EP0284829A1 - Rotorbeschaufelung für Dampfturbinen - Google Patents
Rotorbeschaufelung für Dampfturbinen Download PDFInfo
- Publication number
- EP0284829A1 EP0284829A1 EP88103498A EP88103498A EP0284829A1 EP 0284829 A1 EP0284829 A1 EP 0284829A1 EP 88103498 A EP88103498 A EP 88103498A EP 88103498 A EP88103498 A EP 88103498A EP 0284829 A1 EP0284829 A1 EP 0284829A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- caps
- blades
- blade
- grooves
- contacts
- 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.)
- Granted
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
- F01D5/22—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
- 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
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
Definitions
- the present invention relates to a mobile blade for steam turbines comprising blades with bodies provided with caps or fins, said caps or fins of adjacent blades being in contact at least during the rotation of the blade on a surface. plane substantially parallel to the radial axis of the blade and causing by these contacts a torsion of the body of the blades.
- the mobile blading making it possible to remedy this drawback is characterized in that it comprises a connection in addition to the contacts between adjacent caps or ailerons, said connection being produced by means of additional contacts having a freedom of rectilinear sliding in a plane. corresponding to that of each cap or fin along an axis substantially perpendicular to the axis of rotation OO ⁇ of the blading, said additional contacts being located at a relatively large distance from the contacts causing the torsion.
- connection created between neighboring caps (or fins) by these additional contacts has the effect that the relative movement of these caps (or fins) generates on each of them at points A and A ⁇ (distinct or combined) friction forces f and f ⁇ contained in the plane of the caps (or fins) which have a moment ⁇ M Z relative to the mean contact point C on the planar surface.
- the sum M Z + ⁇ M Z can differ from one blade to another so that even in the extreme case where the faces tightened by the twist are unable to transmit the slightest moment between neighboring caps (or fins), this transmission is ensured by ⁇ M Z (see figure n ° 3). It is important that the points A and A ⁇ are located at the greatest possible distance from the contact faces so as to better block any rotational movement of the cap (or of the fin) which would appear around a point of point contact vs.
- the additional contacts are made by extensions of the caps (or fins), the upper faces of which are applied to the upper faces of complementary cavities provided in the adjacent caps (or fins).
- the additional contacts are made by members located in grooves opening onto the lateral surface of the caps or fins opposite the contacts causing the torsion and rubbing against the walls of these grooves.
- the known blade represented in FIGS. 1, 2 and 3 comprises blades 1 comprising a foot 2 a body 3 and a cap 4.
- the feet 2 of the blades 1 are blocked in a central means 5 forming part of the rotor of the turbine by the 'intermediate of keys 6.
- Each cap 4 has a front face 7 inclined relative to the vertical median plane P and substantially parallel to the radial axis (z ⁇ z) of the blade and a rear face 8 substantially parallel to the front face 7, front and rear 7 and 8 of all the blades being located on the same side of the median plane P.
- the blading is movable in rotation about the axis OO ⁇ .
- each blade 1 When the feet 2 of the blades 1 are put in place, the front face 7 of each blade 1 comes to bear against the rear face 8 of the blade 1 located in front and the faces 7 and 8 rotate to approach the perpendicular in the middle plane. The body 3 of each blade 1 is then twisted under the effect of the forces that the adjacent blades 1 apply to its front and rear faces.
- FIGS. 2 and 3 blades have been shown, the caps of which are applied against each other under the effect of the torsional forces at rest of the bodies of the blades, but it is also known to mount the caps apart, the caps do not being applied against each other only during the rotation of the vanes whose bodies twist under the effect of centrifugal force.
- FIGS. 4 and 5 An embodiment of the blading according to the invention is shown in FIGS. 4 and 5.
- the cap 4 of each blade is provided with an extension 9 of parallelepiped shape, the upper face of which 10 rubs on the upper face 11 of a complementary cavity 12 formed in the adjacent blade.
- the extension 9 and the cavity 12 are located on the lateral surface 13 of the caps 4 situated on the side opposite to the faces 7 and 8 in contact, relative to the plane P.
