EP0259221A1 - Labyrinthspielanpassung für eine Turbomaschine - Google Patents

Labyrinthspielanpassung für eine Turbomaschine Download PDF

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Publication number
EP0259221A1
EP0259221A1 EP87401931A EP87401931A EP0259221A1 EP 0259221 A1 EP0259221 A1 EP 0259221A1 EP 87401931 A EP87401931 A EP 87401931A EP 87401931 A EP87401931 A EP 87401931A EP 0259221 A1 EP0259221 A1 EP 0259221A1
Authority
EP
European Patent Office
Prior art keywords
ring
turbomachine
stator
internal
pivot
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
EP87401931A
Other languages
English (en)
French (fr)
Other versions
EP0259221B1 (de
Inventor
Philippe Jean Lefebvre
Gérard Stangalini
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 EP0259221A1 publication Critical patent/EP0259221A1/de
Application granted granted Critical
Publication of EP0259221B1 publication Critical patent/EP0259221B1/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
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the present invention relates to a turbomachine comprising a device for adjusting the clearances of a labyrinth seal which seals between a rotor and a stator, this device also making it possible to obtain alignment of the main stream of gases.
  • the invention also relates to a method of applying the real-time adjustment of the seal clearances.
  • the labyrinth seal used consists of two parts: wipers or teeth carried by a rotor disc and a sealing ring.
  • This sealing ring is radially integral with the internal side of the blades constituting a stator stage and carries a so-called “abradable” layer capable of cooperating with the wipers and of being worn on contact in order to ensure in all cases of operation the tightness without risking harmful interference.
  • FR-A-2 395 403 describes such a turbine ring support device in which the radial position of the segments constituting the ring is adjusted by means of a mechanism comprising an axis- support mounted on eccentric and driven in rotation by a ring gear which moves according to the variations of the engine operating parameters.
  • This device applied to a fixed stator ring cannot however be used for stator vanes which, moreover, require in operation a setting of the timing to vary the inclination of the vanes, for example by means of a swiveling pivot.
  • the complexity of the device comprising the use of an eccentric can lead to drawbacks.
  • the invention aims to avoid the drawbacks of known solutions and makes it possible to solve the problems mentioned above.
  • the turbomachine according to the invention comprising a device for adjusting the clearances of a labyrinth seal, the fixed part is carried by the radially internal ring of a stator stage consisting of vanes each provided with a pivot at each end cooperating one with said internal ring and the other on the radially external side with a casing is characterized in that first means secure said internal pivot and the inner ring and second means secure said external pivot and a bushing and in that said bush cooperates with a boss of the casing by means of threads and is secured to a lever ordered.
  • control lever is connected to a control and synchronization ring associated with a computer which integrates the various operating parameters of the turbomachine.
  • a stator stage 1 of a turbomachine is shown in the single figure. It consists of vanes 1 a , the blade of which carries at each end, on the one hand a radially external pivot 2 and on the other hand, a radially internal pivot 3.
  • the internal pivots 3 of vanes are housed through of sockets 4 of the self-lubricating type in semi-cylindrical impressions of two half-rings 5 and 6, each consisting of segments.
  • the half-rings 5 and 6 are joined by a circular rail 7 made up of two segments.
  • a layer 8 of a material wear and sealing said "abradable”.
  • a circlip or any other equivalent means radially secures each internal pivot 3 and the rings 5 and 6.
  • the external pivot pivots are housed in sockets 9 to which they are radially secured.
  • Each socket 9 has at its radially external end a circular plate 10 whose periphery carries a flange 11 in the direction of the axis of the machine.
  • the internal face of said flange 11 carries a thread 12.
  • the sockets 9 are mounted in bosses 13 disposed peripherally, to the right of the blades, outside a casing 14.
  • the thread 12 of the socket 9 cooperates with a thread 15 of boss 13.
  • the stator stage 1 is inserted between two rotor stages each consisting respectively of movable vanes 1b and 1c carried by discs 16 and 17.
  • the disc 17 also carries the rotating part of the seal cooperating with the layer 8 abradable and consisting of wipers or teeth 18.
  • Each half-ring 5 and 6 respectively has a lateral rim 19 and 20 at its radially external part. These flanges 19 and 20 cooperate with the edges of the platforms of the corresponding rotor blades 1b and 1c so as to establish an aerodynamic continuity of the internal wall of the gas stream.
  • the circular plates 10 of the sockets 9 each carry a circular row of threaded holes 21 for fixing on the socket 9 a control lever 22.
  • the other end of the levers 22 is articulated on a control and synchronization ring 23.
  • one of the blades 1 of the variable valve timing control device 1 of the stator stage may be added.
  • the end of the external pivot 2, at beyond the sleeve 9 has a thread on which one end of a control lever 24 and a fixing nut 25 fits.
  • the lever 24 is connected to a control ring 26.
  • the device which has just been described makes it possible to ensure an adjustment of the clearance of the cold labyrinth seal to the desired value without being dependent on the various manufacturing tolerances and by making an optimized choice.
  • a radial displacement is obtained which makes it possible to adjust the clearance j between the tips of the wipers 18 and the cooperating surface of the abradable layer 8 at the desired value, at the labyrinth seal.
  • a computer 27 capable of producing an output signal which, by a link with the control ring 23, is capable of causing any displacement of said ring.
  • the computer 27 is connected to various sensors which are also used for checks and controls of the turbomachine in operation and placed in the appropriate places.
  • a continuous acquisition of the thermodynamic operating parameters of the turbomachine is thus carried out and which are representative of its thermal state. These parameters include in particular the speed or speed of rotation, the temperature and pressure at different levels of the machine, in particular at the inlet and at the outlet of the compressor.
  • the computer 27 performs various calculations and in particular: - the calculation of the mass temperature of the rotor and the stator concerned, - the calculation of the radial displacements of the rotor and the stator by cumulating the displacements according to their mechanical or thermal origin, - comparison of the resulting game to an objective game, - The calculation of the movement of the control ring 23 relative to a cold established position.
  • Said output signal from said computer 27 is thus produced and acts on the control ring 23.
  • the computer 27 repeats the various operations described above every second and the real-time adjustment of the games of the stator seal and the corresponding displacements of the internal stator ring are thus obtained in order to obtain alignment at all times. correct internal wall elements of the gas circulation stream.

