EP0396726A1 - Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine. - Google Patents
Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine.Info
- Publication number
- EP0396726A1 EP0396726A1 EP89913063A EP89913063A EP0396726A1 EP 0396726 A1 EP0396726 A1 EP 0396726A1 EP 89913063 A EP89913063 A EP 89913063A EP 89913063 A EP89913063 A EP 89913063A EP 0396726 A1 EP0396726 A1 EP 0396726A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- segment
- disc
- blades
- downstream
- turbomachine rotor
- 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
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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
Definitions
- the present invention relates to turbomachine rotors and more particularly to the means for axially locking vanes mounted in axial pinouts of the periphery of the disc.
- a first problem consists in ensuring the axial locking of each of the blades in the simplest possible way but also as safe as possible. so that easy disassembly of a blade or the entire stage is also simplified.
- the second problem is that of the seal between the upstream and downstream of a disc and arises crucially in the compressors of turbomachines. Indeed, if the spaces located between the bottom of the disc cavities and the blade roots are not properly masked, large volumes of downstream air can pass under the blade roots and recirculate upstream of the compressor , which decreases the compression ratio thereof and causes the overall efficiency of the turbomachine to drop prohibitively.
- the blade roots comprising means for wedging the blades on the upstream face ⁇ of the disc and a rear spoiler having a transverse groove radially oriented towards the axis of the disc while the disc has a circular groove radially oriented towards its periphery
- the rotor of which comprises an axial locking means downstream of the blades on the disc, simultaneously ensuring sealing between the blade roots and the bottom of the disc cavities
- said downstream locking means of the vanes on the disc being constituted by two split segments, the first of which at least cooperates simultaneously with the grooves of the spoilers of the vanes and the circular groove of the disc, the sum of the thicknesses of the first and second segments being equal to the thickness of the grooves of the blade spoilers.
- turbomachinery of the type currently studied for example fast propeller turbojet engines whose compressor rotors have very small diameters, it is necessary to minimize the height under the platforms and to gain mass on the compressor blades, the solution above mentioned cannot be used because it is too bulky.
- the object of the present invention is therefore to replace the anterior double segmentation with a single monobloc segment. performing both locking and sealing functions.
- the subject of the invention is therefore a turbomachine rotor of the type already indicated above and which is characterized in that the locking means consists of a single split segment with Y-shaped section of which a radially external upstream branch is inserted. in the grooves of the spoilers downstream of the blades and of the disc, the downstream radially external branch of the segment being pressed against the downstream part of the spoilers of the blades.
- FIG. 1 shows a turbomachine rotor stage fitted with the locking means according to the invention according to a first variant;
- - Figure 2 shows a second alternative embodiment of the locking segment;
- FIG. 3 shows a third alternative embodiment of said segment.
- the rotor disc 1 comprises substantially axial cells 2 into which are inserted the feet 3 of blades 4 having an upstream wedging means 5 on the upstream face of the disc 1 and a downstream spoiler 6 comprising a transverse groove 7 radially oriented towards the axis of the disc.
- the latter comprises opposite the groove 7 of the blades a groove 8 radially oriented towards its periphery, which will be used for mounting / dismounting the segment.
- split segment 9 is inserted, the section of which has the shape of a Y with asymmetrical branches 9a and 9b joined together by their common pie 9c.
- the upstream flat branch 9a is inserted into the groove 7.
- the downstream branch 9b longer than the branch 9a, has a curved shape which matches the downstream shape of the spoiler 6 and which rises under the platform 10 of the blade.
- the two branches 9a and 9b can be produced during manufacture with a slight tightening so that during assembly of the segment in its location the downstream branch is pressed against the downstream face of the spoiler 6.
- the pressure coming from the __ P between the upstream and downstream of the disc combined with the centrifugal force, increases the plating of the downstream branch against the blade.
- the segment is produced by welding radially internal parts of two annular sheets of which the downstream one has a curved shape and the upstream one is flat.
- the segment is produced by folding and forming a single annular sheet, the fold of which forms the foot 9c of the Y section of the segment.
- the segment is produced by machining around a one-piece annular blank.
- the segment is assembled by placing the foot 9c of the segment in the groove 8c and compressing it radially so that the upstream branch 9a passes under the spoiler 6. Once pressed forward, the segment can be released radially so that the upstream branch 9a enters the groove 7. In operation, the centrifugal force will maintain the segment in la.gorge 7.
