EP0918139A2 - Reibungsdämpfer - Google Patents

Reibungsdämpfer Download PDF

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Publication number
EP0918139A2
EP0918139A2 EP98309280A EP98309280A EP0918139A2 EP 0918139 A2 EP0918139 A2 EP 0918139A2 EP 98309280 A EP98309280 A EP 98309280A EP 98309280 A EP98309280 A EP 98309280A EP 0918139 A2 EP0918139 A2 EP 0918139A2
Authority
EP
European Patent Office
Prior art keywords
damper
friction
friction surface
blades
blade
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Withdrawn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
EP98309280A
Other languages
English (en)
French (fr)
Other versions
EP0918139A3 (de
Inventor
Kenan Yuce Sanliturk
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP0918139A2 publication Critical patent/EP0918139A2/de
Publication of EP0918139A3 publication Critical patent/EP0918139A3/de
Withdrawn legal-status Critical Current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
    • F01D5/26—Antivibration means not restricted to blade form or construction or to blade-to-blade connections or to the use of particular materials

Definitions

  • the invention relates to a blade to blade friction damper particularly but not exclusively for a gas turbine engine.
  • Gas turbine engines typically include a plurality of blades mounted around the periphery of a rotor disc.
  • Each blade includes an aerofoil which projects into a working fluid flowing axially through the turbine. The flow of the fluid across the aerofoils causes the blades to rotate in the circumferential direction, thus rotating the rotor disc.
  • the blades are closely spaced around the circumference of the rotor disc and include inner root sections mounted on the disc in such a way that expansion or contraction of the materials due to changes in temperature can be accommodated. This may be by use of a dovetailed joint and slot arrangement as described in US 5478207.
  • dampers known as friction dampers, under platform dampers or cottage roof dampers, between adjacent turbine blades.
  • the dampers are positioned such that during operation of the turbine, centrifugal forces draw inclined friction faces of the dampers into contact with complementary inclined faces on platforms associated with the blades.
  • the platforms are located on and extend circumferentially from the blades, between their aerofoil and root sections. Vibration of the blades causes relative movement of the friction faces of the dampers and the faces of the blade platforms, causing these faces to slide against one another.
  • the work done in overcoming the associated frictional forces dissipates the vibrational energy and thus reduces resonant response levels and suppresses excess vibration of the turbine blades.
  • a commonly used prior art vibration damper design is essentially wedge shaped with friction faces angled at approximately 45° to the radial direction of the blades and 90° to one another. The faces bear against angled faces of the blade platforms, faces of adjacent blade platforms forming a recess of approximately inverted V shape.
  • Such wedge shape designs suffer from the drawback that they do not always achieve an exact fit in the inverted V shaped recess formed by the platforms of adjacent blades. This can result in one or both pairs of faces being in poor contact and in the damping action being correspondingly reduced.
  • EP 509838 discloses a wedge shaped damper having raised pad surfaces on the two faces of the damper normally in surface to surface contact with the inclined faces of the turbine blade platforms.
  • the raised surfaces are located so as to reduce tilting of the dampers and keep the raised surfaces in sliding contact with the platform faces.
  • US 5478207 discloses a damper which is generally wedge shaped but which has an off-set centre of gravity, intended to improve stability of the damper and to maintain planar contact between damper faces and the platform faces of the blades.
  • a blade to blade vibration damper for a gas turbine engine, the damper including a first friction surface for contacting a first face associated with a blade of the turbine and a second friction surface for contacting a second face associated with an adjacent blade of the turbine; wherein the damper is formed in at least two parts such that the first friction surface can move relative to the second friction surface.
  • the parts may undergo relative movement in the radial direction of the blades.
  • the parts of the damper engage a further friction surface.
  • This further friction surface may be on another part of the damper.
  • the damper includes a friction interface between two parts, the interface extending substantially in the radial direction of the blades.
  • the damper is substantially wedge shaped.
  • the first friction surface is disposed at an angle of approximately 90° to the second friction surface.
  • the first and second friction surfaces are located in use at an angle of approximately 45° to the radial direction of the blades.
