EP0146449A1 - Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln - Google Patents

Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln Download PDF

Info

Publication number
EP0146449A1
EP0146449A1 EP84402381A EP84402381A EP0146449A1 EP 0146449 A1 EP0146449 A1 EP 0146449A1 EP 84402381 A EP84402381 A EP 84402381A EP 84402381 A EP84402381 A EP 84402381A EP 0146449 A1 EP0146449 A1 EP 0146449A1
Authority
EP
European Patent Office
Prior art keywords
ring
sockets
fins
pivot
sectors
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
EP84402381A
Other languages
English (en)
French (fr)
Other versions
EP0146449B1 (de
Inventor
Jacky Naudet
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 EP0146449A1 publication Critical patent/EP0146449A1/de
Application granted granted Critical
Publication of EP0146449B1 publication Critical patent/EP0146449B1/de
Expired legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Definitions

  • the invention relates to stators with blades with variable setting of compressors.
  • the stators of this type consist of fins mounted with possibilities of rotation about their longitudinal axis in the compressor casing, their pitch angle relative to the axis of the motor being controlled by a mechanism external to the casing constituted for example by 'a synchronism ring whose movement is transmitted to the head pivots of the fins by means of rods.
  • these fins are generally connected together by an inner ring divided into a plurality of sectors, the upper face of which defines the internal wall of the vein and which support sealing means such as that a seal cooperating with the wipers of a labyrinth seal integral with the rotor in order to limit the internal leakage rates between the downstream and the upstream of the stator stage.
  • the invention relates in particular to the foot connection point of the internal fin-ring.
  • This connection is made by means of a pivot of feet movable in a bearing bush housed in a radial bore of the ring; in order to preserve the free expansion of the ring in operation, it has a certain freedom of sliding along the pivots of the fin feet.
  • the quality of the games between wipers and abradable is determining for the output and the performance of the machine.
  • the radial positioning and the rigidity of the ring are ensured by the radiating arrangement of the fins.
  • the clearances are thus determined with precision.
  • the fins can show, during assembly, a slope in a plane transverse to the axis of the engine, more or less marked; moreover, the play between pivot and bushing is not zero; this leads to a certain dispersion of the radial position of each sector which is not compensated for when these sectors are joined by the seal-wear and wear carrier rails since the rigidity of the assembly is insufficient.
  • the ring may have circularity and centering defects with respect to the rotor.
  • the extreme positions of the ring sectors are difficult to estimate; in the absence of a stop, in particular between the platform of the fins and the ring sectors, the lower corners of the fins can come into contact with the wall of the ring with the consequence of possible deterioration of the fins when they are controlled for travel around of their axis by the control system.
  • a first improvement consisted in reducing the number of sectors constituting the ring and the rail in order to limit the effects thereof due to the fractionation and in introducing at the head of each fin under the control lever a shim limiting the radial position of the 'fin, the thickness of this wedge being determined according to the residual clearance of the attachment point. Finally, by having a spacer acting as a stop between the foot pivot and the rail, it is possible to limit the variations in the radial position of the sectors.
  • US Pat. No. 3,079,128 is known in which the pivot of the feet ends in a thread, so as to radially block the ring sector between a nut tightened on the pivot and the platform of the fin.
  • Such an embodiment has the disadvantage of not lending itself to % adjustment in position of the ring sector requiring the resumption in place, by machining, of the seal and wear; moreover, the ring does not have any freedom of sliding making it possible to absorb the differential expansions in operation.
  • Patent GB 749 577 describes an inner ring assembly of the stator with the possibility of adjustment; the fins are fixed to the ring by means of a bolt mounted eccentrically in an axial bore of the feet of the fin via a sleeve with eccentric internal and external axes. It is therefore possible, by this means, to adjust the position of the ring relative to the fins and to the rotor; unfortunately, such a system cannot be applied to a stator whose fins are of variable setting.
  • adjustment means are distributed over each ring sector making it possible to position them radially.
  • These means are constituted by pivot bushings provided with an external thread cooperating with a complementary tapping of their housing in the ring sector, so that the bushings being in abutment against the lower edge of the platform of the fins, a displacement radial sector is obtained by rotation of the sockets in their housing.
  • a locking means is provided to avoid any untimely rotation once the adjustment has been made.
  • this locking means is constituted by a radial and circumferential flange secured to the outer face of the seal and wear seal carrier rail, abutting against one of the faces of the prismatic base from the socket.
  • FIG. 1 there is shown in axial section a portion of the compressor of a gas turbine engine.
  • a stator stage separates two stages of movable vanes 3 mounted on a drum-shaped rotor.
  • the stator is formed of a ring of fins 2 extending radially from the casing 1 on which they are mounted to rotate about their longitudinal axis by means of a head pivot 4 rotating in a bearing of the casing 1, with the interposition of a socket 22.
  • This pivot 4 is connected to a timing control mechanism, not shown.
  • the fins are provided with a pivot of feet 5 movable in a socket 6 fixed in a radial bore of the ring sector 7.
  • the edges of the rail 8 are curved in the form of hooks and engage with two lateral flanges of the ring.
  • This rail 8 serves as a support for a material forming a seal and wear seal 9 which cooperates in known manner, with the wipers 10 of the labyrinth seal integral with the rotor, to limit leaks due to the difference in pressures prevailing on the part and on the other side of the stator stage.
  • the radial position of the sectored ring 7 cannot be determined precisely because of the manufacturing and mounting tolerances; in operation, the ring sectors can slide along the pivots modifying the clearance between the seal and wear and labyrinth seal on the one hand, the clearance between the inner edges of the fins and the wall of the vein on the other hand; when the latter clearance becomes zero, the operation of the timing control of the fins is impeded, causing the latter to deteriorate.
  • the pivot 5 of the fin 2 pivots in a bush 12 made of a self-lubricating material such as graphite; this bushing is itself supported by a second bushing 14 provided with an external thread cooperating with a complementary tapping of its housing in the ring sector 7.
  • Panes 15 are cut at the widened base of the bushing 14 which has in this way a cross section of polygonal shape for example hexagonal ( Figure 4) and which opens into a groove 16, peripheral, of the inner face of the ring (7).
  • This groove provides around the base of the sleeve a space allowing on the one hand, the use of a tool on the other hand, sufficient relative displacement of the sleeve in the sector; in particular, the bush must be able to come to bear against the internal shoulder of the platform 21.
  • This platform is engaged in a recess extending the tapped part of the housing of the bush 14.
  • the rail 8 has a radial flange 81, peripheral, on its upper face which is received in the groove 16 of the ring and against which one of the sections of the base of the socket abuts.
  • the ring is thus reconstituted step by step and the sectors joined to each other by fitting segments of the seal and wear-bearing rail 8.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP84402381A 1983-12-07 1984-11-22 Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln Expired EP0146449B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8319538 1983-12-07
FR8319538A FR2556410B1 (fr) 1983-12-07 1983-12-07 Dispositif de centrage de l'anneau interieur d'un stator a ailettes a calage variable

