EP0470907B1 - Vibrationsdämpfer mit Nocken für die Schaufeln eines Bläsertreibwerks - Google Patents
Vibrationsdämpfer mit Nocken für die Schaufeln eines Bläsertreibwerks Download PDFInfo
- Publication number
- EP0470907B1 EP0470907B1 EP91402205A EP91402205A EP0470907B1 EP 0470907 B1 EP0470907 B1 EP 0470907B1 EP 91402205 A EP91402205 A EP 91402205A EP 91402205 A EP91402205 A EP 91402205A EP 0470907 B1 EP0470907 B1 EP 0470907B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- bobweight
- fan
- blades
- rockers
- stem
- 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.)
- Expired - Lifetime
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
-
- 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
- turbomachines such as turboblowers
- One of the problems to be solved in the design of turbomachines, such as turboblowers, is that of seeking to reduce or eliminate the vibrations to which the blades are subjected.
- each blade has a root having a shape also in a dovetail complementary to that of the cross section of said first space, as well as a rod, which connects said root to the blade proper, and two platforms which s 'extend transversely to said rod, one on one side, the other on the other side of the rod, and which separate the rod from the blade proper, however that a second space is delimited between the stem and the platform of a first blade e, the stem and the platform of a second blade adjacent to the first blade, and the top of the tooth separating the roots of
- the invention taking up the general known arrangement, proposes to increase the efficiency thereof by multiplying the reaction forces both in magnitude, as regards their areas of application.
- two rigid rockers are arranged in said second space, being interposed between the counterweight and the rods and platforms of the first and second blades, and are likely, under the effect of the centrifugal force to which the counterweight is subjected, to be in support, on the one hand, mutual one on the other, on the other hand, each on a platform of one of the blades, on a rod of one of the blades and on the counterweight, the bearing zones of a rocker on the platform and on the stem of a blade being distinct.
- the main advantage of the arrangements according to the invention resides in the reduction separately of the vibrations to which the rods and the platforms of the blades are subjected.
- the realization of the rockers in the form of cams reinforces the effort of dissipation of vibrational energy and thus also increases the overall effectiveness of the fight against vibrations.
- the arrangement shown is that of a disc 1 of a turbo-fan, which is rotatably mounted around an axis 2 and whose periphery is formed by teeth 3, angularly regularly spaced and sparing, between any two successive between them a housing 4 shaped like a dovetail.
- Blades 5 are each formed by a root 6, of complementary shape, in dovetail shape, that of a housing 4, by a rod 7 which surmounts the root 6, by the active profile 8 of the blade , placed in the extension of the rod 7, and by two platforms 9, which extend on either side of the rod 7, substantially perpendicular to the general axis 10 of the blade, and which constitute the separation limit of the active profile 8 from the rod 7.
- Each blade 5 is mounted on the disk 1 by introducing its root 6 into a housing 4, the general axis 10 of this blade extending substantially radially relative to the axis of rotation 2 of the disk 1, and the platforms 9 extending substantially parallel to the vertices 3A of the teeth 3 of the disc 1, the ends of the platforms 9 of two successive teeth being adjacent.
- the faces 9A of the platforms 9 oriented towards the axis of rotation 2, the lateral faces 7A of the rods 7 and the apex 3A of a tooth together define a space 11.
- This space 11 contains, on the one hand, a counterweight 12, which either rests by its lower face 12A on the apex 3A delimiting said space 11, or, under the effect of centrifugal force, is slightly detached from said apex 3A, on the other hand, two rockers 13, each having a generally triangular shape.
- each rocker 13 constitute two contact zones 14 and 15 with the face 9A of the platform 9 and with the lateral face 7A of a rod 7 of a blade, respectively.
- the counterweight 12 comprises an oblong part 16, here prismatic with a trapezoidal section, which constitutes its upper part, which has an upper face 16A and in which a groove 17 is formed.
- the face of the third angle of a rocker 13 is shaped as a cam 18 in contact, in the zone 18A with the upper face 16A of the oblong part 16 of the counterweight, and, in a zone 18B with the cam 18 of the second rocker 13.
- the distance D18B of the area 18B relative to the upper face 16A of the oblong part 16 of the counterweight has a variable value, a function of the relative positions of the two rockers 13 mutually and relative to the rods 7 and to the platforms 9 of the blades, this being in relation to the shape of the cam 18.
