EP1925781A1 - Agencement d'aubes - Google Patents

Agencement d'aubes Download PDF

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Publication number
EP1925781A1
EP1925781A1 EP06024326A EP06024326A EP1925781A1 EP 1925781 A1 EP1925781 A1 EP 1925781A1 EP 06024326 A EP06024326 A EP 06024326A EP 06024326 A EP06024326 A EP 06024326A EP 1925781 A1 EP1925781 A1 EP 1925781A1
Authority
EP
European Patent Office
Prior art keywords
rotor
damping elements
damping
blade
contact
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Withdrawn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
EP06024326A
Other languages
German (de)
English (en)
Inventor
Andreas Dr. Kayser
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 EP06024326A priority Critical patent/EP1925781A1/fr
Priority to PCT/EP2007/061469 priority patent/WO2008061856A1/fr
Priority to AT07821832T priority patent/ATE469288T1/de
Priority to CN2007800436875A priority patent/CN101542073B/zh
Priority to ES07821832T priority patent/ES2345686T3/es
Priority to EP07821832A priority patent/EP2094946B1/fr
Priority to RU2009123844/06A priority patent/RU2417323C2/ru
Priority to US12/515,845 priority patent/US8167563B2/en
Priority to JP2009537583A priority patent/JP4806075B2/ja
Priority to DE502007003972T priority patent/DE502007003972D1/de
Publication of EP1925781A1 publication Critical patent/EP1925781A1/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Withdrawn legal-status Critical Current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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • the invention relates to a blade assembly having a rotor and a plurality of blades arranged on the circumference of the rotor, wherein a plurality of damping elements in the circumferential direction of the rotor are arranged one behind the other between the blades of at least one blade pair, which is formed of two adjacent blades, and wherein adjacent damping elements in a Rotation of the rotor about a rotor axis by a radially acting centrifugal force in contact.
  • damping elements generally loose body which rest in the idle state first between the blade roots of the blades on the rotor or on corresponding support structures and are pressed during operation of the rotor due to acting in the radial direction centrifugal force against the underside of the blade platforms of adjacent blades.
  • Each damping element is at the same time in contact with both adjacent blade platforms. Thereby, the kinetic energy of a caused relative to vibration relative movement between the blades can be converted into heat energy, due to the friction between the respective blade platforms and the adjacent damping element.
  • the invention has for its object to provide a blade assembly with damping elements, with the unwanted vibrations can be attenuated more effectively.
  • the contact regions of adjacent damping elements that form when the rotor rotates are designed in the form of a planar contact.
  • the entire provided friction surface between the damping elements is significantly increased compared to known blade arrangements, in which the damping elements only come into contact with each other in the form of a line contact.
  • Friction surface causes a very effective vibration damping of the entire blade assembly. Also different vibration modes can be effectively damped.
  • the blade arrangement according to the invention enables a reduction of the vibration amplitudes and stresses by additional friction damping.
  • the damping elements differ in their geometric shape. According to the invention, oscillation modes can thus be effectively damped with suitably shaped damping elements, which can not be effectively damped with a constant design of all damping elements.
  • the damping elements can also differ in their masses to effectively damp by combining with suitable geometric shapes as large a number of different vibration modes.
  • the friction conditions coefficient of friction, roughness
  • the contact areas can be influenced, in order to enable targeted damping of several modes, even in increased frequency ranges.
  • damping elements are preferably rod-shaped.
  • damping elements in the circumferential direction of the rotor are arranged one behind the other, wherein the damping elements are preferably rod-shaped and a damping element has a cross section of the shape of a wedge and the other damping element has a cross section of the shape of a quarter circle.
  • This combination of two differently acting damping elements can effectively attenuate a multiplicity of different vibration states, with the in-phase vibration states as well as the in-phase vibrations being damped, since the surface contacts of the wedge-shaped one Damping element rolling of the circular element is prevented at the line contact to the plate shape.
