EP0214876B1 - Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor - Google Patents

Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor Download PDF

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Publication number
EP0214876B1
EP0214876B1 EP86401519A EP86401519A EP0214876B1 EP 0214876 B1 EP0214876 B1 EP 0214876B1 EP 86401519 A EP86401519 A EP 86401519A EP 86401519 A EP86401519 A EP 86401519A EP 0214876 B1 EP0214876 B1 EP 0214876B1
Authority
EP
European Patent Office
Prior art keywords
disc
labyrinth
rotor
carrying
face
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
Application number
EP86401519A
Other languages
English (en)
French (fr)
Other versions
EP0214876A1 (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
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 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 an assembly of a rotor and a multifunctional labyrinth-bearing disc for a turbomachine, the rotor comprising at least one disc in the rim of which grooves are provided receiving the blade roots, the labyrinth-bearing comprising on its upstream face of the wipers cooperating with complementary means provided on the stator, and on its downstream face of the 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 hold the spouts, 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. Locking in the downstream-upstream direction and fixing the upstream flange are obtained by the downstream flange which has on its inner edge 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.
  • FR-A 2 286 282 describes an impeller rotor for a gas turbine in which a disk carrying the blades also carries a continuous ring having the shape of a cage whose continuous axial ends are connected by bars s' extending axially, interposed between the blade roots, this ring carrying on each side, upstream and downstream, an axial flange carrying sealing rings forming seals of the labyrinth type.
  • 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 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 achieves the 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, kept 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.
  • 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.

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)

Claims (4)

1. Aus einem Rotor und einer Mehrfunktions-Labyrinthträgerscheibe bestehende Baugruppe für Turbomaschinen, deren Rotor folgende Teile umfasst: wenigstens eine Scheibe (2), in deren Außenkranz (3) Nuten (4) zur Aufnahme der Schaufelfüße (5) ausgebildet sind, einen Labyrinthträger mit Dichtungslippen (10, 11, 12) auf seiner stromaufwärtigen Seite, die mit an dem Stator vorgesehenen komplementären Mitteln zusammenwirken, und mit Mitteln (16) auf seiner stromabwärtigen Seite zur Abdichtung gegen die stromaufwärtige Seite der Rotorscheibe (2), Mittel zur Befestigung des Labyrinthträgers sowie Mittel zur axialen Festlegung der Schaufeln, dadurch gekennzeichnet, dass die Labyrinthträgerscheibe aus einer von der Rotorscheibe (2) getrennten radialen Scheibe (13) besteht, die an ihrem Umfang folgende Teile aufweist:
- einen konischen Labyrinthträgerring (14), der stromaufwärts der Rotorscheibe angeordnet ist und an seiner Außenfläche die genannten Dichtungslippen (10, 11, 12) trägt,
- einen in stromabwärtiger Richtung der Rotorscheibe weisenden konischen Kragen (15), der ausgestattet ist mit einem an seiner Peripherie und über seinem stromabwärtigen Rand angeordneten ringförmigen Bund (16), der sich gegen die stromaufwärtige Seite des Außenkranzes des Rotors (2) und Schaufelfüße abstützen kann; sowie mit zur Halterung der Schaufeln dienenden, auf der stromabwärtigen Seite des Kragens axial angeordneten Zähnen (17), deren Zahl der Zahl der Nuten (4) zur Aufnahme der Schaufelfüße entspricht und die an ihrem Ende einen der Peripherie zugewandten radialen Absatz (23) sowie einen Teil der Mittel zur Befestigung der Labyrinthträgerscheibe an der Rotorscheibe aufweisen.
2. Aus einem Rotor und einer Mehrfunktions-Labyrinthträgerscheibe bestehende Baugruppe nach Anspruch 1, dadurch gekennzeichnet, daß die Mittel zur Befestigung der Labyrinthträgerscheibe aus folgenden Teilen bestehen:
- einem Arretiersegment (18), das das einzige Mittel zur Halterung der Labyrinthträgerscheibe darstellt,
- einer in der stromaufwärtigen Seite der Rotorscheibe (2) ausgebildeten ringförmigen radialen Kehle (19), deren Öffnung von der Scheibenachse nach außen weist, und
- einer ringförmigen radialen Kerbe (20), die in dem Endbereich der Zähne (17) der Schaufeln ausgebildet ist und deren Öffnung zur Achse der Rotorscheibe weist, wobei das Arretiersegment (18) teilweise in die Kehle (19) und die Kerbe (10) eingreifen kann.
3. Aus einem Rotor und einer Mehrfunktions-Labyrinthträgerscheibe bestehende Baugruppe nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß die zur Halterung der Schaufeln dienenden Zähne (17) an ihrer zur Achse der Turbomaschine weisenden Seite eine Längsnut (21) sowie radiale Durchgänge (22) aufweisen.
4. Aus einem Rotor und einer Mehrfunktions-Labyrinthträgerscheibe bestehende Baugruppe nach Anspruch 1, dadurch gekennzeichnet, daß die Labyrinthträgerscheibe aus einem einzigen Stück besteht, das durch Gießen und/oder spanabhebende Bearbeitung hergestellt ist.
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 EP0214876A1 (de) 1987-03-18
EP0214876B1 true 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)

Families Citing this family (23)

* 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
FR2663997B1 (fr) * 1990-06-27 1993-12-24 Snecma Dispositif de fixation d'une couronne de revolution sur un disque de turbomachine.
US5302086A (en) * 1992-08-18 1994-04-12 General Electric Company Apparatus for retaining rotor blades
FR2695433B1 (fr) * 1992-09-09 1994-10-21 Snecma Joint annulaire d'étanchéité disposé à une extrémité axiale d'un rotor et recouvrant des brochages d'aubes.
US5281097A (en) * 1992-11-20 1994-01-25 General Electric Company Thermal control damper for turbine rotors
GB2272946A (en) * 1992-11-28 1994-06-01 Rolls Royce Plc Gas turbine engine interstage seal.
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

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CA1209482A (en) * 1983-12-22 1986-08-12 Douglas L. Kisling Two stage rotor assembly with improved coolant flow

Also Published As

Publication number Publication date
FR2586061A1 (fr) 1987-02-13
EP0214876A1 (de) 1987-03-18
US4668167A (en) 1987-05-26
FR2586061B1 (fr) 1989-06-09
DE3662421D1 (en) 1989-04-20

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