EP0165860B1 - Axiale Schaufelverriegelung für eine Turbomaschine - Google Patents
Axiale Schaufelverriegelung für eine Turbomaschine Download PDFInfo
- Publication number
- EP0165860B1 EP0165860B1 EP85401152A EP85401152A EP0165860B1 EP 0165860 B1 EP0165860 B1 EP 0165860B1 EP 85401152 A EP85401152 A EP 85401152A EP 85401152 A EP85401152 A EP 85401152A EP 0165860 B1 EP0165860 B1 EP 0165860B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- disc
- blade
- locking ring
- axial
- blade root
- 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
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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/32—Locking, e.g. by final locking blades or keys
- F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
Definitions
- the present invention relates to an axial locking device for a turbomachine blade.
- Document FR-A-2 345 605 constitutes the state of the art closest to the invention and has served as a basis for establishing the preamble of the main claim of the present invention.
- the object of the present invention is to remedy these drawbacks by using a device allowing unitary disassembly of the blades.
- a locking ring having regularly spaced notches in each of which is inserted an axial protuberance of each blade root projecting downstream of the disc and said axial protuberance of the blade root has on its sides two radial grooves which cooperate with the edges of the notches of the locking ring by lifting the blade foot under the action of the wedge.
- This locking device makes it possible, compared to French patent 2,507,679, to use a simplified disc and to avoid the presence of teeth both on the blades and on the disc, the realization of which is difficult.
- the device according to the invention allows unitary disassembly of the blades unlike known collective locks which require unlocking of an entire sector to disassemble a blade.
- the locking ring according to the invention which is in one piece does not add any additional force to the disc supporting it unlike sectored rings whose centrifugal forces are taken up by the disc.
- the embodiment in which the locking ring is integrated into the compressor drum has the advantage of a further reduction in the number of parts because the attachment of the disc to the drum is achieved by means of the ring of locking.
- Figure 1 there is shown a disc 1 of a turbomachine rotor having at the upper part of the upstream face a rim which is smooth, the lower part of the rim having a flange 2 on which is fixed a conical front cover 3 .
- the rim of the disc 1 On its downstream face the rim of the disc 1 has a radial flange 5 which is intended for fixing, by bolts 6 of a locking ring 7 and of a sealing ring 8.
- the sealing ring 8 comes to bear on the downstream edge of the platform 9 of the vanes 10 and its internal edge on the drum 11 of the intermediate compressor.
- a lower flange 12 is also provided on the downstream face of the rim of the disc 1 and on this flange is fixed the drum 11 of the low pressure compressor.
- Each blade 10 is mounted on the disk 1 by means of a foot 13 with a section in the shape of a dovetail and which is slidably engaged in a cell 4 of the disk, said blade foot 13 being locked radially by a wedge 14 engaged between said foot 13 of the blade and the bottom of the cell 4.
- the wedge 14 bears on one side against a stop 15 of the front cover 3 and on the other side against a flange 16 of the drum 11.
- the rear part of the blade root 13 is extended by an axial protuberance 17 which is engaged in one of the notches 18 ( Figures 1, 3, 4 and 5) provided in the locking ring 7, said notches are regularly spaced in number equal to that of the blades.
- the notches 18 of the ring 7 are located opposite the cells 4 of the disc rim and their sides partially mask each side of the cells 4.
- the axial protuberance 17 which projects beyond the downstream face of the disc has two radial grooves 19, 19a machined on the sides of said protuberance ( Figures 3 and 5).
- the grooves 19, 19a are engaged on the edges of the notch 18 of the locking ring 7 during the lifting of the foot 13 of the blade under the action of the wedge 14 thus ensuring the axial locking of the blade 10 .
- the rear part of the foot 13 is extended by a radial protuberance 20 which can come to bear against the bottom of the notch 18, in the case of loss of a blade.
- Each blade 10 is inserted from front to back into the corresponding socket 4 of the disc, until the rear face of the stilt comes to bear on the ring.
- the front cover 3 is mounted on the flange 2 which axially locks the shims 4 in abutment against the flange 15.
- the cover 3 is removed and the shim 14 is deposited, which has the effect of allowing the blade to descend to the bottom of the cell 4 and to release the rear part and the protuberance 17 of the locking ring 7.
- the locking ring 7 is integrated into the drum 22 of the low pressure compressor and forms only one piece with it.