- the counterweight 12 further comprises an end face 12B, transverse, perpendicular to the axis of rotation 2, which is in axial abutment on the face 19A of the head 19 of a fixing bolt 20, on the disc 1, of a flange 21.
- the periphery of the flange 21 has a cross section shaped like a U, one of which, 23, of the branches is supported on one, 22, of the axial ends of each dawn 5.
- a spring 24, of open annular shape, having two ends 25, surrounds the oblong part 16 of the counterweight, being held in position relative to it by being introduced, partially in the groove 17.
- the ends 25 constitute hooks and are supported, each on a flange 26 which comprises the third angle of each rocker 13.
- the flanges 26 are arranged substantially on the faces of the triangular ends of the rockers 13, which are opposite to the faces 18B of their mutual contact.
- the spring 24 thus constitutes a means of maintaining the assembly of the two rockers 13 and the counterweight 12, which however allows very small relative displacements of these various elements.
- the embodiment shown allows the dissipation of vibrational energy by means of small frictions which occur between the faces in contact: 16A-18A; 9A-14; 7A-15; and, 18B-18B, and, between the ends 22 of the blades and the branch 23 of the flange 21.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Claims (9)
- Turbotriebwerkgebläse, bestehend aus einer Anordnung einer drehenden Scheibe (1) und am Umkreis der Scheibe befestigten Schaufeln (5), bei der einerseits der genannte Umkreis der Scheibe in Form von mehreren Zähnen (3) ausgeführt ist, von denen zwei beliebige aufeinanderfolgende zwischen sich einen ersten Zwischenraum begrenzen, dessen Querschnitt in Form von mindestens einem Schwalbenschwanz (4) ausgeführt ist, und andererseits jede Schaufel einen Fuß (6) ebenfalls in Form eines Schwalbenschwanzes, der komplementär ist zu dem des Querschnitts des genannten ersten Zwischenraums, sowie einen Schaft (7), der den genannten Fuß (6) mit der eigentlichen Schaufel (8) verbindet, und zwei Plattformen (9) aufweist, die quer zum genannten Schaft (7) verlaufen, die eine auf der einen Seite, die andere auf der anderen Seite des Schafts, und die den Schaft (7) von der eigentlichen Schaufel (8) trennen, während ein zweiter Raum (11) zwischen dem Schaft (7) und der Plattform (9) einer ersten Schaufel, dem Schaft (7) und der Plattform (9) einer zweiten Schaufel, die der ersten Schaufel benachbart ist, und dem Kopf (3A) des Zahns (3), der die Füsse (6) der genannten ersten und zweiten Schaufeln voneinander trennt, eingegrenzt ist, und ein Fliehgewicht (12) in dem genannten zweiten Raum enthalten ist und unter Einwirkung der bei der Drehbewegung der Scheibe ausgeübten Zentrifugalkraft in Anlage an die Plattformen (9) und/oder an die Schäfte (7) der genannten ersten und zweiten Schaufel kommen kann,
dadurch gekennzeichnet, daß zwei steife Kipper (13) in dem genannten zweiten Raum angeordnet sind, indem sie zwischen dem Fliehgewicht (12-16) und den Schäften (7) und Plattformen (9) der ersten und zweiten Schaufel eingefügt sind, und geeignet sind, unter Einwirkung der Zentrifugalkraft, der das Fliehgewicht unterworfen ist, einerseits aneinander (18B), andererseits jeweils an (14) einer Plattform (9) einer der Schaufeln, an (15) einem Schaft einer der Schaufeln und an (16A) dem Fliehgewicht (16) in Anlage zu kommen, wobei die Anlagebereiche (14, 15) eines Kippers (13) an der Plattform (9) und an dem Schaft (7) einer Schaufel verschieden sind. - Turbotriebwerkgebläse nach Anspruch 1, dadurch gekennzeichnet, daß die Seite eines Kippers, die mit dem Fliehgewicht (16-12) in Berührung ist, als ein Nocken (18) ausgebildet ist, so daß der Abstand (D 18B) zwischen dem Bereich (18B) des Kontakts der beiden Kipper (13) miteinander und dem Fliehgewicht (16-12) mit dem Kippen der Kipper variabel ist.