  • damping elements By combining these damping elements with a surface contact on a blade platform and a line contact (Hertzian contact) on the other platform of the blade pair a kinematic stable arrangement is provided which prevents tilting and local lifting of all contact surfaces.
  • three damping elements are arranged one behind the other in the circumferential direction of the rotor.
  • a further damping element which preferably has a different geometric shape than the other damping elements, optionally further disturbing vibration modes can be effectively damped.
  • the two outer damping elements arranged one after the other in the circumferential direction of the rotor come into contact with the blades of the pair of vanes via friction surfaces which are formed on the vanes of the pair of vanes.
  • the damping elements made of steel or ceramic, ie materials with which an effective damping can be realized.
  • the invention further relates to a method for vibration damping of a blade assembly comprising a rotor and a plurality of blades arranged on the circumference of the rotor, in which a plurality of damping elements are arranged in the circumferential direction of the rotor one behind the other between the blades of at least one blade pair, which is formed of two adjacent blades , and wherein adjacent damper elements in a rotation of the rotor about a rotor axis by a radially acting centrifugal force in contact, and are used in the damping elements, which are formed so in the circumferential direction of the rotor can be arranged one behind the other, that the contact is a surface contact.
  • FIG. 1 shows a schematic section of the blade arrangement 1 according to the invention in a sectional plane perpendicular to the rotor axis.
  • the detail shows two blade platforms 3 of adjacent blades of the blade arrangement 1 according to the invention.
  • the blades are suspended from the rotor disk of the blade arrangement 1 and are at a small distance from one another.
  • two damping elements 5 and 7 are arranged loosely. Both damping elements 5, 7 form a damper group and are rod-shaped in the axial direction, wherein the damping element 7 has a quarter-circle-shaped cross-section and the damping element 5 has a wedge-shaped cross section.
  • the undersides of the two blade platforms 3 form friction surfaces 9, 11. against these friction surfaces 9, 11, the two damping elements 5, 7 are pressed during a rotation of the rotor (not shown) by the action of centrifugal force.
  • the friction surfaces 9, 11 are here inclined at certain angles ⁇ and ⁇ to the plane which is spanned by the radial direction R and the rotor axis, so that they together form a V-shaped guide, in which the damping elements 5, 7 through the centrifugal be pressed.
  • the wedge-shaped damping element 5 has a friction surface 13 whose inclination is adapted to the angle ⁇ in order to provide an effective areal frictional contact between the damping element 5 and the corresponding blade platform 3.
  • the angles ⁇ and ⁇ are preferably in the range of 20 ° to 70 °, the range of 40 ° to 60 ° being more preferred.
  • the damping elements 5 and 7 are formed and arranged in the circumferential direction of the rotor one behind the other, that the contact in the contact region 15 is a flat contact 15, as well as the contact between the damping element 5 and platform 3.
  • the entire provided friction surface between the Damping elements 5 and 7 compared to known blade assemblies significantly increased, in which the contact area between the damping elements is not formed as a flat contact, but in the form of a line contact (Hertzian contact).
  • the friction surface additionally provided according to the invention via the flat contact 15 effects a very effective vibration damping of the entire blade arrangement 1.
  • the flat contact 15 extends parallel to the radial direction R, but can also be inclined by correspondingly selected angles ⁇ and ⁇ to the radial direction R.
  • the angle ⁇ is within a range of 70 ° to 90 ° and the angle ⁇ within a range of 110 ° to 90 ° or vice versa.
  • Fig. 2 shows schematically the arrangement of two damping element groups 25, 27.
  • the positions of the damping element groups 25 and 27, each comprising a certain number of damping elements are indicated schematically by circles.
  • the damping elements extend rod-shaped in the axial direction, wherein the groups along the axial extent of a blade 17 (axial direction 23) 'are distributed.
  • the blade 17 comprises an airfoil 19, a blade platform 3, a blade root 21, a blade leading edge 29 and a blade trailing edge 31.
  • the damping element group 27 is located on the blade leading edge 29 and the damping element group 25 on the blade trailing edge 31.
  • the flow direction 33 is indicated by an arrow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Power Steering Mechanism (AREA)
  • Processing Of Stones Or Stones Resemblance Materials (AREA)
  • Fluid-Damping Devices (AREA)
EP06024326A 2006-11-23 2006-11-23 Agencement d'aubes Withdrawn EP1925781A1 (fr)

