EP0789133A1 - Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor - Google Patents

Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor Download PDF

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Publication number
EP0789133A1
EP0789133A1 EP97400211A EP97400211A EP0789133A1 EP 0789133 A1 EP0789133 A1 EP 0789133A1 EP 97400211 A EP97400211 A EP 97400211A EP 97400211 A EP97400211 A EP 97400211A EP 0789133 A1 EP0789133 A1 EP 0789133A1
Authority
EP
European Patent Office
Prior art keywords
disc
labyrinth
fixing
rotor
rim
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
Application number
EP97400211A
Other languages
English (en)
French (fr)
Other versions
EP0789133B1 (de
Inventor
Frédéric Chambon
Jacques Henri Mouchel
Patrick Didier Michel Lestoille
Jean-Claude Taillant
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0789133A1 publication Critical patent/EP0789133A1/de
Application granted granted Critical
Publication of EP0789133B1 publication Critical patent/EP0789133B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • 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 invention relates to turbomachines, such as axial flow turbojets using labyrinth sealing devices to separate chambers containing air and / or oil. This is the case, in particular, of the labyrinth fixed upstream of the high pressure turbine.
  • turbomachines involving air flows at different pressures and temperatures
  • This part as it is placed, undergoes extremely high mechanical forces, due, in particular, to centrifugal force, since it is placed on the rotor.
  • a difficult environment is added to this because the air flow surrounding it is rather oxidizing and the thermal level is very high.
  • this part also called the front labyrinth of the high-pressure turbine, is one of the most difficult parts to size. This operation can also sometimes lead to giving it an insufficient lifespan, or a limitation in its thermal qualities.
  • this labyrinth disk 2 has several parts, including the labyrinth itself being largely opposite the arrow referenced 2.
  • the lips of this labyrinth are carried by a rim 3 extending towards the top by a vault 4 which bears on a downstream surface 5 of the disc 8 of the rotor to which this part is fixed.
  • This fixing is carried out, on many current turbojets, by means of bolts 6 passing through the interior part of this part which ends in an interior stiffener 7.
  • the object of the invention is to optimize the shape of this part which is the labyrinth disk and its device for fixing to the disk 8 of the rotor of the high pressure turbine.
  • the labyrinth disc comprises a main stiffener incorporated in the rim, just inside the labyrinth.
  • the arch is an upper part of the rim which is fairly radially elongated, slightly curved, its downstream surface being placed at the axial level of the downstream end of the main stiffener.
  • the fixing means comprise fixing bolts placed in fixing holes made in the inner part of the rim, inside and upstream of the stiffener.
  • the fixing means consist of fixing teeth intended to be placed behind teeth of a bayonet locking system fixed on the rotor.
  • the arch can include stiffeners placed in the interior extension of the fixing teeth.
  • Axial stops can complete the system by coming into abutment opposite the rotor stop surfaces placed on an upstream surface thereof.
  • the vault of the labyrinth disc according to the invention may include stiffeners placed on the downstream surface of the rim.
  • Part of the downstream surface of the vault can then act as an axial abutment surface, in particular when the latter has ribs.
  • the axial stops can also be provided by the inner surface of the fixing teeth.
  • the labyrinth disk, object of the invention is placed substantially in the same place as that where the labyrinth disk of FIG. 1 is placed.
  • rim 13 which constitutes the radial framework of this part.
  • the inner part of this rim 13 ends with an inner stiffener 9 which is less consistent than that referenced 7 in FIG. 1.
  • the labyrinth 10 of the labyrinth disc is made up of two parts, each comprising several lips tangent with the friction parts 16 fixed on a fixed part 17 attached to the stator inside and at the outlet of the combustion chamber 20.
  • the rim 13 is extended by a central part comprising passages 11 and lower orifices 15 allowing the passage of the cooling air flow from the upstream part to the downstream part of the labyrinth disc.
  • the outer part of the labyrinth disk 12, according to the invention, is constituted by the arch 14 extending the rim 13 to bear by an outer end 18 on an upstream surface 19 of the rotor.
  • This vault 14 is slightly less rounded than that of FIG. 1.
  • the internal stiffener 9 is of reduced shape.
  • a main stiffener 23 is provided in the middle of the labyrinth disc 12, that is to say on the rim 13. Its shape is such that it forms a toric bead which protrudes over the downstream surface 22 of the labyrinth disc 12 , just below the labyrinth lips 10, below the passages 11. Its downstream end is at the same longitudinal level as the downstream end of the downstream surface 22 of the arch 14. Lower orifices 15 are also provided so that 'a relatively small part of the cold air flow passing from upstream to downstream with respect to the labyrinth disc can pass below and around this main stiffener 23, between the latter and the upstream surface 19 of the disc 8 of the rotor.
  • Such a cold air flow allows to cool this main stiffener 23 and the downstream surface 22 of the labyrinth disc 12.
