EP0214876A1 - Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor - Google Patents

Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor Download PDF

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Publication number
EP0214876A1
EP0214876A1 EP86401519A EP86401519A EP0214876A1 EP 0214876 A1 EP0214876 A1 EP 0214876A1 EP 86401519 A EP86401519 A EP 86401519A EP 86401519 A EP86401519 A EP 86401519A EP 0214876 A1 EP0214876 A1 EP 0214876A1
Authority
EP
European Patent Office
Prior art keywords
disc
labyrinth
rotor
radial
downstream
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
EP86401519A
Other languages
English (en)
French (fr)
Other versions
EP0214876B1 (de
Inventor
Théophile François Le Maout
Marc Roger Marchi
André Françis Ollivier
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 EP0214876A1 publication Critical patent/EP0214876A1/de
Application granted granted Critical
Publication of EP0214876B1 publication Critical patent/EP0214876B1/de
Expired 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
    • 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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades 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
    • F01D5/30—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 a multifunctional labyrinth-bearing disc for a turbomachine rotor, the rotor comprising at least one disc in the rim of which grooves receiving the blade roots are provided, the labyrinth-bearing comprising on its upstream face wipers cooperating with additional means provided on the stator, and on its downstream face sealing means with the upstream face of the rotor disc, means for fixing the labyrinth holder and means for axially holding the blades.
  • French Patent No. 2 324 873 describes a device comprising two flanges: an upstream and a downstream, arranged on either side of the rotor disc and formed of segments.
  • the upstream flange carries on its radial upstream face wipers ensuring the sealing of the stage with the stator while the peripheral edge of its downstream face carries means ensuring the sealing with the radial upstream face of the rim and the feet d 'dawn.
  • This downstream face carries towards its inner edge an axial flange in which are provided housings intended to maintain beaks, formed at the end of the blade roots, when all the segments are mounted.
  • the flange and therefore the upstream flange ensures the axial locking of the blades in the upstream-downstream direction.
  • the locking in the downstream-upstream direction and the fixing of the upstream flange are obtained by the downstream flange which has on its inner side and on its upstream face, bosses which are housed in a groove in the rim and which, by rotation of the flange , are placed behind a heel provided at the end of the blade root.
  • the flange is then locked in rotation by pins held by dowels immobilized by a sealing element welded to the flange.
  • the invention aims to provide a device consisting of two parts, the labyrinth-bearing disc and a stop segment capable of ensuring both the seal with respect to the rotor, the sealed supply of the blades with cooling air and the axial retention of the blades.
  • the labyrinth-bearing disc according to the invention can be removed in that it consists of a radial disc comprising at its periphery: - a conical labyrinth ring, placed upstream of the disc, and carrying on its outer surface the wipers; - A conical flange directed downstream of the disc provided with an annular bearing disposed at its periphery and on its downstream edge, capable of pressing against the upstream face of the rim of the rotor and of the blade roots; and blade retaining teeth arranged axially on the downstream face of the flange in a number equal to that of the grooves receiving the blade roots, and comprising at their end a radial heel directed towards the periphery and part of the means for fixing the disc labyrinte to the rotor disc.
  • the means for fixing the labyrinth-bearing disc consist of a stop segment, of an annular radial groove provided in the downstream face of the rotor disc and the opening of which is directed outward relative to the disc axis, and a radial annular notch provided at the end of the retaining teeth and the opening of which is directed towards the axis of the rotor disc, the stop segment constituting the only means of retaining the labyrinth-bearing disc , being capable of partially engaging in the groove and the notch.
  • FIG. 1 represents a simplified partial view in section of a turbine stage of a turbomachine.
  • the hollow shaft 1 of the turbomachine rotates the rotor disk 2 which is attached to it.
  • This disc comprises, as known, a rim 3 which is crossed axially by grooves 4 in fir (visible in FIG. 2), which receive and hold the feet 5 of the blades 6.
  • the blades are separated of the foot by a platform 7 which provides aerodynamic continuity of the annular channel in which the rotor blade turns.
  • the blades 6 of the rotor 2 receive the air flow directed by the stator vane, placed upstream, consisting of blades 8, adjustable or not, held at the periphery of the casing (not shown) of the turbine.
  • stator vanes 8 carry sealing means 9 consisting of one or more cylindrical rings (three according to the example) cooperating with the wipers 10, 11, 12 carried by a labyrinth-bearing disc 13 secured to the turbine engine rotor.
  • the labyrinth-bearing disc is - a disc 13; - A labyrinth-bearing ring 14, conical, directed upstream of the disc 13 relative to the direction of the air flow and comprising on its outer surface the wipers 10, 11, 12 forming part of a labyrinth seal; - a conical flange 15, directed downstream of the disc 13 relative to the direction of the air flow, provided at its periphery and on its downstream edge, with an annular bearing 16, intended to bear directly or indirectly by means of a seal on the upstream face of the rim of the rotor 2 and of the blade roots 5.
  • This flange still carries on its downstream surface and in a circle, blades retaining teeth, 17, 172, 173 ... axial, in number equal to that of the grooves 4 receiving the blade roots, arranged so as to be able to be housed in each of the grooves between the bottom of the groove and that of the blade root, constituting the means for axially holding the blades; -
  • a stop segment 18 partially housed in an annular radial groove 19 of the rotor disc 2, open towards the outside relative to the axis of the disc, and partially in an annular notch 20, radial, provided at the end retaining teeth 17, 172, 173 ... and on their face directed towards the axis of the turbomachine and open towards this axis.
  • the stop segment 18 is in the form of a split ring having a certain elasticity.
  • teeth these have on their face directed towards the axis of the turbomachine, a longitudinal groove 21 (FIG. 3) intended to bring the cooling air to the blades by radial passages 22.
  • the free end of the teeth carries, on their face directed towards the periphery, a radial heel 23 intended for retaining the blades.
  • the labyrinth-bearing disc according to the invention is obtained in one piece by molding and / or machining.
  • the above labyrinth disk mounting method described is as follows: - The rotor disc being placed flat on a suitable support, the stop segment 18 being in place in the groove 19, the labyrinth-bearing disc is presented, so that the teeth 17 engage slightly by their heel 23 in the grooves 4 of the rotor rim; - The blade roots 5 are placed on the teeth 17 between the bearing surface 16 and the upstream face of the radial heel 23; - the labyrinth-bearing disc is then pushed so as to simultaneously penetrate all of the blade roots into the grooves until the stop segment, previously compressed by the heels of the teeth, comes to be partially housed in the notches annular 20 of said heels. Conversely, to disassemble the labyrinth-bearing disc, the stop segment 19 must be retracted into the groove 19 of the disc 2.
  • the labyrinth carrier disc performs the following functions: the blades are locked: the blades are held axially upstream by pressing on the bearing surface 16 and downstream by pressing on the upstream face of the heel 23 of the tooth 17; the locking of the labyrinth-bearing disc: the disc is locked axially, by the stop segment 18 inserted partially in the rotor disc and partially in the teeth 17; - the cooling air supply to the blades: the cooling air enters the groove 21 and from there by radial passages in the internal cooling channels of the blades; - Damping: in operation, the span 16 of the labyrinth carrier presses on the upstream face of the blade roots and dampens the vibrations of the blades.
  • a flexible O-ring, housed in a groove in the bearing surface 16 possibly takes up the manufacturing tolerances of the blade roots.