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)
EP87401931A 1986-09-03 1987-08-26 Labyrinthspielanpassung für eine Turbomaschine Expired - Lifetime EP0259221B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8612358 1986-09-03
FR8612358A FR2603340B1 (fr) 1986-09-03 1986-09-03 Turbomachine comportant un dispositif d'ajustement des jeux d'un joint a labyrinthe entre rotor et stator et de l'alignement de veine des gaz et methode d'application

Publications (2)

Publication Number Publication Date
EP0259221A1 true EP0259221A1 (de) 1988-03-09
EP0259221B1 EP0259221B1 (de) 1990-03-07

Family

ID=9338658

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401931A Expired - Lifetime EP0259221B1 (de) 1986-09-03 1987-08-26 Labyrinthspielanpassung für eine Turbomaschine

Country Status (4)

Country Link
US (1) US4773817A (de)
EP (1) EP0259221B1 (de)
DE (1) DE3761834D1 (de)
FR (1) FR2603340B1 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0546935A1 (de) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator zur Einführung von Luft in das Innere einer Turbomaschine und Verfahren zum Montieren einer Schaufel dieses Stators
WO2010003405A1 (de) * 2008-07-10 2010-01-14 Mtu Aero Engines Gmbh Strömungsmaschine
FR2994453A1 (fr) * 2012-08-08 2014-02-14 Snecma Ensemble a faible usure pour couronne aubagee de stator de turbomachine d'aeronef
EP2806107A1 (de) * 2013-05-22 2014-11-26 MTU Aero Engines GmbH Geteilter Innenring
US11280212B2 (en) * 2019-01-24 2022-03-22 MTU Aero Engines AG Guide vane cascade for a turbomachine