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)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8814913 | 1988-11-17 | ||
FR8814913A FR2639063A1 (fr) | 1988-11-17 | 1988-11-17 | Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0396726A1 true EP0396726A1 (fr) | 1990-11-14 |
EP0396726B1 EP0396726B1 (fr) | 1992-05-13 |
Family
ID=9371914
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP89913063A Expired - Lifetime EP0396726B1 (fr) | 1988-11-17 | 1989-11-16 | Segment d'arret et d'etancheite d'un ensemble d'aubes monte sur un disque de rotor de turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US5052893A (fr) |
EP (1) | EP0396726B1 (fr) |
FR (1) | FR2639063A1 (fr) |
WO (1) | WO1990005837A1 (fr) |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5211407A (en) * | 1992-04-30 | 1993-05-18 | General Electric Company | Compressor rotor cross shank leak seal for axial dovetails |
FR2694046B1 (fr) * | 1992-07-22 | 1994-09-23 | Snecma | Dispositif d'étanchéité et de rétention pour un rotor entaillé de brochages recevant des pieds d'aubes. |
US5257909A (en) * | 1992-08-17 | 1993-11-02 | General Electric Company | Dovetail sealing device for axial dovetail rotor blades |
FR2715975B1 (fr) * | 1994-02-10 | 1996-03-29 | Snecma | Rotor de turbomachine à rainures d'aube débouchantes axiales ou inclinées. |
JP2726895B2 (ja) * | 1994-09-14 | 1998-03-11 | 川崎重工業株式会社 | セラミックブレードの取付構造 |
GB2311826B (en) * | 1996-04-02 | 2000-05-10 | Europ Gas Turbines Ltd | Turbomachines |
CZ20002685A3 (cs) * | 1999-12-20 | 2001-08-15 | General Electric Company | Zařízení pro uchycení lopatek otáčivého stroje a způsob jejich uchycení |
US7252481B2 (en) * | 2004-05-14 | 2007-08-07 | Pratt & Whitney Canada Corp. | Natural frequency tuning of gas turbine engine blades |
US7238008B2 (en) * | 2004-05-28 | 2007-07-03 | General Electric Company | Turbine blade retainer seal |
JP4873200B2 (ja) * | 2007-03-27 | 2012-02-08 | 株式会社Ihi | ファン動翼支持構造とこれを有するターボファンエンジン |
US8038405B2 (en) * | 2008-07-08 | 2011-10-18 | General Electric Company | Spring seal for turbine dovetail |
US8210820B2 (en) * | 2008-07-08 | 2012-07-03 | General Electric Company | Gas assisted turbine seal |
US8011894B2 (en) * | 2008-07-08 | 2011-09-06 | General Electric Company | Sealing mechanism with pivot plate and rope seal |
US8215914B2 (en) * | 2008-07-08 | 2012-07-10 | General Electric Company | Compliant seal for rotor slot |
US8210823B2 (en) * | 2008-07-08 | 2012-07-03 | General Electric Company | Method and apparatus for creating seal slots for turbine components |
US8210821B2 (en) * | 2008-07-08 | 2012-07-03 | General Electric Company | Labyrinth seal for turbine dovetail |
FR2939832B1 (fr) * | 2008-12-11 | 2011-01-07 | Turbomeca | Roue de turbine equipee d'un dispositif de retenue axiale verrouillant des pales par rapport a un disque. |
US8657580B2 (en) * | 2010-06-17 | 2014-02-25 | Pratt & Whitney | Blade retainment system |
FR2974863B1 (fr) * | 2011-05-06 | 2015-10-23 | Snecma | Disque de soufflante de turbomachine |
FR3127255A1 (fr) * | 2021-09-23 | 2023-03-24 | Safran Aircraft Engines | Ensemble rotatif pour turbomachine |
EP4230843A1 (fr) * | 2022-02-17 | 2023-08-23 | Siemens Energy Global GmbH & Co. KG | Agencement de rotor pour un rotor d'une turbine à gaz |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB802476A (en) * | 1955-09-29 | 1958-10-08 | Rolls Royce | Improvements in or relating to rotors of axial-flow fluid machines for example compressors and turbines |
DE1116094B (de) * | 1959-07-22 | 1961-10-26 | Buessing Nutzkraftwagen G M B | Schwimmvorrichtung fuer Landfahrzeuge |
GB905582A (en) * | 1960-05-26 | 1962-09-12 | Rolls Royce | Improvements relating to the sealing of blades in a bladed rotor |
US3853425A (en) * | 1973-09-07 | 1974-12-10 | Westinghouse Electric Corp | Turbine rotor blade cooling and sealing system |
FR2324873A1 (fr) * | 1975-09-17 | 1977-04-15 | Snecma | Perfectionnements aux flasques de rotors de turbomachines |
FR2419389A1 (fr) * | 1978-03-08 | 1979-10-05 | Snecma | Perfectionnements aux flasques de rotors de turbomachines |
JPS6339741A (ja) * | 1986-07-30 | 1988-02-20 | Mazda Motor Corp | 部品組付装置 |
FR2603333B1 (fr) * | 1986-09-03 | 1990-07-20 | Snecma | Rotor de turbomachine comportant un moyen de verrouillage axial et d'etancheite d'aubes montees dans des brochages axiaux du disque et procede de montage |
-
1988
- 1988-11-17 FR FR8814913A patent/FR2639063A1/fr active Pending
-
1989
- 1989-11-16 WO PCT/FR1989/000588 patent/WO1990005837A1/fr active IP Right Grant
- 1989-11-16 US US07/543,717 patent/US5052893A/en not_active Expired - Fee Related
- 1989-11-16 EP EP89913063A patent/EP0396726B1/fr not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO9005837A1 * |
Also Published As
Publication number | Publication date |
---|---|
FR2639063A1 (fr) | 1990-05-18 |
EP0396726B1 (fr) | 1992-05-13 |
WO1990005837A1 (fr) | 1990-05-31 |
US5052893A (en) | 1991-10-01 |
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