- the contact between the face of the extension 9 and that of the cavity 12 can be obtained by prestressing at rest and / or deformation due to centrifugal forces.
- the caps 4 are provided with a machined groove 14 opening onto the lateral surface 13 of the caps 14 opposite the contacting faces 7, 8.
- the grooves 14 of the adjacent blades 1 are not in the extension of one another.
- each shim 15 being fitted into two consecutive caps 4.
- the wedges are spaced from each other and their ends come approximately towards the middle of the lateral surface 13 of the caps.
- the groove 14 is provided with a peripheral tooth 16 at its upper part which prevents the wedges 15 from coming out during the rotation of the blading.
- This tooth 16 has been folded down after the shims 15 have been placed in the grooves 14.
- the caps 4 have grooves 14 which are in line with one another when the blading is not driven in rotation.
- the bodies 3 of the vanes 2 tend to bend (see FIG. 11) in the absence of the presence of connecting members in the grooves 14.
- a wedging element constituted for example by a flat wire 17 which opposes the bending of the blades 1 under the effect of centrifugal force and develops frictional forces.
- This wire can consist of four quarters of circumference.
- the groove 14 opens onto the lateral surface 13 of the caps 4 on the side opposite to the contacting surfaces 7 and 8 and it can be provided with a flange 16 preventing the wedging wire 17 from coming out of the groove 14 during the rotation of the blading (see figure 14).
- the grooves 14 are in the extension of each other at rest and they remain when the blade is rotated.
- a connecting element such as a flat wire 18 is introduced into the groove.
- This wire 18 is provided with protrusions 19 arranged towards the middle of the grooves 14 which rub against the upper wall of these grooves 14 when the blade is in rotation.
- the groove 14 is located as in the second embodiment on the lateral surface 13 of the caps 14 on the side opposite to the contacting surfaces 7 and 8 and it can be provided with a flange 16 preventing the wedging wire 18 from coming out of the groove 14 .
- a rod-shaped member 20 has been introduced into the groove 14 opening onto the lateral surface 13 of the caps 4 opposite the faces 7 and 8, the grooves at rest being as in figure 10.
- Each member 20 has at one end an axis 21 parallel to the axis of rotation OO ⁇ of the blading which is housed without sliding in a hollow hollow 22 in the walls of the groove 14.
- the axis 21 of the member 20 is connected by an arm 23 to a cubic mass 24 located in the groove of the cap 4 close to that in which the axis 21 is housed.
- the axis 21 of the member 20 can be oriented and a frictional force occurs between the mass 24 and the wall of the groove 14.
- the groove 14 is provided with a peripheral tooth 16 which prevents the members 20 from leaving the groove 14.
- rod-shaped members 25 with two supports 26 are introduced into the grooves 14 opening onto the lateral surfaces 13 of the caps 4 opposite the surfaces 7 and 8, the grooves 14 at rest being as in FIG. 10.
- the bars 25 are astride the grooves 14 of two adjacent caps 4 with a support 26 in each of the grooves 14.
- the bars 26 are stopped tangentially by a stud 27 and axially by a tooth 16.
- the stud 27 is housed with clearance in a housing 28 in the groove 14.
- the bodies 3 of the blades were terminated with caps but they could instead be fitted with fins 4 situated at an intermediate height.