  • the first and second faces are preferably formed on platforms extending tangentially from the blades of the turbine.
  • a gas turbine engine including a vibration damper as previously defined.
  • a turbine section of a gas turbine engine includes a plurality of turbine blades 10 mounted on a rotatable disc 12.
  • Each turbine blade 10 includes an aerofoil 14 which projects into a working fluid flowing axially through the turbine. The flow of the fluid across the aerofoils causes the blades 14 to rotate in the circumferential direction, thus rotating the disc 12.
  • the blades 10 are mounted on the disc 12 by means of dovetailed root portions 16 which fit into correspondingly shaped dovetailed recesses 18 in the rotatable disc 12. These mountings are able to accommodate small changes in the material dimensions due to thermal expansion and contraction.
  • each blade 10 Located between the aerofoil 14 and root portion 16 of each blade 10 is a platform 20 having angled faces 22 on its radially inner side.
  • the angled faces 22 of two adjacent blades form an inverted V shape which defines the upper boundary of the damper cavity 24.
  • Each damper cavity 24 houses an approximately wedge shaped friction damper 26 having angled friction surfaces 28 of complementary shape to the inverted V formed by the angled faces 22.
  • the friction damper 26 shown in Fig. 1 is of conventional "cottage roof" design.
  • This basic damper design is effective in reducing certain modes of vibration. For example, if circumferential vibrations are set up, whereby the circumferential distance between adjacent blade platforms 20 varies as the blades vibrate, the centrifugal forces acting on the damper 26 cause it to move radially inwards and outwards as the blades 10 vibrate, the friction surfaces 28 generally remaining in contact with the angled faces 22.
  • conventional dampers are not very effective. They may roll, as illustrated in Fig. 3, rather than slide or one side may stick while contact separation occurs momentarily on the other side, as illustrated in Fig. 4, or a combination of both may occur, particularly when the blade vibration results in platform motion having a radial component.
  • Fig. 5 shows a damper 30 according to the invention, subjected to radial platform motion.
  • the damper 30 is split down its centre to provide an extra central friction interface 32.
  • centrifugal forces cause the two halves of the friction damper to slide relative to one another as illustrated in Fig. 5.
  • rolling movement is prevented, and the friction surfaces 28 are maintained in contact with the faces 22.
  • FIG. 6 An alternative damper 34 according to the invention is illustrated in Fig. 6.
  • This damper has grooves 36 located approximately in the central region of its friction surfaces. Such grooves help to prevent rolling encouraged by unpredictable distribution of contact areas if the mating surfaces are not exactly flat. There is no contact in the grooved region and therefore the areas of contact are defined more precisely than in the first embodiment of the invention.
  • the friction faces 22 and the friction surfaces 28 of the damper 30,34 may be angled at any suitable angle to the radial direction of the blades 10, not just at approximately 45° as is typically the case.
  • the friction surfaces 28 of the damper 30,34 accordingly may also not necessarily be at 90° to one another.
  • the angle of the respective friction surfaces 28 and friction faces 22 to the radial direction of the blades 10 may also be different for the respective surfaces 28 of a single damper 30,34 and respective faces 22.
  • the splitting may be asymmetric, and the damper may be split into more than two pieces. The two or more pieces of the damper 34 may therefore be non-identical and/or non symmetric.
  • the splitting effect can be extended in other directions, for example along the damper longitudinal axis, and the friction interfaces formed by the splitting may be inclined relative to the radial direction.
  • the contact and non-contact surfaces of the damper need not be flat.
  • the contact and non contact surfaces and faces could be curved whilst still allowing sliding of the respective surfaces, faces and parts of the damper 30,34.
  • grooves are provided on the damper friction surfaces, more than one groove may be provided, and the grooves may be provided in any location, including on the friction interfaces formed by the splitting.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Vibration Prevention Devices (AREA)
EP98309280A 1997-11-25 1998-11-12 Reibungsdämpfer Withdrawn EP0918139A3 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9724731 1997-11-25
GBGB9724731.6A GB9724731D0 (en) 1997-11-25 1997-11-25 Friction damper

Publications (2)

Publication Number Publication Date
EP0918139A2 true EP0918139A2 (de) 1999-05-26
EP0918139A3 EP0918139A3 (de) 2000-07-26