Priority Applications (10)

Application Number Priority Date Filing Date Title
EP06024326A EP1925781A1 (fr) 2006-11-23 2006-11-23 Agencement d'aubes
PCT/EP2007/061469 WO2008061856A1 (fr) 2006-11-23 2007-10-25 Ensemble d'aubes
AT07821832T ATE469288T1 (de) 2006-11-23 2007-10-25 Schaufelanordnung
CN2007800436875A CN101542073B (zh) 2006-11-23 2007-10-25 叶片装置
ES07821832T ES2345686T3 (es) 2006-11-23 2007-10-25 Disposicion de paletas.
EP07821832A EP2094946B1 (fr) 2006-11-23 2007-10-25 Ensemble d'aubes
RU2009123844/06A RU2417323C2 (ru) 2006-11-23 2007-10-25 Система лопаток
US12/515,845 US8167563B2 (en) 2006-11-23 2007-10-25 Blade arrangement
JP2009537583A JP4806075B2 (ja) 2006-11-23 2007-10-25 翼配置構造
DE502007003972T DE502007003972D1 (de) 2006-11-23 2007-10-25 Schaufelanordnung

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP06024326A EP1925781A1 (fr) 2006-11-23 2006-11-23 Agencement d'aubes

Publications (1)

Publication Number Publication Date
EP1925781A1 true EP1925781A1 (fr) 2008-05-28

Family

ID=37888032

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06024326A Withdrawn EP1925781A1 (fr) 2006-11-23 2006-11-23 Agencement d'aubes
EP07821832A Not-in-force EP2094946B1 (fr) 2006-11-23 2007-10-25 Ensemble d'aubes

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP07821832A Not-in-force EP2094946B1 (fr) 2006-11-23 2007-10-25 Ensemble d'aubes

Country Status (9)

Country Link
US (1) US8167563B2 (fr)
EP (2) EP1925781A1 (fr)
JP (1) JP4806075B2 (fr)
CN (1) CN101542073B (fr)
AT (1) ATE469288T1 (fr)
DE (1) DE502007003972D1 (fr)
ES (1) ES2345686T3 (fr)
RU (1) RU2417323C2 (fr)
WO (1) WO2008061856A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2418356A1 (fr) 2010-08-10 2012-02-15 Siemens Aktiengesellschaft Amortisseur pour une turbine et aube de turbine correspondante
EP3078808A1 (fr) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Rangée d'aubes pour une turbomachine
CN113803115A (zh) * 2020-06-16 2021-12-17 中国航发商用航空发动机有限责任公司 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2434098A1 (fr) 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Agencement d'aubes et turbine à gaz associée
US9194238B2 (en) * 2012-11-28 2015-11-24 General Electric Company System for damping vibrations in a turbine
CN104594957B (zh) * 2014-12-08 2016-06-15 东方电气集团东方汽轮机有限公司 汽轮机调节级动叶片的阻尼结构
US10472975B2 (en) * 2015-09-03 2019-11-12 General Electric Company Damper pin having elongated bodies for damping adjacent turbine blades
US10662784B2 (en) * 2016-11-28 2020-05-26 Raytheon Technologies Corporation Damper with varying thickness for a blade
US10677073B2 (en) 2017-01-03 2020-06-09 Raytheon Technologies Corporation Blade platform with damper restraint
US10731479B2 (en) 2017-01-03 2020-08-04 Raytheon Technologies Corporation Blade platform with damper restraint
JP7039355B2 (ja) * 2018-03-28 2022-03-22 三菱重工業株式会社 回転機械
US11828191B2 (en) * 2019-05-29 2023-11-28 Safran Aircraft Engines Assembly for turbomachine
US11391157B1 (en) 2021-03-23 2022-07-19 Pratt & Whitney Canada Corp. Damped rotor assembly
US11525464B2 (en) 2021-03-23 2022-12-13 Pratt & Whitney Canada Corp. Rotor with centrifugally wedged damper
JP2023093088A (ja) * 2021-12-22 2023-07-04 三菱重工業株式会社 回転機械