- FIG. 20 and 21 shows a partial view of a vane provided with fins 4 mounted on their bodies 3 tight against each other by their contact face 7, 8 and having a groove 14 opening onto the lateral surface 13 of the fins 4 opposite the side faces 7 and 8.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Organic Low-Molecular-Weight Compounds And Preparation Thereof (AREA)
- Production Of Liquid Hydrocarbon Mixture For Refining Petroleum (AREA)
- Toys (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Control Of Turbines (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT88103498T ATE70891T1 (de) | 1987-03-12 | 1988-03-07 | Rotorbeschaufelung fuer dampfturbinen. |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8703390 | 1987-03-12 | ||
FR8703390A FR2612249B1 (fr) | 1987-03-12 | 1987-03-12 | Aubage mobile pour turbines a vapeur |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0284829A1 true EP0284829A1 (de) | 1988-10-05 |
EP0284829B1 EP0284829B1 (de) | 1991-12-27 |
Family
ID=9348893
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP88103498A Expired - Lifetime EP0284829B1 (de) | 1987-03-12 | 1988-03-07 | Rotorbeschaufelung für Dampfturbinen |
Country Status (15)
Country | Link |
---|---|
US (1) | US4840539A (de) |
EP (1) | EP0284829B1 (de) |
JP (1) | JPS63246402A (de) |
KR (1) | KR960004207B1 (de) |
CN (1) | CN88101214A (de) |
AT (1) | ATE70891T1 (de) |
AU (1) | AU1273088A (de) |
BR (1) | BR8801122A (de) |
CA (1) | CA1279826C (de) |
DE (1) | DE3867102D1 (de) |
ES (1) | ES2028154T3 (de) |
FR (1) | FR2612249B1 (de) |
GR (1) | GR3003829T3 (de) |
MX (1) | MX167279B (de) |
ZA (1) | ZA881716B (de) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5730584A (en) * | 1996-05-09 | 1998-03-24 | Rolls-Royce Plc | Vibration damping |
FR2975123A1 (fr) * | 2011-05-13 | 2012-11-16 | Snecma Propulsion Solide | Rotor de turbomachine comprenant des aubes en materiau composite avec talon rapporte |
EP2612996A1 (de) * | 2012-01-04 | 2013-07-10 | General Electric Company | Vorrichtung und Verfahren zur Ausrichtung von Spitzendeckbänder |
WO2021176168A1 (fr) * | 2020-03-04 | 2021-09-10 | Safran Aircraft Engines | Procédé pour remboiter des talons d'aubes d'une roue de rotor dans une turbomachine d'aéronef |
WO2023247857A1 (fr) * | 2022-06-22 | 2023-12-28 | Safran Aircraft Engines | Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5201850A (en) * | 1991-02-15 | 1993-04-13 | General Electric Company | Rotor tip shroud damper including damper wires |
US5257908A (en) * | 1991-11-15 | 1993-11-02 | Ortolano Ralph J | Turbine lashing structure |
US5238366A (en) * | 1992-07-06 | 1993-08-24 | Westinghouse Electric Corp. | Method and apparatus for determining turbine blade deformation |
US5509784A (en) * | 1994-07-27 | 1996-04-23 | General Electric Co. | Turbine bucket and wheel assembly with integral bucket shroud |
JP3178327B2 (ja) * | 1996-01-31 | 2001-06-18 | 株式会社日立製作所 | 蒸気タービン |
US5645402A (en) * | 1996-04-10 | 1997-07-08 | Solar Turbines Incorporated | Turbine blade vibration dampening |
US6553665B2 (en) * | 2000-03-08 | 2003-04-29 | General Electric Company | Stator vane assembly for a turbine and method for forming the assembly |
US6439844B1 (en) * | 2000-12-11 | 2002-08-27 | General Electric Company | Turbine bucket cover and brush seal |
US6454534B1 (en) | 2000-12-21 | 2002-09-24 | General Electric Company | Flush bucket cover |