Family

ID=10822505

Family Applications (1)

Application Number Title Priority Date Filing Date
EP98309280A Withdrawn EP0918139A3 (de) 1997-11-25 1998-11-12 Reibungsdämpfer

Country Status (2)

Country Link
EP (1) EP0918139A3 (de)
GB (1) GB9724731D0 (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1249576A2 (de) * 2001-04-10 2002-10-16 Rolls-Royce Plc Schwingungsdämpfer für Gasturbinen
EP1154125A3 (de) * 2000-05-08 2003-10-29 ALSTOM (Switzerland) Ltd Schaufelanordnung mit Dämpfungselementen
EP1452694A2 (de) * 2003-02-26 2004-09-01 ROLLS-ROYCE plc Dämpfungs- und Dichtungselement für Turbine
JP2004257391A (ja) * 2003-02-27 2004-09-16 General Electric Co <Ge> タービンバケットダンパーピン
EP1818506A1 (de) 2006-02-08 2007-08-15 Siemens Aktiengesellschaft HCF-Beanspruchungsreduktion in Tannenfüssen
EP1925781A1 (de) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Schaufelanordnung
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
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

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0509838A1 (de) 1991-04-19 1992-10-21 General Electric Company Vibrationsdämpfung von Gasturbinenschaufeln
US5478207A (en) 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine

Family Cites Families (6)

* 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
FR1263677A (fr) * 1960-07-29 1961-06-09 Havilland Engine Co Ltd Dispositif antivibratoire applicable à des organes rotatifs
US3181835A (en) * 1964-01-07 1965-05-04 Carroll C Davis Blade vibration damping device
US4480957A (en) * 1983-04-14 1984-11-06 General Electric Company Dynamic response modification and stress reduction in dovetail and blade assembly
FR2665726B1 (fr) * 1990-08-08 1993-07-02 Snecma Soufflante de turbomachine a amortisseur dynamique a cames.
FR2739135B1 (fr) * 1995-09-21 1997-10-31 Snecma Agencement amortisseur monte entre des aubes de rotor

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0509838A1 (de) 1991-04-19 1992-10-21 General Electric Company Vibrationsdämpfung von Gasturbinenschaufeln
US5478207A (en) 1994-09-19 1995-12-26 General Electric Company Stable blade vibration damper for gas turbine engine

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1154125A3 (de) * 2000-05-08 2003-10-29 ALSTOM (Switzerland) Ltd Schaufelanordnung mit Dämpfungselementen
EP1249576A2 (de) * 2001-04-10 2002-10-16 Rolls-Royce Plc Schwingungsdämpfer für Gasturbinen
EP1249576A3 (de) * 2001-04-10 2003-10-08 Rolls-Royce Plc Schwingungsdämpfer für Gasturbinen
EP1452694A2 (de) * 2003-02-26 2004-09-01 ROLLS-ROYCE plc Dämpfungs- und Dichtungselement für Turbine
EP1452694A3 (de) * 2003-02-26 2007-01-03 ROLLS-ROYCE plc Dämpfungs- und Dichtungselement für Turbine
JP2004257391A (ja) * 2003-02-27 2004-09-16 General Electric Co <Ge> タービンバケットダンパーピン
EP1818506A1 (de) 2006-02-08 2007-08-15 Siemens Aktiengesellschaft HCF-Beanspruchungsreduktion in Tannenfüssen
WO2008061856A1 (de) * 2006-11-23 2008-05-29 Siemens Aktiengesellschaft Schaufelanordnung
EP1925781A1 (de) * 2006-11-23 2008-05-28 Siemens Aktiengesellschaft Schaufelanordnung
CN101542073A (zh) * 2006-11-23 2009-09-23 西门子公司 叶片装置
JP2010510436A (ja) * 2006-11-23 2010-04-02 シーメンス アクチエンゲゼルシヤフト 翼配置構造
US8167563B2 (en) 2006-11-23 2012-05-01 Siemens Aktiengesellschaft Blade arrangement
CN101542073B (zh) * 2006-11-23 2013-02-13 西门子公司 叶片装置
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same
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
GB9724731D0 (en) 1998-01-21
EP0918139A3 (de) 2000-07-26

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