  • the two fresh air flows passing through the passages 11 and the lower orifices 15 meet behind the labyrinth disc 10 on the downstream surface 22 of the arch 14 to go back up between the fixing teeth 24. They thus cool the entire rear of this assembly which constitutes the labyrinth disc. They reach the rim of the turbine disk 8 and join the cooling circuits of the blades 21 and the fixing cells of these blades.
  • This main stiffener 23 constitutes the main mechanical holding element of the labyrinth disc 10. It contributes to reducing the internal stiffener 9 and reducing the general dimension of the labyrinth disc 10 and, in particular, of the arch 14. It is noted that the latter may have a slightly less rounded shape but slightly offset towards the downstream side of the labyrinth disc 12 to come almost to tangent with the upstream surface 19 of the disc 8 of the rotor.
  • these can be constituted by fixing teeth 24 placed on the downstream surface 22 of the labyrinth disk 12 and, in particular, on the outer part of the arch 14.
  • fixing teeth 25 of a bayonet locking system in number corresponding to the number of fixing teeth 24 of the labyrinth disc 12.
  • the axial positioning of the labyrinth disk 12 is ensured with respect to the disk 8 of the rotor, by means of the downstream surface 22 of the rim 13 and of the arch 14.
  • ribs 26 are placed on the downstream surface 22 of the arch 14 to stiffen the latter. They bear on the downstream surface 22 of the disc 8 of the rotor and thus constitute axial stops.
  • the labyrinth disk 12 can be fixed by a bolt system 6 in its interior.
  • Radial stops 27 can be provided on the upstream surface 19 of the disc 8 of the rotor, just below the bayonet fixing teeth 25, so as to bear on the external surface of the fixing teeth 24 of the labyrinth disc 12.
  • the stops radials 27 face the fixing teeth 24 only when the part is in the locking position in the bayonet system.
  • part of the radial loads is absorbed by the radial stops 27, a part being absorbed by the main stiffener 23 and a small part being passed on to the bolts 6.
  • FIG. 3 represents a first variant of the labyrinth disk according to the invention. It shows the use of holes 30 placed on the base 31 of the main stiffener 33 which is unique and which, therefore, is a little more elongated, but still placed just below the labyrinth 10.
  • the system of bayonet fixing comes down to a single series of teeth 34 on the labyrinth disc 32, since these act both as fixing teeth by being housed behind the fixing teeth 35 for fixing the bayonet locking system of the disc 38 rotor and also act as radial stops, thanks to their inclined surfaces combined with the corresponding inclined surfaces of the fixing teeth 35 of the disc 38 of the rotor.
  • These fixing teeth 34 of the labyrinth disc 32 are preferably housed in the upper part of ribs 36.
  • the second variant taken up the same holes 30 in the main stiffener 33.
  • the fixing system described in FIG. 2 is the same.
  • the same set of fixing teeth 24 is used there on the labyrinth disc 42, placed in correspondence with fixing teeth 25 on the disc 8 of the rotor to constitute the bayonet system.
  • Radial stops 28 are provided in the outer part of the ribs 26 and placed in correspondence with stops 27 of the disc 8 of the rotor.
  • FIG. 5 shows a third variant, still using the single main stiffener 33, extended to provide for the use of holes 32 on either side of the stiffening disc 52.
  • the radial stops 58 are placed further outside. with respect to the fixing system. They are placed opposite abutment surfaces 59 of the disc 8 of the rotor.
  • the axial fixing is effected by means of a bayonet fixing system at the level of the ribs 56. They use teeth 54 engaging in teeth of the bayonet locking system 55 corresponding to the discs 8 of the rotor.
  • FIG. 6 shows a different shape from the vault 64 of the labyrinth disk 62. Indeed, from its external end 61, this is almost straight, that is to say that its downstream surface 63 is more spaced from the disc 68 of the rotor than in the other embodiments. As a result, the ribs 66 are wider.
  • the number of variants can also be increased by changing the means of fixing the labyrinth disk to the rotor disk.
  • the bolting attachment can be omitted to be replaced by a bayonet style attachment.
  • inside and upstream of the main stiffener 33 there is an axial ring 71, the sectional view of which gives it the shape of a lug, as shown in this FIG. 7.
  • the disc 78 of the rotor also has an axial ring 77 extending substantially parallel to the axis A of the turbojet engine in order to come into contact with the end of the axial ring 71 of the labyrinth disc 72.
  • the fixing means consist, on the labyrinth disk 72, of a series of pins 74 each penetrating into a groove 76 formed on the outer surface 79 of the axial ring 77 of the disk 78 of the rotor.
  • the insertion of these pins 74 can be done by means of longitudinal notches 75 machined on this external surface 79 of the axial ring 77 of the disc 78 of the rotor. Centering is obtained by direct contact of these two parts at the level of the external surface 79 of the axial ring 77 of the disc 78 of the rotor.
  • this assembly which constitutes the labyrinth disk, is less difficult in its design and makes it possible to obtain longer service lives.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
EP97400211A 1996-02-08 1997-01-30 Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor Expired - Lifetime EP0789133B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9601527A FR2744761B1 (fr) 1996-02-08 1996-02-08 Disque labyrinthe avec raidisseur incorpore pour rotor de turbomachine
FR9601527 1996-02-08