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5096375A (en) * 1989-09-08 1992-03-17 General Electric Company Radial adjustment mechanism for blade tip clearance control apparatus
US5104287A (en) * 1989-09-08 1992-04-14 General Electric Company Blade tip clearance control apparatus for a gas turbine engine
US5018942A (en) * 1989-09-08 1991-05-28 General Electric Company Mechanical blade tip clearance control apparatus for a gas turbine engine
US4995786A (en) * 1989-09-28 1991-02-26 United Technologies Corporation Dual variable camber compressor stator vane
US4990056A (en) * 1989-11-16 1991-02-05 General Motors Corporation Stator vane stage in axial flow compressor
US5054997A (en) * 1989-11-22 1991-10-08 General Electric Company Blade tip clearance control apparatus using bellcrank mechanism
US5056988A (en) * 1990-02-12 1991-10-15 General Electric Company Blade tip clearance control apparatus using shroud segment position modulation
US5049033A (en) * 1990-02-20 1991-09-17 General Electric Company Blade tip clearance control apparatus using cam-actuated shroud segment positioning mechanism
US5228828A (en) * 1991-02-15 1993-07-20 General Electric Company Gas turbine engine clearance control apparatus
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
FR2691749B1 (fr) * 1992-05-27 1994-07-22 Snecma Dispositif d'etancheite entre des etages d'aubes et un tambour tournant notamment pour eviter les fuites autour des etages d'aubes de redresseur .
FR2696500B1 (fr) * 1992-10-07 1994-11-25 Snecma Turbomachine équipée de moyens de réglage du jeu entre les redresseurs et le rotor d'un compresseur.
US6588764B2 (en) 2001-11-20 2003-07-08 Dresser-Rand Company Segmented labyrinth seal assembly and method
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
DE102005040574A1 (de) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Spaltkontrollvorrichtung für eine Gasturbine
US7552893B2 (en) * 2005-09-28 2009-06-30 21St Century Airship Technologies Inc. Airship & method of operation
US7604455B2 (en) * 2006-08-15 2009-10-20 Siemens Energy, Inc. Rotor disc assembly with abrasive insert
US8967951B2 (en) 2012-01-10 2015-03-03 General Electric Company Turbine assembly and method for supporting turbine components
US10316684B2 (en) 2013-04-12 2019-06-11 United Technologies Corporation Rapid response clearance control system for gas turbine engine
US9970315B2 (en) * 2015-02-12 2018-05-15 Hamilton Sundstrand Corporation Movable vane control system
FR3033007B1 (fr) * 2015-02-19 2018-07-13 Safran Aircraft Engines Dispositif pour le reglage individuel d'une pluralite d'aubes radiales fixes a calage variable dans une turbomachine
ITUB20155442A1 (it) * 2015-11-11 2017-05-11 Ge Avio Srl Stadio di un motore a turbina a gas provvisto di una tenuta a labirinto
BE1024523B1 (fr) * 2016-08-30 2018-03-29 Safran Aero Boosters S.A. Stator a aubes ajustables pour compresseur de turbomachine axiale
FR3089577B1 (fr) * 2018-12-10 2021-04-02 Safran Aircraft Engines Compresseur de turbomachine comprenant des aubes statoriques à calage variable et procédé de déplacement desdites aubes
CN110005474A (zh) * 2019-04-18 2019-07-12 中国航发沈阳发动机研究所 一种静子组件及具有其的航空发动机
FR3109959B1 (fr) * 2020-05-06 2022-04-22 Safran Helicopter Engines Compresseur de turbomachine comportant une paroi fixe pourvue d’un traitement de forme
CN112228386B (zh) * 2020-12-14 2021-03-16 中国航发上海商用航空发动机制造有限责任公司 压气机和航空发动机
US11965422B2 (en) * 2022-08-02 2024-04-23 Pratt & Whitney Canada Corp. Variable guide vane assembly for gas turbine engine