Publications (2)

Publication Number Publication Date
EP0146449A1 true EP0146449A1 (de) 1985-06-26
EP0146449B1 EP0146449B1 (de) 1986-11-12

Family

ID=9294921

Family Applications (1)

Application Number Title Priority Date Filing Date
EP84402381A Expired EP0146449B1 (de) 1983-12-07 1984-11-22 Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln

Country Status (5)

Country Link
US (1) US4604030A (de)
EP (1) EP0146449B1 (de)
JP (1) JPS60145500A (de)
DE (1) DE3461318D1 (de)
FR (1) FR2556410B1 (de)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2603340A1 (fr) * 1986-09-03 1988-03-04 Snecma 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
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
EP0432885A1 (de) * 1989-11-16 1991-06-19 General Motors Corporation Montage von verstellbaren Leitschaufeln in einer Stufe eines Axialkompressors
GB2289726A (en) * 1994-05-25 1995-11-29 Gen Electric Stator vane support
FR2928961A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur sectorise pour une turbomachine.
FR2994453A1 (fr) * 2012-08-08 2014-02-14 Snecma Ensemble a faible usure pour couronne aubagee de stator de turbomachine d'aeronef
EP3176384A1 (de) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Innenring, zugehöriger innenringsektor, leitschaufelkranz und strömungsmaschine
CN110656981A (zh) * 2019-10-09 2020-01-07 莱芜钢铁集团有限公司 一种trt静叶可调机构定位方法
FR3083564A1 (fr) * 2018-07-05 2020-01-10 Safran Aircraft Engines Turbine comportant un element abradable a position radiale ajustable
FR3085060A1 (fr) * 2018-08-17 2020-02-21 Safran Aircraft Engines Anneau de guidage d'aubes a calage variable et procede de montage dudit anneau
EP3913194A1 (de) * 2020-05-21 2021-11-24 Raytheon Technologies Corporation Verstellbare leitschaufeleinheit und verfahren zum betreiben einer verstellbaren leitschaufeleinheit
RU223040U1 (ru) * 2023-10-25 2024-01-29 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Направляющий аппарат компрессора газотурбинного двигателя с уплотнением