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)
EP86401519A 1985-08-08 1986-07-09 Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor Expired EP0214876B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8512142 1985-08-08
FR8512142A FR2586061B1 (fr) 1985-08-08 1985-08-08 Disque porte labyrinthe multifonction pour rotor de turbomachine

Publications (2)

Publication Number Publication Date
EP0214876A1 true EP0214876A1 (de) 1987-03-18
EP0214876B1 EP0214876B1 (de) 1989-03-15

Family

ID=9322104

Family Applications (1)

Application Number Title Priority Date Filing Date
EP86401519A Expired EP0214876B1 (de) 1985-08-08 1986-07-09 Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor

Country Status (4)

Country Link
US (1) US4668167A (de)
EP (1) EP0214876B1 (de)
DE (1) DE3662421D1 (de)
FR (1) FR2586061B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0463955A1 (de) * 1990-06-27 1992-01-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Befestigung eines Kranzes an einem Turbinenlaufrad
GB2270544A (en) * 1992-09-09 1994-03-16 Snecma Annular seal for a bladed rotor.
GB2272946A (en) * 1992-11-28 1994-06-01 Rolls Royce Plc Gas turbine engine interstage seal.

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4813848A (en) * 1987-10-14 1989-03-21 United Technologies Corporation Turbine rotor disk and blade assembly
US5302086A (en) * 1992-08-18 1994-04-12 General Electric Company Apparatus for retaining rotor blades
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
US5725353A (en) * 1996-12-04 1998-03-10 United Technologies Corporation Turbine engine rotor disk
US6077035A (en) * 1998-03-27 2000-06-20 Pratt & Whitney Canada Corp. Deflector for controlling entry of cooling air leakage into the gaspath of a gas turbine engine
GB2405183A (en) * 2003-08-21 2005-02-23 Rolls Royce Plc Ring and channel arrangement for joining components
FR2875270B1 (fr) * 2004-09-10 2006-12-01 Snecma Moteurs Sa Retenue des clavettes de centrage des anneaux sous aubes de stator a calage variable d'un moteur a turbine a gaz
US7520718B2 (en) * 2005-07-18 2009-04-21 Siemens Energy, Inc. Seal and locking plate for turbine rotor assembly between turbine blade and turbine vane
DE102009007664A1 (de) * 2009-02-05 2010-08-12 Mtu Aero Engines Gmbh Abdichtvorrichtung an dem Schaufelschaft einer Rotorstufe einer axialen Strömungsmaschine
US8511976B2 (en) * 2010-08-02 2013-08-20 General Electric Company Turbine seal system
FR2963806B1 (fr) * 2010-08-10 2013-05-03 Snecma Dispositif de blocage d'un pied d'une aube de rotor
GB201417038D0 (en) 2014-09-26 2014-11-12 Rolls Royce Plc A bladed rotor arrangement
US9664058B2 (en) * 2014-12-31 2017-05-30 General Electric Company Flowpath boundary and rotor assemblies in gas turbines
EP3048256A1 (de) * 2015-01-20 2016-07-27 Siemens Aktiengesellschaft Rotor umfassend eine Turbinenschaufel mit einer Sicherungseinrichtung
US10975714B2 (en) 2018-11-22 2021-04-13 Pratt & Whitney Canada Corp. Rotor assembly with blade sealing tab
CN110375948B (zh) * 2019-08-16 2024-02-23 中国航空工业集团公司沈阳空气动力研究所 一种用于模型-支撑间缝隙密封装置
CN112594068B (zh) * 2021-01-21 2021-05-28 中国航发上海商用航空发动机制造有限责任公司 航空发动机的盘鼓密封机构和航空发动机
CN115653698B (zh) * 2022-10-19 2025-09-26 西北工业大学 一种斜篦齿涡轮级间封严结构及燃气轮机
FR3158535B1 (fr) * 2024-01-24 2025-12-05 Safran Aircraft Engines Plaquette a multi cales axiales pour rotor de turbomachine, ensemble de rotor et turbomachine associes