Publications (2)

Publication Number Publication Date
EP0789133A1 true EP0789133A1 (de) 1997-08-13
EP0789133B1 EP0789133B1 (de) 2000-03-01

Family

ID=9488969

Family Applications (1)

Application Number Title Priority Date Filing Date
EP97400211A Expired - Lifetime EP0789133B1 (de) 1996-02-08 1997-01-30 Labyrinthträgerscheibe mit einer eingebauten Versteifung für Turbomaschinenrotor

Country Status (5)

Country Link
US (1) US5816776A (de)
EP (1) EP0789133B1 (de)
CA (1) CA2196642C (de)
DE (1) DE69701332T2 (de)
FR (1) FR2744761B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961249A1 (fr) * 2010-06-10 2011-12-16 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
EP2942483A1 (de) * 2014-04-01 2015-11-11 United Technologies Corporation Belüftete bordseitige tangenzialdüse für einen gasturbinenmotor
FR3078363A1 (fr) * 2018-02-23 2019-08-30 Safran Aircraft Engines Anneau mobile d'etancheite

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US5984636A (en) * 1997-12-17 1999-11-16 Pratt & Whitney Canada Inc. Cooling arrangement for turbine rotor
FR2817290B1 (fr) * 2000-11-30 2003-02-21 Snecma Moteurs Flasque de disque aubage de rotor et agencement correspondant
US6464453B2 (en) * 2000-12-04 2002-10-15 General Electric Company Turbine interstage sealing ring
US6761034B2 (en) * 2000-12-08 2004-07-13 General Electroc Company Structural cover for gas turbine engine bolted flanges
US6575703B2 (en) * 2001-07-20 2003-06-10 General Electric Company Turbine disk side plate
FR2831918B1 (fr) 2001-11-08 2004-05-28 Snecma Moteurs Stator pour turbomachine
FR2840351B1 (fr) * 2002-05-30 2005-12-16 Snecma Moteurs Refroidissement du flasque amont d'une turbine a haute pression par un systeme a double injecteur fond de chambre
FR2841591B1 (fr) * 2002-06-27 2006-01-13 Snecma Moteurs Circuits de ventilation de la turbine d'une turbomachine
US6749400B2 (en) * 2002-08-29 2004-06-15 General Electric Company Gas turbine engine disk rim with axially cutback and circumferentially skewed cooling air slots
US6779972B2 (en) * 2002-10-31 2004-08-24 General Electric Company Flowpath sealing and streamlining configuration for a turbine
JP2005009382A (ja) * 2003-06-18 2005-01-13 Ishikawajima Harima Heavy Ind Co Ltd タービンロータ、タービンディスク、及びタービン
US20110150640A1 (en) * 2003-08-21 2011-06-23 Peter Tiemann Labyrinth Seal in a Stationary Gas Turbine
EP1508672A1 (de) * 2003-08-21 2005-02-23 Siemens Aktiengesellschaft Segmentierter Befestigungsring für eine Turbine
GB2426289B (en) * 2005-04-01 2007-07-04 Rolls Royce Plc Cooling system for a gas turbine engine
FR2885167B1 (fr) * 2005-04-29 2007-06-29 Snecma Moteurs Sa Module de turbine pour moteur a turbine a gaz
US7341429B2 (en) * 2005-11-16 2008-03-11 General Electric Company Methods and apparatuses for cooling gas turbine engine rotor assemblies
US8708652B2 (en) * 2007-06-27 2014-04-29 United Technologies Corporation Cover plate for turbine rotor having enclosed pump for cooling air
US8444387B2 (en) * 2009-11-20 2013-05-21 Honeywell International Inc. Seal plates for directing airflow through a turbine section of an engine and turbine sections
FR2961250B1 (fr) * 2010-06-14 2012-07-20 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine a l'aval du cone d'entrainement
US9109457B2 (en) * 2010-09-03 2015-08-18 Siemens Energy, Inc. Axial locking seals for aft removable turbine blade
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8740554B2 (en) 2011-01-11 2014-06-03 United Technologies Corporation Cover plate with interstage seal for a gas turbine engine