Families Citing this family (43)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2582720B1 (fr) * 1985-05-29 1989-06-02 Snecma Procede de realisation de pivot d'aube de turbomachine et aube de stator le comportant
US4925364A (en) * 1988-12-21 1990-05-15 United Technologies Corporation Adjustable spacer
CA2082709A1 (en) * 1991-12-02 1993-06-03 Srinivasan Venkatasubbu Variable stator vane assembly for an axial flow compressor of a gas turbine engine
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
DE4217099C1 (de) * 1992-05-22 1993-11-04 Magnet Motor Gmbh Elektrischer rotationsmotor mit retarderbremse
FR2723614B1 (fr) 1994-08-10 1996-09-13 Snecma Dispositif d'assemblage d'un etage circulaire d'aubes pivotantes.
FR2742799B1 (fr) * 1995-12-20 1998-01-16 Snecma Palier d'extremite interne d'aube pivotante
FR2742800B1 (fr) * 1995-12-20 1998-01-16 Snecma Agencement d'extremites internes d'un etage d'aubes a calage variable
US5921749A (en) * 1996-10-22 1999-07-13 Siemens Westinghouse Power Corporation Vane segment support and alignment device
US6139261A (en) * 1999-04-16 2000-10-31 General Electric Company Bushing assembly with removable wear sleeve
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
DE10225679A1 (de) * 2002-06-10 2003-12-18 Rolls Royce Deutschland Lagerring zur Lagerung von Schaufelfüßen von verstellbaren Statorschaufeln im Hochdruckverdichter einer Gasturbine
US7220098B2 (en) * 2003-05-27 2007-05-22 General Electric Company Wear resistant variable stator vane assemblies
US20050084190A1 (en) * 2003-10-15 2005-04-21 Brooks Robert T. Variable vane electro-graphitic bushing
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
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
EP1788199A3 (de) * 2005-11-22 2011-02-23 General Electric Company Verstellbare Leitschaufelbaugruppe mit verschleissresistenter Beschichtung
DE102006024085B4 (de) * 2006-05-23 2020-04-16 MTU Aero Engines AG Turboverdichter in Axialbauweise
FR2920469A1 (fr) * 2007-08-30 2009-03-06 Snecma Sa Aube a calage variable de turbomachine
FR2930592B1 (fr) * 2008-04-24 2010-04-30 Snecma Distributeur de turbine pour une turbomachine
FR2964710B1 (fr) * 2010-09-14 2012-08-31 Snecma Douille pour aube a calage variable
US8480423B2 (en) * 2011-08-16 2013-07-09 Tyco Electronics Corporation Contact region of an electrically conductive member
US8920116B2 (en) * 2011-10-07 2014-12-30 Siemens Energy, Inc. Wear prevention system for securing compressor airfoils within a turbine engine
FR2988787B1 (fr) * 2012-04-03 2016-01-22 Snecma Redresseur a calage variable pour compresseur de turbomachine comprenant deux anneaux internes
EP2696041B1 (de) * 2012-08-07 2020-01-22 MTU Aero Engines AG Leitschaufelkranz einer gasturbine sowie montageverfahren
EP2728123A1 (de) * 2012-11-06 2014-05-07 MTU Aero Engines GmbH Strömungsmaschine sowie zugehöriges Montageverfahren einer Strömungsmaschine
US9932988B2 (en) 2013-02-15 2018-04-03 United Technologies Corporation Bushing arranged between a body and a shaft, and connected to the shaft
US20140234087A1 (en) * 2013-02-17 2014-08-21 United Technologies Corporation Inlet guide vane retention feature
DE102013211629A1 (de) * 2013-06-20 2015-01-08 MTU Aero Engines AG Leitschaufelanordnung und Verfahren zum Montieren einer Leitschaufel
US9404376B2 (en) * 2013-10-28 2016-08-02 General Electric Company Sealing component for reducing secondary airflow in a turbine system
FR3014152B1 (fr) 2013-11-29 2015-12-25 Snecma Dispositif de guidage d'aubes de redresseur a angle de calage variable de turbomachine et procede d'assemblage d'un tel dispositif
DE102014223975A1 (de) * 2014-11-25 2016-05-25 MTU Aero Engines AG Leitschaufelkranz und Strömungsmaschine
EP3109520B1 (de) * 2015-06-24 2020-05-06 MTU Aero Engines GmbH Dichtungsträger, leitschaufelkranz und strömungsmaschine
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
US10502077B2 (en) * 2016-03-17 2019-12-10 United Technologies Corporation Vane retainer
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
CN110520631B (zh) * 2017-03-30 2021-06-08 三菱动力株式会社 可变静叶及压缩机
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
US10634000B2 (en) 2017-06-23 2020-04-28 Rolls-Royce North American Technologies Inc. Method and configuration for improved variable vane positioning
GB201715165D0 (en) * 2017-09-20 2017-11-01 Rolls Royce Plc Bearing assembly
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018213983A1 (de) * 2018-08-20 2020-02-20 MTU Aero Engines AG Verstellbare Leitschaufelanordnung, Leitschaufel, Dichtungsträger und Turbomaschine
CN114278435B (zh) * 2020-09-28 2023-05-16 中国航发商用航空发动机有限责任公司 压气机、燃气涡轮发动机、可调静叶组件以及装配方法

