WO2012056161A1 - Ensemble de disques de rotor pour une turbomachine - Google Patents
Ensemble de disques de rotor pour une turbomachine Download PDFInfo
- Publication number
- WO2012056161A1 WO2012056161A1 PCT/FR2011/052483 FR2011052483W WO2012056161A1 WO 2012056161 A1 WO2012056161 A1 WO 2012056161A1 FR 2011052483 W FR2011052483 W FR 2011052483W WO 2012056161 A1 WO2012056161 A1 WO 2012056161A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- downstream
- discs
- ferrule
- upstream
- flange
- Prior art date
Links
- 238000011144 upstream manufacturing Methods 0.000 claims description 35
- 240000006108 Allium ampeloprasum Species 0.000 claims description 3
- 235000005254 Allium ampeloprasum Nutrition 0.000 claims description 3
- 238000001816 cooling Methods 0.000 claims description 3
- 238000009423 ventilation Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000007789 sealing Methods 0.000 description 2
- 238000005242 forging Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/005—Sealing means between non relatively rotating elements
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a set of rotor discs for a turbomachine, such as a turbojet or an airplane turboprop.
- the rotor of the turbine comprises a plurality of discs on the periphery of which are formed cells for mounting the blade roots.
- the discs are centered on the axis of the turbomachine and are connected to each other and to a turbine shaft by upstream and downstream flanges, the downstream flange of an upstream disc being fixed to the upstream flange of a downstream disc by the intermediate bolts.
- An annular flange for holding the blade roots is fixed to the upstream flange of the downstream disk and extends up to the cells of the disk so as to form an axial abutment for the blade roots mounted on the disk.
- This flange further carries wipers intended to cooperate with blocks of abradable material mounted on vanes fixed by a distributor located axially between the two aforementioned upstream and downstream disks.
- the wipers and the abradable blocks form sealing means of the labyrinth seal type.
- An annular space is delimited between the flange and the upstream flange of the downstream disc and is, upstream, supplied with guided air to the cells of the downstream disc to cool them.
- the discs are machined from a forged raw element having large axial dimensions necessary to form the flanges extending upstream and downstream. The resulting machining times and costs are very important.
- discs consisting of a radial rim devoid of axial flange. Two disks of this type are then connected via another type of disc, interposed axially between them, and having upstream and downstream flanges of very large lengths. If the machining of disks without flanges is greatly reduced, it remains very important for the interposed discs with the flanges.
- the ferrules carrying the darts are also to be redefined, given the structural modifications made to the disks.
- the invention aims in particular to provide a simple, effective and economical solution to this problem.
- a set of rotor disks for a turbomachine such as a turbojet or an airplane turbo-prop, comprising disks fixedly bolted together and formed at their outer periphery with mounting cavities of feet of blades, characterized in that each disk is formed by a rim extending radially and devoid of axial flange, two consecutive disks being connected by means of an axially extending ferrule fixed to the rims of the disks and equipped with a flange for holding the blade roots of the downstream disc, and in that the ferrule comprises cooling openings at its downstream end, said openings opening into a ventilation space formed upstream of the downstream disc and delimited by the ferrule and the flange holding the blade roots.
- all the disks may be free of flanges, which facilitates their manufacture by machining.
- the shells may, in turn, be rolled using pressure rollers, to reduce the thickness of material to be machined. The machining of these ferrules is therefore faster and less expensive.
- cooling openings effectively provide ventilation of the mounting cells of the blade roots formed in the downstream disk.
- balancing leeks are formed at the radially inner ends of the rims.
- the axial ends of the ferrule comprise annular flanges fixed to the rims of the upstream and downstream discs by means of bolts.
- the ferrule comprises a frustoconical or cylindrical median portion and cylindrical rims at its upstream and downstream ends, these flanges being radially plated against the rims of the upstream and downstream discs.
- the ferrule may comprise a median portion formed with wipers intended to cooperate with blocks of abradable material mounted on vanes of a distributor.
- This median portion preferably having a cylindrical flange extending upstream and on which are formed wipers.
- the flange for holding the blade roots of the downstream disc is in one piece with the ferrule.
- the retaining flange is a separate part of the ferrule and is mounted in abutment between an outer annular flange of the shell and the downstream disk.
