (zh) * 2021-08-23 2021-11-05 中国联合重型燃气轮机技术有限公司 压气机叶片及其调频槽口尺寸的确定方法、压气机和燃气轮机
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1024218A (fr) * 1950-09-01 1953-03-30 Rateau Soc Dispositif d'amortissement de vibrations pour pales d'hélices et ailettes de turbomachines
US3796513A (en) * 1972-06-19 1974-03-12 Westinghouse Electric Corp High damping blades
GB1479855A (en) * 1976-04-23 1977-07-13 Statni Vyzkumny Ustav Material Protective coating for titanium alloy blades for turbine and turbo-compressor rotors
US4118147A (en) * 1976-12-22 1978-10-03 General Electric Company Composite reinforcement of metallic airfoils
US4178667A (en) * 1978-03-06 1979-12-18 General Motors Corporation Method of controlling turbomachine blade flutter
GB2142387A (en) * 1983-07-02 1985-01-16 Rolls Royce An aerofoil for a gas turbine engine
EP0852164A1 (fr) * 1995-09-13 1998-07-08 Kabushiki Kaisha Toshiba Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane
EP0924380A2 (fr) * 1997-12-22 1999-06-23 General Electric Company Aube striée pour turbomachine

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1024218A (fr) * 1950-09-01 1953-03-30 Rateau Soc Dispositif d'amortissement de vibrations pour pales d'hélices et ailettes de turbomachines
US3796513A (en) * 1972-06-19 1974-03-12 Westinghouse Electric Corp High damping blades
GB1479855A (en) * 1976-04-23 1977-07-13 Statni Vyzkumny Ustav Material Protective coating for titanium alloy blades for turbine and turbo-compressor rotors
US4118147A (en) * 1976-12-22 1978-10-03 General Electric Company Composite reinforcement of metallic airfoils
US4178667A (en) * 1978-03-06 1979-12-18 General Motors Corporation Method of controlling turbomachine blade flutter
GB2142387A (en) * 1983-07-02 1985-01-16 Rolls Royce An aerofoil for a gas turbine engine
EP0852164A1 (fr) * 1995-09-13 1998-07-08 Kabushiki Kaisha Toshiba Procede de fabrication de pales de turbine en alliage de titane et pales de turbines en alliage de titane
EP0924380A2 (fr) * 1997-12-22 1999-06-23 General Electric Company Aube striée pour turbomachine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2008128902A1 (fr) * 2007-04-23 2008-10-30 Siemens Aktiengesellschaft Procédé de fabrication d'aubes mobiles de turbine recouvertes et bague d'aube mobile pour un rotor d'une turbine à impulsions axiales
US8607455B2 (en) 2007-04-23 2013-12-17 Siemens Aktiengesellschaft Method for the production of coated turbine moving blades and moving-blade ring for a rotor of an axial-throughflow turbine
EP1985803A1 (fr) * 2007-04-23 2008-10-29 Siemens Aktiengesellschaft Procédé pour la fabrication des aubes de turbine avec revêtement
DE102009033618A1 (de) 2009-07-17 2011-01-20 Mtu Aero Engines Gmbh Verfahren zur Frequenzverstimmung eines Rotorkörpers einer Gasturbine und ein Rotor einer Gasturbine
US9752441B2 (en) 2012-01-31 2017-09-05 United Technologies Corporation Gas turbine rotary blade with tip insert
EP2762678A1 (fr) * 2013-02-05 2014-08-06 Siemens Aktiengesellschaft Procédé de désaccordage d'une matrice d'aube directrice
WO2014122028A1 (fr) * 2013-02-05 2014-08-14 Siemens Aktiengesellschaft Procédé permettant de modifier les fréquences au sein d'un ensemble d'aubes mobiles
US9835034B2 (en) 2013-02-05 2017-12-05 Siemens Aktiengesellschaft Method for detuning a rotor-blade cascade
FR3008185A1 (fr) * 2013-07-03 2015-01-09 Snecma Insert comprenant une surface externe faisant partie d'au moins un profil aerodynamique d'une aube de test de turbomachine
US9695693B2 (en) 2013-07-03 2017-07-04 Snecma Insert with an external surface which is part of at least one aerodynamic profile of a turbomachine test blade
US11015462B2 (en) * 2018-05-22 2021-05-25 Safran Aircraft Engines Blade body and a blade made of composite material having fiber reinforcement made up both of three-dimensional weaving and also of short fibers, and method of fabrication
US20210123347A1 (en) * 2019-10-23 2021-04-29 Rolls-Royce Corporation Gas turbine engine blades with airfoil plugs for selected tuning
US11220913B2 (en) * 2019-10-23 2022-01-11 Rolls-Royce Corporation Gas turbine engine blades with airfoil plugs for selected tuning
US11536144B2 (en) 2020-09-30 2022-12-27 General Electric Company Rotor blade damping structures
US11739645B2 (en) 2020-09-30 2023-08-29 General Electric Company Vibrational dampening elements
CN113606189A (zh) * 2021-08-23 2021-11-05 中国联合重型燃气轮机技术有限公司 压气机叶片及其调频槽口尺寸的确定方法、压气机和燃气轮机

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