US8662845B2 (en) 2011-01-11 2014-03-04 United Technologies Corporation Multi-function heat shield for a gas turbine engine
US8840375B2 (en) 2011-03-21 2014-09-23 United Technologies Corporation Component lock for a gas turbine engine
US9080456B2 (en) * 2012-01-20 2015-07-14 General Electric Company Near flow path seal with axially flexible arms
US8827637B2 (en) 2012-03-23 2014-09-09 Pratt & Whitney Canada Corp. Seal arrangement for gas turbine engines
US20160017755A1 (en) * 2013-01-29 2016-01-21 United Technologies Corporation Common joint for a combustor, diffuser, and tobi of a gas turbine engine
WO2014120135A1 (en) * 2013-01-30 2014-08-07 United Technologies Corporation Double snapped cover plate for rotor disk
EP2818643B1 (de) * 2013-06-27 2018-08-08 MTU Aero Engines GmbH Dichteinrichtung und Strömungsmaschine
US9556737B2 (en) 2013-11-18 2017-01-31 Siemens Energy, Inc. Air separator for gas turbine engine
PL2924237T3 (pl) 2014-03-25 2019-01-31 Industria De Turbo Propulsores S.A. Wirnik turbiny gazowej
US10655480B2 (en) * 2016-01-18 2020-05-19 United Technologies Corporation Mini-disk for gas turbine engine
US10329929B2 (en) * 2016-03-15 2019-06-25 United Technologies Corporation Retaining ring axially loaded against segmented disc surface
DE102017205122A1 (de) * 2017-03-27 2018-09-27 MTU Aero Engines AG Turbomaschinen-Bauteilanordnung
US10280842B2 (en) * 2017-04-10 2019-05-07 United Technologies Corporation Nut with air seal
US20180320522A1 (en) * 2017-05-04 2018-11-08 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10968744B2 (en) 2017-05-04 2021-04-06 Rolls-Royce Corporation Turbine rotor assembly having a retaining collar for a bayonet mount
US10774678B2 (en) 2017-05-04 2020-09-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
US10865646B2 (en) 2017-05-04 2020-12-15 Rolls-Royce Corporation Turbine assembly with auxiliary wheel
EP3495611B1 (de) * 2017-12-06 2020-07-29 Ansaldo Energia Switzerland AG Vorrichtung zur kontrollierten abgabe von kühlluft an turbinenschaufeln in einer gasturbine
EP3564489A1 (de) * 2018-05-03 2019-11-06 Siemens Aktiengesellschaft Rotor mit fliehkraft-optimierten kontaktflächen
CN109489957B (zh) * 2018-12-10 2020-12-15 中国航发四川燃气涡轮研究院 一种用于轮盘试验的带应力分割槽的转接结构
FR3093541B1 (fr) * 2019-03-08 2021-07-16 Safran Aircraft Engines Turbine à gaz pour aéronef à double rotor
CN110805476B (zh) * 2019-10-17 2022-04-12 南京航空航天大学 一种带有容腔封严结构的涡轮盘
US11313240B2 (en) 2020-02-05 2022-04-26 Raytheon Technologies Corporation Rounded radial snap configuration for a gas turbine engine cover plate

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Publication number Priority date Publication date Assignee Title
FR2961249A1 (fr) * 2010-06-10 2011-12-16 Snecma Dispositif de refroidissement des alveoles d'un disque de rotor de turbomachine
EP2942483A1 (de) * 2014-04-01 2015-11-11 United Technologies Corporation Belüftete bordseitige tangenzialdüse für einen gasturbinenmotor
US10697321B2 (en) 2014-04-01 2020-06-30 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
US10920611B2 (en) 2014-04-01 2021-02-16 Raytheon Technologies Corporation Vented tangential on-board injector for a gas turbine engine
FR3078363A1 (fr) * 2018-02-23 2019-08-30 Safran Aircraft Engines Anneau mobile d'etancheite

Also Published As

Publication number Publication date
DE69701332D1 (de) 2000-04-06
FR2744761B1 (fr) 1998-03-13
CA2196642A1 (en) 1997-08-09
EP0789133B1 (de) 2000-03-01
CA2196642C (en) 2005-11-15
US5816776A (en) 1998-10-06
FR2744761A1 (fr) 1997-08-14
DE69701332T2 (de) 2000-07-27

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