- the invention also relates to a turbomachine, such as a turbojet or an airplane turboprop, comprising a low-pressure turbine whose rotor is formed by a set of disks of the aforementioned type.
- - Figure 1 is a partial view in axial section of a set of rotor discs, according to a first embodiment of the prior art
- - Figure 2 is a partial view in axial section of a set of rotor discs, according to a second embodiment of the prior art
- FIG. 3 is a partial view in axial section of a set of rotor discs, according to a first embodiment of the invention
- FIG. 4 is a view corresponding to FIG. 1, illustrating a second embodiment of the invention.
- FIG. 1 A first embodiment of a turbine rotor 1 of the prior art is shown in FIG.
- This rotor 1 comprises a plurality of discs 2 on the periphery of which are formed cavities 3 for mounting blade roots 4.
- the discs 2 are centered on the axis of the turbomachine and are connected to one another and to a turbine shaft by means of upstream and downstream flanges 5, 6, the downstream flange 6 of an upstream disk 2 being fixed to the upstream flange 5 of a downstream disk 2 by means of bolts 7.
- An annular flange 8 for holding the blade roots 4 is fastened by the bolts 7 to the upstream flange 5 of the downstream disc 2 and extends up to the cavities of the disc so as to form an axial abutment for the feet of the disc. blades 4 of the disk 2.
- This flange 8 also carries wipers 9 intended to cooperate with blocks of abradable material 10 mounted on fixed blades 1 1 of a distributor located axially between the two upstream and downstream discs 2 above.
- the wipers 9 and the abradable blocks 10 form sealing means of the labyrinth seal type.
- An annular space is delimited between the flange 8 and the upstream flange 5 of the downstream disk 2 and is, upstream, supplied with guided air to the cells of the downstream disk 2 to cool them.
- FIG. 2 A second embodiment of a turbine rotor 1 of the prior art is illustrated in Figure 2.
- This rotor 1 comprises discs 12 having a radial rim 13 without axial flange.
- Two discs 12 of this type are then connected via a disc 14 of another type, interposed axially between them, and having upstream and downstream flanges 15, 16 of very large length.
- Ferrules 17 carrying wipers 18 are interposed axially between two discs 12, and are clutched to the downstream disc 12, so as to be rotatably connected with the rotor 1.
- the invention proposes a set of rotor disks 1, in particular for a low-pressure turbine of a turbomachine, a first embodiment of which is shown in FIG. 3.
- This assembly comprises rotor disks. 19, 20, 21 fixedly connected by bolting and formed at their outer periphery with cells 3 for mounting blade roots.
- Each disc 19, 20, 21 is formed by a radial rim 22 without axial flange. Balancing leeks 23 are formed at the radially inner ends of the rims 22.
- the consecutive discs are interconnected by ferrules 24 extending axially and fixed to the rims 22 of the discs by bolting.
- Each ferrule 24 has a frustoconical central portion 25 having a cylindrical rim 26 extending upstream and carrying wipers 18 intended to cooperate with blocks of abradable material mounted on vanes of a distributor, in the same way as previously.
- the shell 24 also has cylindrical flanges 27, 28 at its upstream and downstream ends, these flanges being pressed radially against the rims 22 of the upstream and downstream discs 19, 20, 21.
- Ring flanges 29 extend radially inwards from these flanges 27, 28 and are fixed to the rims 22 of the upstream and downstream discs by means of bolts 7.
- the ferrule 24 also comprises a frustoconical holding flange 30 of the blade roots of the downstream disc, formed integrally with the ferrule 24 in this embodiment, the flange 30 extending downstream and outwards, since the downstream edge 28.
- the assembly according to the invention also comprises an upstream flange 31 having an annular portion 32 pressed against the rim 22 of the upstream disc 19 and a portion 33 whose section has a hook shape, intended to maintain the blade roots in the cavities 3 of the upstream disk 19.
- Air passage holes 34 may be made in the downstream rim 28 of each shell, so as to cool the blade roots housed in the cavities 3.
- FIG. 4 illustrates a second embodiment which differs from that of FIG. 3 in that the holding flange 30 is a part distinct from the ferrule 24, of generally frustoconical shape, which is mounted in abutment between an outer annular flange 35 ferrule 24 and the downstream disc.