- Turbotriebwerkgebläse nach einem der Ansprüche 1 und 2, dadurch gekennzeichnet, daß eine Feder (24) an das Fliehgewicht (16-12) und an jeden der Kipper (13) angehängt ist, so daß der Halt des Zusammenbaus dieser Elemente gewährleistet ist und sie sich dabei leicht zueinander verschieben konnen;
- Turbotriebwerkgebläse nach Anspruch 3, dadurch gekennzeichnet, daß die Feder (24) aus einem offenen Ring mit zwei Enden (25) besteht, die sich in federnder Anlage an den Seiten (6) der beiden Kipper (13) befinden, die den Anlageseiten (18B) der genannten Kipper miteinander gegenüberliegen.
- Turbotriebwerkgebläse nach Anspruch 4, dadurch gekennzeichnet, daß das Fliehgewicht einen länglichen Teil (16) aufweist, der von der Feder (24) umgeben ist.
- Turbotriebwerkgebläse nach Anspruch 5, dadurch gekennzeichnet, daß der genannte längliche Teil (16) mit einer Kehlung (17) versehen ist, die die Feder (24) teilweise aufnimmt.
- Turbotriebwerkgebläse nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß jedes Fliehgewicht (12) eine querliegende Endseite (12B) hat, die sich in Anlage an einem mit der Scheibe (1) fest verbundenen, axialen Anschlag (19A) befindet.
- Turbotriebwerkgebläse nach Anspruch 7, dadurch gekennzeichnet, daß der genannte axiale Anschlag (19A) von dem Kopf (19) einer auf der Scheibe (1) befestigten Schraube (20) gebildet wird.
- Turbotriebwerkgebläse nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß jedes Fliehgewicht (12-16) und die beiden damit verbundenen Kipper (13) sich in dem genannten zweiten Raum (11) befinden, ohne an der Scheibe (1) oder an den Schaufeln (5) befestigt zu sein.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9010107 | 1990-08-08 | ||
FR9010107A FR2665726B1 (fr) | 1990-08-08 | 1990-08-08 | Soufflante de turbomachine a amortisseur dynamique a cames. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0470907A1 EP0470907A1 (de) | 1992-02-12 |
EP0470907B1 true EP0470907B1 (de) | 1994-01-12 |
Family
ID=9399516
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP91402205A Expired - Lifetime EP0470907B1 (de) | 1990-08-08 | 1991-08-08 | Vibrationsdämpfer mit Nocken für die Schaufeln eines Bläsertreibwerks |
Country Status (4)
Country | Link |
---|---|
US (1) | US5143517A (de) |
EP (1) | EP0470907B1 (de) |
DE (1) | DE69100981T2 (de) |
FR (1) | FR2665726B1 (de) |
Families Citing this family (26)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5415526A (en) * | 1993-11-19 | 1995-05-16 | Mercadante; Anthony J. | Coolable rotor assembly |
FR2726323B1 (fr) * | 1994-10-26 | 1996-12-13 | Snecma | Ensemble d'un disque rotatif et d'aubes, notamment utilise dans une turbomachine |
FR2739135B1 (fr) * | 1995-09-21 | 1997-10-31 | Snecma | Agencement amortisseur monte entre des aubes de rotor |
GB9724731D0 (en) * | 1997-11-25 | 1998-01-21 | Rolls Royce Plc | Friction damper |
US6042336A (en) * | 1998-11-25 | 2000-03-28 | United Technologies Corporation | Offset center of gravity radial damper |
GB2344383B (en) * | 1998-12-01 | 2002-06-26 | Rolls Royce Plc | A bladed rotor |
KR20020005034A (ko) * | 1999-05-14 | 2002-01-16 | 칼 하인쯔 호르닝어 | 회전자용 밀봉 시스템을 갖는 터보 머신 |
DE10022244A1 (de) * | 2000-05-08 | 2001-11-15 | Alstom Power Nv | Schaufelanordnung mit Dämpfungselementen |
GB0523106D0 (en) * | 2005-11-12 | 2005-12-21 | Rolls Royce Plc | A cooliing arrangement |
EP1925781A1 (de) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Schaufelanordnung |