US6644924B1 (en) * | 2002-05-31 | 2003-11-11 | General Electric Company | Covers for turbine buckets and methods of assembly |
US6877956B2 (en) * | 2002-12-23 | 2005-04-12 | General Electric Company | Methods and apparatus for integral radial leakage seal |
US7063509B2 (en) * | 2003-09-05 | 2006-06-20 | General Electric Company | Conical tip shroud fillet for a turbine bucket |
US7001152B2 (en) * | 2003-10-09 | 2006-02-21 | Pratt & Wiley Canada Corp. | Shrouded turbine blades with locally increased contact faces |
DE102005030516A1 (de) * | 2005-06-28 | 2007-01-04 | Man Turbo Ag | Rotor für eine Turbine sowie Verfahren und Vorrichtung zur Herstellung des Rotors |
JP4765882B2 (ja) * | 2006-10-05 | 2011-09-07 | 株式会社日立製作所 | 蒸気タービン動翼 |
US8262359B2 (en) * | 2007-01-12 | 2012-09-11 | Alstom Technology Ltd. | Diaphragm for turbomachines and method of manufacture |
EP2213837A1 (de) * | 2009-01-29 | 2010-08-04 | Siemens Aktiengesellschaft | Turbinenschaufelsystem |
EP2218875A1 (de) * | 2009-02-17 | 2010-08-18 | Siemens Aktiengesellschaft | Schaufelverband einer Strömungsmaschine |
JP5426305B2 (ja) * | 2009-09-30 | 2014-02-26 | 株式会社東芝 | ターボ機械 |
FR2955608B1 (fr) * | 2010-01-26 | 2013-01-11 | Snecma | Amortisseur de vibrations a lamelle et chemises entre talons d'aubes adjacentes en materiau composite d'une roue mobile de turbomachine. |
FR2960021B1 (fr) * | 2010-05-12 | 2014-04-25 | Snecma | Roue mobile de turbomachine munie d'un jonc d'amortissement des vibrations |
US8888459B2 (en) * | 2011-08-23 | 2014-11-18 | General Electric Company | Coupled blade platforms and methods of sealing |
US9249669B2 (en) | 2012-04-05 | 2016-02-02 | General Electric Company | CMC blade with pressurized internal cavity for erosion control |
EP2669477B1 (de) * | 2012-05-31 | 2017-04-05 | General Electric Technology GmbH | Deckplatte für Schaufeln |
CN102825436B (zh) * | 2012-10-08 | 2015-04-22 | 南通中能机械制造有限公司 | 一种汽轮机小动叶片加工方法 |
JP5956365B2 (ja) * | 2013-02-28 | 2016-07-27 | 三菱日立パワーシステムズ株式会社 | タービン動翼列組立体、および蒸気タービン設備 |
FR3002970A1 (fr) * | 2013-03-07 | 2014-09-12 | Alstom Technology Ltd | Rotor de turbine pour une centrale thermoelectrique |
CN106425283A (zh) * | 2016-11-30 | 2017-02-22 | 哈尔滨理工大学 | 汽轮机转子旋转工作台 |
KR101874243B1 (ko) * | 2017-03-31 | 2018-07-03 | 두산중공업 주식회사 | 버킷의 진동감쇠구조와 이를 포함하는 버킷 및 터보머신 |
RU182453U1 (ru) * | 2017-12-01 | 2018-08-17 | Публичное Акционерное Общество "Одк-Сатурн" | Рабочее колесо турбины |
FR3137123A1 (fr) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Ensemble de turbomachine comprenant des aubes dont les plateformes sont espacées à froid et en contact lorsque la turbomachine est en service |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1544318A (en) * | 1923-09-12 | 1925-06-30 | Westinghouse Electric & Mfg Co | Turbine-blade lashing |
US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
FR1340331A (fr) * | 1962-09-07 | 1963-10-18 | Rateau Soc | Perfectionnements aux dispositifs de liaison des extrémités d'aubes mobiles de turbines |
FR1382057A (fr) * | 1962-07-11 | 1964-12-18 | Cem Comp Electro Mec | Perfectionnement aux ailetages de turbines à vapeur |
FR1403799A (fr) * | 1964-05-13 | 1965-06-25 | Rateau Soc | Roue de turbine soumise à l'injection partielle |
FR1519898A (fr) * | 1967-02-24 | 1968-04-05 | Creusot Forges Ateliers | Perfectionnements aux aubages torses mobiles de turbo-machines |
FR2329845A1 (fr) * | 1975-10-28 | 1977-05-27 | Europ Turb Vapeur | Disposition de liaison continue des aubes mobiles d'une turbo-machine |