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
SU1127979A1 (ru) * 1983-02-23 1984-12-07 Предприятие П/Я Р-6837 Рабочее колесо турбомашины
EP0918139A2 (fr) * 1997-11-25 1999-05-26 ROLLS-ROYCE plc Amortisseur à friction
EP1154125A2 (fr) * 2000-05-08 2001-11-14 ALSTOM Power N.V. Aubage avec des éléments amortisseurs

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
SU128868A1 (ru) 1959-04-20 1959-11-30 В.С. Осадченко Демпфер сухого трени дл изменени собственной частоты колебаний бандажированных рабочих лопаток турбин
US4580946A (en) * 1984-11-26 1986-04-08 General Electric Company Fan blade platform seal
GB2223277B (en) * 1988-09-30 1992-08-12 Rolls Royce Plc Aerofoil blade damping
FR2665726B1 (fr) * 1990-08-08 1993-07-02 Snecma Soufflante de turbomachine a amortisseur dynamique a cames.
US5156528A (en) 1991-04-19 1992-10-20 General Electric Company Vibration damping of gas turbine engine buckets
FR2716502B1 (fr) * 1994-02-23 1996-04-05 Snecma Garniture d'étanchéité entre des aubes et des plates-formes intermédiaires.
JP2006125372A (ja) 2004-11-01 2006-05-18 Mitsubishi Heavy Ind Ltd 回転機械翼の防振構造および回転機械

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2942843A (en) * 1956-06-15 1960-06-28 Westinghouse Electric Corp Blade vibration damping structure
SU1127979A1 (ru) * 1983-02-23 1984-12-07 Предприятие П/Я Р-6837 Рабочее колесо турбомашины
EP0918139A2 (fr) * 1997-11-25 1999-05-26 ROLLS-ROYCE plc Amortisseur à friction
EP1154125A2 (fr) * 2000-05-08 2001-11-14 ALSTOM Power N.V. Aubage avec des éléments amortisseurs

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2418356A1 (fr) 2010-08-10 2012-02-15 Siemens Aktiengesellschaft Amortisseur pour une turbine et aube de turbine correspondante
EP3078808A1 (fr) * 2015-04-07 2016-10-12 Siemens Aktiengesellschaft Rangée d'aubes pour une turbomachine
CN113803115A (zh) * 2020-06-16 2021-12-17 中国航发商用航空发动机有限责任公司 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机
CN113803115B (zh) * 2020-06-16 2024-04-05 中国航发商用航空发动机有限责任公司 涡轮叶片缘板阻尼器、涡轮叶片和航空发动机

Also Published As

Publication number Publication date
US8167563B2 (en) 2012-05-01
EP2094946B1 (fr) 2010-05-26
ATE469288T1 (de) 2010-06-15
CN101542073A (zh) 2009-09-23
RU2009123844A (ru) 2010-12-27
EP2094946A1 (fr) 2009-09-02
JP4806075B2 (ja) 2011-11-02
US20100021302A1 (en) 2010-01-28
RU2417323C2 (ru) 2011-04-27
CN101542073B (zh) 2013-02-13
DE502007003972D1 (de) 2010-07-08
JP2010510436A (ja) 2010-04-02
WO2008061856A1 (fr) 2008-05-29
ES2345686T3 (es) 2010-09-29

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