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB629770A (en) * 1947-11-21 1949-09-28 Napier & Son Ltd Improvements in or relating to sealing rings for turbines
CH306452A (de) * 1951-04-30 1955-04-15 Nat Research Council Turbomaschine mit verstellbaren Leitschaufeln.
CH350506A (fr) * 1957-04-04 1960-11-30 Napier & Son Ltd Stator de turbomachine
US2972441A (en) * 1957-05-14 1961-02-21 Gen Motors Corp Variable blade system
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
GB1112058A (en) * 1966-04-06 1968-05-01 Gen Motors Corp Variable-configuration turbo machine blades
US3850544A (en) * 1973-11-02 1974-11-26 Gen Electric Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades
US4135362A (en) * 1976-02-09 1979-01-23 Westinghouse Electric Corp. Variable vane and flowpath support assembly for a gas turbine
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
EP0146449A1 (de) * 1983-12-07 1985-06-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3019035A (en) * 1957-12-17 1962-01-30 Orenda Engines Ltd Mounting mechanism for labyrinth seal disc
US3039737A (en) * 1959-04-13 1962-06-19 Int Harvester Co Device for controlling clearance between rotor and shroud of a turbine
GB1149326A (en) * 1968-01-18 1969-04-23 Rolls Royce Sealing device
GB1277212A (en) * 1968-09-26 1972-06-07 Rolls Royce A sealing device
US3558237A (en) * 1969-06-25 1971-01-26 Gen Motors Corp Variable turbine nozzles
US4127357A (en) * 1977-06-24 1978-11-28 General Electric Company Variable shroud for a turbomachine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB629770A (en) * 1947-11-21 1949-09-28 Napier & Son Ltd Improvements in or relating to sealing rings for turbines
CH306452A (de) * 1951-04-30 1955-04-15 Nat Research Council Turbomaschine mit verstellbaren Leitschaufeln.
CH350506A (fr) * 1957-04-04 1960-11-30 Napier & Son Ltd Stator de turbomachine
US2972441A (en) * 1957-05-14 1961-02-21 Gen Motors Corp Variable blade system
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
GB1112058A (en) * 1966-04-06 1968-05-01 Gen Motors Corp Variable-configuration turbo machine blades
US3850544A (en) * 1973-11-02 1974-11-26 Gen Electric Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades
US4135362A (en) * 1976-02-09 1979-01-23 Westinghouse Electric Corp. Variable vane and flowpath support assembly for a gas turbine
US4395195A (en) * 1980-05-16 1983-07-26 United Technologies Corporation Shroud ring for use in a gas turbine engine
EP0146449A1 (de) * 1983-12-07 1985-06-26 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0546935A1 (de) * 1991-12-11 1993-06-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Stator zur Einführung von Luft in das Innere einer Turbomaschine und Verfahren zum Montieren einer Schaufel dieses Stators
FR2685033A1 (fr) * 1991-12-11 1993-06-18 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
US5328327A (en) * 1991-12-11 1994-07-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator for directing the inlet of air inside a turbo-engine and method for mounting a vane of said stator
WO2010003405A1 (de) * 2008-07-10 2010-01-14 Mtu Aero Engines Gmbh Strömungsmaschine
FR2994453A1 (fr) * 2012-08-08 2014-02-14 Snecma Ensemble a faible usure pour couronne aubagee de stator de turbomachine d'aeronef
EP2806107A1 (de) * 2013-05-22 2014-11-26 MTU Aero Engines GmbH Geteilter Innenring
US10066668B2 (en) 2013-05-22 2018-09-04 MTU Aero Engines AG Split inner ring
US11280212B2 (en) * 2019-01-24 2022-03-22 MTU Aero Engines AG Guide vane cascade for a turbomachine

Also Published As

Publication number Publication date
FR2603340A1 (fr) 1988-03-04
EP0259221B1 (de) 1990-03-07
US4773817A (en) 1988-09-27
DE3761834D1 (de) 1990-04-12
FR2603340B1 (fr) 1988-11-04

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