DE102009011964A1 (de) * | 2009-03-05 | 2010-09-09 | Mtu Aero Engines Gmbh | Rotor für eine Strömungsmaschine |
DE102010052965B4 (de) * | 2010-11-30 | 2014-06-12 | MTU Aero Engines AG | Dämpfungsmittel zum Dämpfen einer Schaufelbewegung einer Turbomaschine |
EP2520768A1 (de) | 2011-05-02 | 2012-11-07 | MTU Aero Engines AG | Dichteinrichtung für einen integral beschaufelten Rotorgrundkörper einer Strömungsmaschine |
US20130011271A1 (en) * | 2011-07-05 | 2013-01-10 | United Technologies Corporation | Ceramic matrix composite components |
US8985956B2 (en) * | 2011-09-19 | 2015-03-24 | General Electric Company | Compressive stress system for a gas turbine engine |
FR3003294B1 (fr) * | 2013-03-15 | 2018-03-30 | Safran Aircraft Engines | Soufflante de turbomoteur a flux multiple, et turbomoteur equipe d'une telle soufflante |
US10197009B2 (en) * | 2014-07-30 | 2019-02-05 | Pratt & Whitney Canada Corp. | Gas turbine engine ejector |
FR3037097B1 (fr) * | 2015-06-03 | 2017-06-23 | Snecma | Aube composite comprenant une plateforme munie d'un raidisseur |
US10662784B2 (en) | 2016-11-28 | 2020-05-26 | Raytheon Technologies Corporation | Damper with varying thickness for a blade |
US10731479B2 (en) | 2017-01-03 | 2020-08-04 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10677073B2 (en) * | 2017-01-03 | 2020-06-09 | Raytheon Technologies Corporation | Blade platform with damper restraint |
US10220461B2 (en) * | 2017-04-12 | 2019-03-05 | General Electric Company | Hole drilling elastically deformed superalloy turbine blade |
JP7168395B2 (ja) * | 2018-09-26 | 2022-11-09 | 三菱重工航空エンジン株式会社 | ロータアッセンブリ及び回転機械 |
US11193376B2 (en) | 2020-02-10 | 2021-12-07 | Raytheon Technologies Corporation | Disk supported damper for a gas turbine engine |
CN114382549B (zh) * | 2020-10-21 | 2024-04-23 | 中国航发商用航空发动机有限责任公司 | 涡轮和航空发动机 |
US20230194096A1 (en) * | 2021-12-17 | 2023-06-22 | Pratt & Whitney Canada Corp. | Exhaust system for a gas turbine engine and method for using same |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1263677A (fr) * | 1960-07-29 | 1961-06-09 | Havilland Engine Co Ltd | Dispositif antivibratoire applicable à des organes rotatifs |
US3666376A (en) * | 1971-01-05 | 1972-05-30 | United Aircraft Corp | Turbine blade damper |
US4101245A (en) * | 1976-12-27 | 1978-07-18 | United Technologies Corporation | Interblade damper and seal for turbomachinery rotor |
US4182598A (en) * | 1977-08-29 | 1980-01-08 | United Technologies Corporation | Turbine blade damper |
GB2112466A (en) * | 1981-12-30 | 1983-07-20 | Rolls Royce | Rotor blade vibration damping |
SU1127979A1 (ru) * | 1983-02-23 | 1984-12-07 | Предприятие П/Я Р-6837 | Рабочее колесо турбомашины |
FR2585069B1 (fr) * | 1985-07-16 | 1989-06-09 | Snecma | Dispositif de limitation du debattement angulaire d'aubes montees sur un disque de rotor de turbomachine |
JPH0295702A (ja) * | 1988-09-30 | 1990-04-06 | Hitachi Ltd | 動翼制振装置 |
-
1990
- 1990-08-08 FR FR9010107A patent/FR2665726B1/fr not_active Expired - Fee Related
-
1991
- 1991-08-08 EP EP91402205A patent/EP0470907B1/de not_active Expired - Lifetime
- 1991-08-08 US US07/742,010 patent/US5143517A/en not_active Expired - Lifetime
- 1991-08-08 DE DE91402205T patent/DE69100981T2/de not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
DE69100981D1 (de) | 1994-02-24 |
FR2665726B1 (fr) | 1993-07-02 |
DE69100981T2 (de) | 1994-05-11 |
EP0470907A1 (de) | 1992-02-12 |
US5143517A (en) | 1992-09-01 |
FR2665726A1 (fr) | 1992-02-14 |
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