FR2337251A1 (fr) * | 1975-12-29 | 1977-07-29 | Europ Turb Vapeur | Etage mobile de turbomachine |
FR2432134A1 (fr) * | 1978-07-25 | 1980-02-22 | Rolls Royce | Structure cantilever, notamment pour aubages de turbines a gaz |
Family Cites Families (16)
Publication number | Priority date | Publication date | Assignee | Title |
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CA873151A (en) * | 1971-06-15 | The Minister Of Aviation In Her Britannic Majesty's Government Of The Un Ited Kingdom Of Great Britain And Northern Ireland | Bladed rotor for fluid flow machines | |
US1061648A (en) * | 1910-08-27 | 1913-05-13 | George Westinghouse | Blades. |
DE606351C (de) * | 1932-03-23 | 1934-11-30 | Vormals Skodawerke Ag | Einrichtung zur Laufschaufelbefestigung fuer Dampf- oder Gasturbinen |
US2315612A (en) * | 1942-02-14 | 1943-04-06 | Westinghouse Electric & Mfg Co | Turbine shrouding |
US2398140A (en) * | 1943-12-08 | 1946-04-09 | Armstrong Siddeley Motors Ltd | Bladed rotor |
US2430140A (en) * | 1945-04-06 | 1947-11-04 | Northrop Hendy Company | Turbine blade and mounting |
US2778854A (en) * | 1953-04-21 | 1957-01-22 | Olin Mathieson | Purified polyethenoxy alkylphenyl ethers |
US3004750A (en) * | 1959-02-24 | 1961-10-17 | United Aircraft Corp | Stator for compressor or turbine |
US3014695A (en) * | 1960-02-03 | 1961-12-26 | Gen Electric | Turbine bucket retaining means |
FR1374917A (fr) * | 1963-11-21 | 1964-10-09 | Ass Elect Ind | Perfectionnements aux déflecteurs d'étanchéité des aubes mobiles de turbines et de compresseurs à écoulement axial |
US3752599A (en) * | 1971-03-29 | 1973-08-14 | Gen Electric | Bucket vibration damping device |
FR2291349A1 (fr) * | 1974-11-14 | 1976-06-11 | Europ Turb Vapeur | Disposition de liaison continue des aubes mobiles d'une turbo-machine |
US3986792A (en) * | 1975-03-03 | 1976-10-19 | Westinghouse Electric Corporation | Vibration dampening device disposed on a shroud member for a twisted turbine blade |
SU985327A1 (ru) * | 1980-03-24 | 1982-12-30 | Всесоюзное Научно-Производственное Объединение "Союзтурбогаз" | Рабочее колесо осевой турбомашины |
US4576551A (en) * | 1982-06-17 | 1986-03-18 | The Garrett Corporation | Turbo machine blading |
CH666722A5 (de) * | 1985-07-05 | 1988-08-15 | Bbc Brown Boveri & Cie | Laufschaufelkranz einer axial durchstroemten turbomaschine. |
-
1987
- 1987-03-12 FR FR8703390A patent/FR2612249B1/fr not_active Expired - Fee Related
-
1988
- 1988-03-04 AU AU12730/88A patent/AU1273088A/en not_active Abandoned
- 1988-03-07 ES ES198888103498T patent/ES2028154T3/es not_active Expired - Lifetime
- 1988-03-07 EP EP88103498A patent/EP0284829B1/de not_active Expired - Lifetime
- 1988-03-07 DE DE8888103498T patent/DE3867102D1/de not_active Expired - Fee Related
- 1988-03-07 AT AT88103498T patent/ATE70891T1/de active
- 1988-03-08 US US07/165,320 patent/US4840539A/en not_active Expired - Fee Related
- 1988-03-10 ZA ZA881716A patent/ZA881716B/xx unknown
- 1988-03-10 CA CA000561132A patent/CA1279826C/fr not_active Expired - Fee Related
- 1988-03-11 MX MX010755A patent/MX167279B/es unknown
- 1988-03-11 JP JP63058152A patent/JPS63246402A/ja active Pending
- 1988-03-11 KR KR1019880002537A patent/KR960004207B1/ko active IP Right Grant
- 1988-03-11 BR BR8801122A patent/BR8801122A/pt not_active IP Right Cessation
- 1988-03-12 CN CN198888101214A patent/CN88101214A/zh active Pending
-
1992
