EP0918139A2 - Amortisseur à friction - Google Patents
Amortisseur à friction Download PDFInfo
- 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- Withdrawn
Links
Images
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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB9724731.6A GB9724731D0 (en) | 1997-11-25 | 1997-11-25 | Friction damper |
GB9724731 | 1997-11-25 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0918139A2 true EP0918139A2 (fr) | 1999-05-26 |
EP0918139A3 EP0918139A3 (fr) | 2000-07-26 |
Family
ID=10822505
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98309280A Withdrawn EP0918139A3 (fr) | 1997-11-25 | 1998-11-12 | Amortisseur à friction |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0918139A3 (fr) |
GB (1) | GB9724731D0 (fr) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1249576A2 (fr) * | 2001-04-10 | 2002-10-16 | Rolls-Royce Plc | Amortisseur de vibrations pour turbines à gaz |
EP1154125A3 (fr) * | 2000-05-08 | 2003-10-29 | ALSTOM (Switzerland) Ltd | Aubage avec des éléments amortisseurs |
EP1452694A2 (fr) * | 2003-02-26 | 2004-09-01 | ROLLS-ROYCE plc | Dispositif d'amortissement et d'étanchéité pour 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 (fr) | 2006-02-08 | 2007-08-15 | Siemens Aktiengesellschaft | Réduction de la fatigue répétitive dans un pied de sapin |
EP1925781A1 (fr) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Agencement d'aubes |
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)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0509838A1 (fr) | 1991-04-19 | 1992-10-21 | General Electric Company | Amortissement des vibrations des aubes de turbines à gaz |
US5478207A (en) | 1994-09-19 | 1995-12-26 | General Electric Company | Stable blade vibration damper for gas turbine engine |
Family Cites Families (6)
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 |
-
1997
- 1997-11-25 GB GBGB9724731.6A patent/GB9724731D0/en not_active Ceased
-
1998
- 1998-11-12 EP EP98309280A patent/EP0918139A3/fr not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0509838A1 (fr) | 1991-04-19 | 1992-10-21 | General Electric Company | Amortissement des vibrations des aubes de turbines à gaz |
US5478207A (en) | 1994-09-19 | 1995-12-26 | General Electric Company | Stable blade vibration damper for gas turbine engine |
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1154125A3 (fr) * | 2000-05-08 | 2003-10-29 | ALSTOM (Switzerland) Ltd | Aubage avec des éléments amortisseurs |
EP1249576A2 (fr) * | 2001-04-10 | 2002-10-16 | Rolls-Royce Plc | Amortisseur de vibrations pour turbines à gaz |
EP1249576A3 (fr) * | 2001-04-10 | 2003-10-08 | Rolls-Royce Plc | Amortisseur de vibrations pour turbines à gaz |
EP1452694A2 (fr) * | 2003-02-26 | 2004-09-01 | ROLLS-ROYCE plc | Dispositif d'amortissement et d'étanchéité pour turbine |
EP1452694A3 (fr) * | 2003-02-26 | 2007-01-03 | ROLLS-ROYCE plc | Dispositif d'amortissement et d'étanchéité pour 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 (fr) | 2006-02-08 | 2007-08-15 | Siemens Aktiengesellschaft | Réduction de la fatigue répétitive dans un pied de sapin |
WO2008061856A1 (fr) * | 2006-11-23 | 2008-05-29 | Siemens Aktiengesellschaft | Ensemble d'aubes |
EP1925781A1 (fr) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Agencement d'aubes |
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 |
---|---|
EP0918139A3 (fr) | 2000-07-26 |
GB9724731D0 (en) | 1998-01-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1249576B1 (fr) | Amortisseur de vibrations pour turbines à gaz | |
EP1867836B1 (fr) | Système d'amortissement de vibration d'aube amélioré | |
EP1867837B1 (fr) | Système d'amortissement pour aubes de turbine | |
US5156528A (en) | Vibration damping of gas turbine engine buckets | |
EP1564375B1 (fr) | Aube de rotor refroidie avec un dispositif d'amortissement des vibrations | |
US8231352B2 (en) | Vibration damper assembly | |
US9309782B2 (en) | Flat bottom damper pin for turbine blades | |
US10287898B2 (en) | Blade root, corresponding blade, rotor disc, and turbomachine assembly | |
US5368444A (en) | Anti-fretting blade retention means | |
US6916021B2 (en) | Sealing arrangement | |
EP0297120B1 (fr) | Joint d'etancheite inter-aubes pour rotor de turbomachine | |
US20010024614A1 (en) | Blade assembly with damping elements | |
JP2004340144A (ja) | タービンのバケット用振動ダンパ組立体 | |
US6302651B1 (en) | Blade attachment configuration | |
US5593282A (en) | Turbomachine rotor construction including a serrated root section and a rounded terminal portion on a blade root, especially for an axial-flow turbine of a gas turbine engine | |
JPH08100603A (ja) | ターボ機械の羽根を備えた回転子 | |
JPH04224202A (ja) | ガスタービンエンジン・ブレード | |
CN102947548A (zh) | 用于转子叶片的轻量围带翼片 | |
EP0777819B1 (fr) | Joint rotatif | |
EP0821133B1 (fr) | Fixation des aubes de soufflante pour un turboréacteur | |
EP0918139A2 (fr) | Amortisseur à friction | |
EP3138999B1 (fr) | Goupille amortissante pour amortir des aubes de turbine adjacentes et moteur à turbine | |
JP6214677B2 (ja) | ターボ機械ロータブレード、ターボ機械ロータディスク、ターボ機械ロータ、複数のルートおよびスロット接触面角を有するガスタービンエンジン | |
Armentrout et al. | Rotordynamic characteristics of flexure-pivot tilting-pad journal bearings | |
EP0971096B1 (fr) | Fixation d'une aube à un rotor |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): DE ES FR GB IT |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
AKX | Designation fees paid |
Free format text: DE ES FR GB IT |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20010129 |