- the ring 7 has, as previously, indentations 18 in which is engaged by radial grooves 19, 19a the protuberance 17 of the foot 13 of the dawn.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Claims (3)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8409286 | 1984-06-14 | ||
FR8409286A FR2566061B1 (fr) | 1984-06-14 | 1984-06-14 | Dispositif de verrouillage axial d'une aube de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0165860A1 EP0165860A1 (de) | 1985-12-27 |
EP0165860B1 true EP0165860B1 (de) | 1988-03-16 |
Family
ID=9304994
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP85401152A Expired EP0165860B1 (de) | 1984-06-14 | 1985-06-12 | Axiale Schaufelverriegelung für eine Turbomaschine |
Country Status (5)
Country | Link |
---|---|
US (1) | US4604033A (de) |
EP (1) | EP0165860B1 (de) |
JP (1) | JPS6111404A (de) |
DE (1) | DE3561897D1 (de) |
FR (1) | FR2566061B1 (de) |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
US4836750A (en) * | 1988-06-15 | 1989-06-06 | Pratt & Whitney Canada Inc. | Rotor assembly |
FR2681374B1 (fr) * | 1991-09-18 | 1993-11-19 | Snecma | Fixation d'aube de souflante de turboreacteur. |
US5318405A (en) * | 1993-03-17 | 1994-06-07 | General Electric Company | Turbine disk interstage seal anti-rotation key through disk dovetail slot |
FR2715975B1 (fr) * | 1994-02-10 | 1996-03-29 | Snecma | Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées. |
US6634863B1 (en) * | 2000-11-27 | 2003-10-21 | General Electric Company | Circular arc multi-bore fan disk assembly |
FR2841933B1 (fr) * | 2002-07-04 | 2004-12-03 | Snecma Moteurs | Cale autobloquante |
JP4911286B2 (ja) * | 2006-03-14 | 2012-04-04 | 株式会社Ihi | ファンのダブテール構造 |
JP4807113B2 (ja) * | 2006-03-14 | 2011-11-02 | 株式会社Ihi | ファンのダブテール構造 |
US20090053064A1 (en) * | 2006-09-01 | 2009-02-26 | Ress Jr Robert A | Fan blade retention system |
FR2915495B1 (fr) | 2007-04-30 | 2010-09-03 | Snecma | Procede de reparation d'une aube mobile de turbomachine |
US9662721B2 (en) * | 2008-02-26 | 2017-05-30 | United Technologies Corporation | Method of generating a curved blade retention slot in a turbine disk |
FR2929660B1 (fr) | 2008-04-07 | 2012-11-16 | Snecma | Dispositif anti-usure pour rotor de turbomachine, bouchon formant dispositif anti-usure et rotor de compresseur de moteur a turbine a gaz comportant un bouchon anti-usure |
US8419370B2 (en) * | 2009-06-25 | 2013-04-16 | Rolls-Royce Corporation | Retaining and sealing ring assembly |
FR2948725B1 (fr) * | 2009-07-28 | 2012-10-05 | Snecma | Dispositif anti-usure d'un rotor de turbomachine |
FR2965843B1 (fr) * | 2010-10-06 | 2012-11-09 | Snecma | Rotor pour turbomachine |
FR2972759B1 (fr) * | 2011-03-15 | 2015-09-18 | Snecma | Systeme d'etancheite et de retenue axiale des aubes pour une roue de turbine de turbomachine |
FR2974863B1 (fr) * | 2011-05-06 | 2015-10-23 | Snecma | Disque de soufflante de turbomachine |
FR2986284B1 (fr) | 2012-01-31 | 2014-03-28 | Snecma | Procede de reparation de marques d’usure. |
FR3075284B1 (fr) * | 2017-12-18 | 2020-09-04 | Safran Aircraft Engines | Dispositif amortisseur |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3378230A (en) * | 1966-12-16 | 1968-04-16 | Gen Electric | Mounting of blades in turbomachine rotors |
FR2345605A1 (fr) * | 1976-03-25 | 1977-10-21 | Snecma | Dispositif de retenue pour aubes de soufflantes |
FR2492906A2 (fr) * | 1976-03-25 | 1982-04-30 | Snecma | Dispositif de retenue pour aubes de soufflantes |
US4221542A (en) * | 1977-12-27 | 1980-09-09 | General Electric Company | Segmented blade retainer |
US4265595A (en) * | 1979-01-02 | 1981-05-05 | General Electric Company | Turbomachinery blade retaining assembly |
FR2507679A1 (fr) * | 1981-06-12 | 1982-12-17 | Snecma | Dispositif de verrouillage d'une aube de rotor de turbomachine |
US4453890A (en) * | 1981-06-18 | 1984-06-12 | General Electric Company | Blading system for a gas turbine engine |
FR2519072B1 (fr) * | 1981-12-29 | 1986-05-30 | Snecma | Dispositif de retenue axiale et radiale d'aube de rotor de turboreacteur |
US4451205A (en) * | 1982-02-22 | 1984-05-29 | United Technologies Corporation | Rotor blade assembly |
FR2524932A1 (fr) * | 1982-04-08 | 1983-10-14 | Snecma | Dispositif de retenue axiale de pieds d'aube dans un disque de turbomachine |
FR2535793B1 (fr) * | 1982-11-08 | 1987-04-10 | Snecma | Dispositif de verrouillage axial d'aubes de soufflante |
FR2535794A1 (fr) * | 1982-11-08 | 1984-05-11 | Snecma | Dispositif de retenue axiale et radiale d'aubes de soufflante |
-
1984
- 1984-06-14 FR FR8409286A patent/FR2566061B1/fr not_active Expired
-
1985
- 1985-06-11 US US06/743,599 patent/US4604033A/en not_active Expired - Lifetime
- 1985-06-12 JP JP60127904A patent/JPS6111404A/ja active Granted
- 1985-06-12 EP EP85401152A patent/EP0165860B1/de not_active Expired
- 1985-06-12 DE DE8585401152T patent/DE3561897D1/de not_active Expired
Also Published As
Publication number | Publication date |
---|---|
JPS6111404A (ja) | 1986-01-18 |
JPH0340204B2 (de) | 1991-06-18 |
EP0165860A1 (de) | 1985-12-27 |
DE3561897D1 (en) | 1988-04-21 |
FR2566061A1 (fr) | 1985-12-20 |
US4604033A (en) | 1986-08-05 |
FR2566061B1 (fr) | 1988-09-02 |
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