- This embodiment makes it possible to produce the retaining flange 30 in a material different from that of the ferrule 24.
- the hot zones are located close to the axis of the rotor, that is to say at the level of the holding flanges 30. These must be made of a material resistant to high temperatures.
- the other zones of the ferrule 24 are subjected to lower temperatures, but withstand significant mechanical stresses. They must therefore be made of a material that accepts such constraints.
- the invention can significantly reduce machining disks 19, 20, 21, and therefore their cost and manufacturing time. Indeed, all the disks 19, 20, 21 are free of flanges, so that the forging to be machined to obtain the disk has contours very close to the final contours.
- the machining of the rings 24 is easier, especially since they can be rolled before machining, so that the contour of the workpiece after rolling is close to the contour to obtain.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1308276.3A GB2498321B (en) | 2010-10-28 | 2011-10-25 | A set of rotor disks for a turbine engine |
US13/882,058 US9371742B2 (en) | 2010-10-28 | 2011-10-25 | Set of rotor disks for a turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1058901 | 2010-10-28 | ||
FR1058901A FR2966867B1 (fr) | 2010-10-28 | 2010-10-28 | Ensemble de disques de rotor pour une turbomachine |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012056161A1 true WO2012056161A1 (fr) | 2012-05-03 |
Family
ID=44080175
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2011/052483 WO2012056161A1 (fr) | 2010-10-28 | 2011-10-25 | Ensemble de disques de rotor pour une turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US9371742B2 (fr) |
FR (1) | FR2966867B1 (fr) |
GB (1) | GB2498321B (fr) |
WO (1) | WO2012056161A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3301258A1 (fr) * | 2016-09-30 | 2018-04-04 | Safran Aircraft Engines | Disque de rotor comportant une toile a epaisseur variable |
FR3095669A1 (fr) * | 2019-05-02 | 2020-11-06 | Safran Aircraft Engines | Disque de rotor comportant un insert de boulonnage |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2966867B1 (fr) * | 2010-10-28 | 2015-05-29 | Snecma | Ensemble de disques de rotor pour une turbomachine |
FR3075284B1 (fr) * | 2017-12-18 | 2020-09-04 | Safran Aircraft Engines | Dispositif amortisseur |
FR3077327B1 (fr) * | 2018-01-30 | 2020-02-21 | Safran Aircraft Engines | Ensemble pour turbine de turbomachine comprenant un anneau mobile d'etancheite |
US10954861B2 (en) | 2019-03-14 | 2021-03-23 | Raytheon Technologies Corporation | Seal for a gas turbine engine |
US11428104B2 (en) | 2019-07-29 | 2022-08-30 | Pratt & Whitney Canada Corp. | Partition arrangement for gas turbine engine and method |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2662685A (en) * | 1949-07-13 | 1953-12-15 | Materiels Hispano Suiza S A So | Rotor for fluid machines |
EP1079070A2 (fr) * | 1999-08-26 | 2001-02-28 | Asea Brown Boveri Ag | Bouclier thermique pour un rotor de turbine |
EP1329589A1 (fr) * | 2002-01-17 | 2003-07-23 | Snecma Moteurs | Amenagement de rotor d'une turbomachine |
EP2009235A1 (fr) | 2007-06-27 | 2008-12-31 | Snecma | Dispositif de refroidissement des alvéoles périphériques d'un disque de rotor de turbomachine à double alimentation en air |
Family Cites Families (19)
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US2860851A (en) * | 1953-12-11 | 1958-11-18 | Havilland Engine Co Ltd | Multi-stage turbine rotor assemblies |
US3146938A (en) * | 1962-12-28 | 1964-09-01 | Gen Electric | Shrouding for compressor stator vanes |