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2164197A5 (de) * 1971-12-06 1973-07-27 Gen Electric
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
FR2286282A1 (fr) * 1974-09-28 1976-04-23 Rolls Royce Perfectionnements aux rotors a aubes
FR2324873A1 (fr) * 1975-09-17 1977-04-15 Snecma Perfectionnements aux flasques de rotors de turbomachines
FR2413542A1 (fr) * 1977-12-28 1979-07-27 Gen Electric Amortisseur d'aube de turbomachine
GB2151715A (en) * 1983-12-22 1985-07-24 United Technologies Corp Two stage rotor assembly with improved coolant flow

Family Cites Families (13)

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US3034298A (en) * 1958-06-12 1962-05-15 Gen Motors Corp Turbine cooling system
US3644058A (en) * 1970-05-18 1972-02-22 Westinghouse Electric Corp Axial positioner and seal for turbine blades
GB1318654A (en) * 1970-12-05 1973-05-31 Secr Defence Bladed rotors
US3748060A (en) * 1971-09-14 1973-07-24 Westinghouse Electric Corp Sideplate for turbine blade
BE794573A (fr) * 1972-02-02 1973-05-16 Gen Electric Dispositif de fixation d'aubes
US3832092A (en) * 1973-10-19 1974-08-27 Gen Electric Device for locking turbomachinery blades
FR2345605A1 (fr) * 1976-03-25 1977-10-21 Snecma Dispositif de retenue pour aubes de soufflantes
US4111603A (en) * 1976-05-17 1978-09-05 Westinghouse Electric Corp. Ceramic rotor blade assembly for a gas turbine engine
US4093399A (en) * 1976-12-01 1978-06-06 Electric Power Research Institute, Inc. Turbine rotor with ceramic blades
US4142836A (en) * 1976-12-27 1979-03-06 Electric Power Research Institute, Inc. Multiple-piece ceramic turbine blade
US4221542A (en) * 1977-12-27 1980-09-09 General Electric Company Segmented blade retainer
US4171930A (en) * 1977-12-28 1979-10-23 General Electric Company U-clip for boltless blade retainer
US4505640A (en) * 1983-12-13 1985-03-19 United Technologies Corporation Seal means for a blade attachment slot of a rotor assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2164197A5 (de) * 1971-12-06 1973-07-27 Gen Electric
US3887298A (en) * 1974-05-30 1975-06-03 United Aircraft Corp Apparatus for sealing turbine blade damper cavities
FR2286282A1 (fr) * 1974-09-28 1976-04-23 Rolls Royce Perfectionnements aux rotors a aubes
FR2324873A1 (fr) * 1975-09-17 1977-04-15 Snecma Perfectionnements aux flasques de rotors de turbomachines
FR2413542A1 (fr) * 1977-12-28 1979-07-27 Gen Electric Amortisseur d'aube de turbomachine
GB2151715A (en) * 1983-12-22 1985-07-24 United Technologies Corp Two stage rotor assembly with improved coolant flow

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0463955A1 (de) * 1990-06-27 1992-01-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Befestigung eines Kranzes an einem Turbinenlaufrad
FR2663997A1 (fr) * 1990-06-27 1992-01-03 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US5173024A (en) * 1990-06-27 1992-12-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Fixing arrangement for mounting an annular member on a disk of a turboshaft engine
GB2270544A (en) * 1992-09-09 1994-03-16 Snecma Annular seal for a bladed rotor.
GB2270544B (en) * 1992-09-09 1995-12-13 Snecma Annular seal for a rotor having dovetail grooves which receive the blade roots
GB2272946A (en) * 1992-11-28 1994-06-01 Rolls Royce Plc Gas turbine engine interstage seal.

Also Published As

Publication number Publication date
EP0214876B1 (de) 1989-03-15
FR2586061A1 (fr) 1987-02-13
US4668167A (en) 1987-05-26
FR2586061B1 (fr) 1989-06-09
DE3662421D1 (en) 1989-04-20

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