- 1992-02-18 GR GR920400251T patent/GR3003829T3/el unknown
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1544318A (en) * | 1923-09-12 | 1925-06-30 | Westinghouse Electric & Mfg Co | Turbine-blade lashing |
US2772854A (en) * | 1951-02-27 | 1956-12-04 | Rateau Soc | Vibration damping means for bladings of turbo-machines |
FR1382057A (fr) * | 1962-07-11 | 1964-12-18 | Cem Comp Electro Mec | Perfectionnement aux ailetages de turbines à vapeur |
FR1340331A (fr) * | 1962-09-07 | 1963-10-18 | Rateau Soc | Perfectionnements aux dispositifs de liaison des extrémités d'aubes mobiles de turbines |
FR1403799A (fr) * | 1964-05-13 | 1965-06-25 | Rateau Soc | Roue de turbine soumise à l'injection partielle |
FR1519898A (fr) * | 1967-02-24 | 1968-04-05 | Creusot Forges Ateliers | Perfectionnements aux aubages torses mobiles de turbo-machines |
FR2329845A1 (fr) * | 1975-10-28 | 1977-05-27 | Europ Turb Vapeur | Disposition de liaison continue des aubes mobiles d'une turbo-machine |
FR2337251A1 (fr) * | 1975-12-29 | 1977-07-29 | Europ Turb Vapeur | Etage mobile de turbomachine |
FR2432134A1 (fr) * | 1978-07-25 | 1980-02-22 | Rolls Royce | Structure cantilever, notamment pour aubages de turbines a gaz |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5730584A (en) * | 1996-05-09 | 1998-03-24 | Rolls-Royce Plc | Vibration damping |
FR2975123A1 (fr) * | 2011-05-13 | 2012-11-16 | Snecma Propulsion Solide | Rotor de turbomachine comprenant des aubes en materiau composite avec talon rapporte |
WO2012156626A1 (fr) * | 2011-05-13 | 2012-11-22 | Herakles | Rotor de turbomachine comprenant des aubes en materiau composite avec talon rapporte |
US9790802B2 (en) | 2011-05-13 | 2017-10-17 | Snecma | Turbine engine rotor including blade made of composite material and having an added root |
EP2612996A1 (de) * | 2012-01-04 | 2013-07-10 | General Electric Company | Vorrichtung und Verfahren zur Ausrichtung von Spitzendeckbänder |
WO2021176168A1 (fr) * | 2020-03-04 | 2021-09-10 | Safran Aircraft Engines | Procédé pour remboiter des talons d'aubes d'une roue de rotor dans une turbomachine d'aéronef |
FR3107921A1 (fr) * | 2020-03-04 | 2021-09-10 | Safran Aircraft Engines | Procede pour remboiter des talons d’aubes d’une roue de rotor dans une turbomachine d’aeronef |
US11988111B2 (en) | 2020-03-04 | 2024-05-21 | Safran Aircraft Engines | Method for refitting blade shrouds of a rotor wheel in an aircraft turbomachine |
WO2023247857A1 (fr) * | 2022-06-22 | 2023-12-28 | Safran Aircraft Engines | Ensemble aubage de turbomachine comportant des moyens de limitations de vibrations entre plateformes |
FR3137120A1 (fr) * | 2022-06-22 | 2023-12-29 | Safran Aircraft Engines | Ensemble aubagé de turbomachine comportant des moyens de limitations de vibrations entre plateformes |
Also Published As
Publication number | Publication date |
---|---|
KR880011440A (ko) | 1988-10-28 |
EP0284829B1 (de) | 1991-12-27 |
ATE70891T1 (de) | 1992-01-15 |
FR2612249B1 (fr) | 1992-02-07 |
CN88101214A (zh) | 1988-09-21 |
AU1273088A (en) | 1988-09-15 |
FR2612249A1 (fr) | 1988-09-16 |
ES2028154T3 (es) | 1992-07-01 |
ZA881716B (en) | 1988-09-06 |
BR8801122A (pt) | 1988-10-18 |
JPS63246402A (ja) | 1988-10-13 |
GR3003829T3 (de) | 1993-03-16 |
DE3867102D1 (de) | 1992-02-06 |
CA1279826C (fr) | 1991-02-05 |
KR960004207B1 (ko) | 1996-03-28 |
US4840539A (en) | 1989-06-20 |
MX167279B (es) | 1993-03-15 |
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