GB1148339A (en) * | 1966-10-20 | 1969-04-10 | Rolls Royce | Compressors or turbines for gas turbine engines |
US3451653A (en) * | 1967-03-22 | 1969-06-24 | Gen Electric | Turbomachinery rotors |
US3597110A (en) * | 1969-10-23 | 1971-08-03 | Gen Electric | Joint construction |
US4088422A (en) * | 1976-10-01 | 1978-05-09 | General Electric Company | Flexible interstage turbine spacer |
FR2404212A1 (fr) * | 1977-09-23 | 1979-04-20 | Snecma | Dispositif d'equilibrage d'un rotor |
US4655683A (en) * | 1984-12-24 | 1987-04-07 | United Technologies Corporation | Stator seal land structure |
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 |
US5630703A (en) * | 1995-12-15 | 1997-05-20 | General Electric Company | Rotor disk post cooling system |
FR2748224B1 (fr) * | 1996-05-02 | 1998-06-19 | Snecma | Outillage de montage d'un distributeur de turbomachine |
FR2825748B1 (fr) * | 2001-06-07 | 2003-11-07 | Snecma Moteurs | Agencement de rotor de turbomachine a deux disques aubages separes par une entretoise |
DE10355230A1 (de) * | 2003-11-26 | 2005-06-23 | Mtu Aero Engines Gmbh | Rotor für eine Turbomaschine |
GB0412476D0 (en) * | 2004-06-04 | 2004-07-07 | Rolls Royce Plc | Seal system |
DE102008048006B4 (de) * | 2008-09-19 | 2019-02-21 | MTU Aero Engines AG | Wellenleistungstriebwerk, insbesondere für ein Luftfahrzeug, mit einem Kühlgasführungssystem im Bereich der Befestigungsflansche der Rotorscheiben |
FR2958322B1 (fr) * | 2010-04-01 | 2013-03-15 | Snecma | Rotor de moteur a turbine a gaz comprenant un tambour de rotor et une couronne de rotor |
FR2965291B1 (fr) * | 2010-09-27 | 2015-01-23 | Snecma | Ensemble unitaire de disques de rotor pour une turbomachine |
FR2966867B1 (fr) * | 2010-10-28 | 2015-05-29 | Snecma | Ensemble de disques de rotor pour une turbomachine |
FR2971004B1 (fr) * | 2011-02-01 | 2013-02-15 | Snecma | Procede d'assemblage d'une turbine basse-pression de turboreacteur a double corps |
-
2010
- 2010-10-28 FR FR1058901A patent/FR2966867B1/fr active Active
-
2011
- 2011-10-25 GB GB1308276.3A patent/GB2498321B/en active Active
- 2011-10-25 US US13/882,058 patent/US9371742B2/en active Active
- 2011-10-25 WO PCT/FR2011/052483 patent/WO2012056161A1/fr active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2662685A (en) * | 1949-07-13 | 1953-12-15 | Materiels Hispano Suiza S A So | Rotor for fluid machines |
EP1079070A2 (fr) * | 1999-08-26 | 2001-02-28 | Asea Brown Boveri Ag | Bouclier thermique pour un rotor de turbine |
EP1329589A1 (fr) * | 2002-01-17 | 2003-07-23 | Snecma Moteurs | Amenagement de rotor d'une turbomachine |
EP2009235A1 (fr) | 2007-06-27 | 2008-12-31 | Snecma | Dispositif de refroidissement des alvéoles périphériques d'un disque de rotor de turbomachine à double alimentation en air |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3301258A1 (fr) * | 2016-09-30 | 2018-04-04 | Safran Aircraft Engines | Disque de rotor comportant une toile a epaisseur variable |
FR3057015A1 (fr) * | 2016-09-30 | 2018-04-06 | Safran Aircraft Engines | Disque de rotor comportant une toile a epaisseur variable |
US10767484B2 (en) | 2016-09-30 | 2020-09-08 | Safran Aircraft Engines | Rotor disk comprising a variable thickness web |
FR3095669A1 (fr) * | 2019-05-02 | 2020-11-06 | Safran Aircraft Engines | Disque de rotor comportant un insert de boulonnage |
Also Published As
Publication number | Publication date |
---|---|
GB201308276D0 (en) | 2013-06-12 |
US9371742B2 (en) | 2016-06-21 |
GB2498321A (en) | 2013-07-10 |
FR2966867A1 (fr) | 2012-05-04 |
GB2498321B (en) | 2017-07-05 |
FR2966867B1 (fr) | 2015-05-29 |
US20130209238A1 (en) | 2013-08-15 |
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