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1114241A (fr) * 1953-12-01 1956-04-10 Havilland Engine Co Ltd Perfectionnements aux stators pour compresseurs axiaux et machines analogues
CH315424A (fr) * 1952-07-10 1956-08-15 Havilland Engine Company Limit Rangée circulaire d'aubes fixes d'une turbo-machine à écoulement axial
FR1214261A (fr) * 1957-10-28 1960-04-07 Canadian Patents Dev Paroi de canal de turboréacteur à gaz
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2386071A1 (fr) * 1977-03-31 1978-10-27 Svenska Flaektfabriken Ab Regulateur de debit
GB2065785A (en) * 1979-12-13 1981-07-01 Westinghouse Electric Corp Adjustable mounting arrangement for seal ring and inner shroud of combustion turbine engine
EP0093631A1 (de) * 1982-04-08 1983-11-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749577A (en) * 1952-07-10 1956-05-30 Havilland Engine Co Ltd Improvements in or relating to blade ring assemblies for axial flow compressors or turbines
US3325087A (en) * 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines
US3529904A (en) * 1968-10-28 1970-09-22 Westinghouse Electric Corp Diaphragm seal structure
DE2152365C3 (de) * 1971-02-03 1973-12-06 Carrier Corp., Syracuse, N.Y. (V.St.A.) Einrichtung zum Lagern der inneren Enden von drehbar gelagerten Leitschaufeln einer Axial Stromungs maschine
US3999883A (en) * 1975-07-02 1976-12-28 General Motors Corporation Variable turbomachine stator
DE2810240C2 (de) * 1978-03-09 1985-09-26 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Verstelleitgitter für axial durchströmte Turbinen, insbesondere Hochdruckturbinen von Gasturbinentriebwerken
US4214852A (en) * 1978-04-20 1980-07-29 General Electric Company Variable turbine vane assembly

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH315424A (fr) * 1952-07-10 1956-08-15 Havilland Engine Company Limit Rangée circulaire d'aubes fixes d'une turbo-machine à écoulement axial
FR1114241A (fr) * 1953-12-01 1956-04-10 Havilland Engine Co Ltd Perfectionnements aux stators pour compresseurs axiaux et machines analogues
FR1214261A (fr) * 1957-10-28 1960-04-07 Canadian Patents Dev Paroi de canal de turboréacteur à gaz
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US3990810A (en) * 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2386071A1 (fr) * 1977-03-31 1978-10-27 Svenska Flaektfabriken Ab Regulateur de debit
GB2065785A (en) * 1979-12-13 1981-07-01 Westinghouse Electric Corp Adjustable mounting arrangement for seal ring and inner shroud of combustion turbine engine
EP0093631A1 (de) * 1982-04-08 1983-11-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Sicherheitsanschlag für die Zapfen von drehregelbaren Leitschaufeln

Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2603340A1 (fr) * 1986-09-03 1988-03-04 Snecma 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
EP0259221A1 (de) * 1986-09-03 1988-03-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Labyrinthspielanpassung für eine Turbomaschine
US4773817A (en) * 1986-09-03 1988-09-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Labyrinth seal adjustment device for incorporation in a turbomachine
EP0298894A1 (de) * 1987-07-08 1989-01-11 United Technologies Corporation Kompressor mit geteiltem Gehäuse
EP0432885A1 (de) * 1989-11-16 1991-06-19 General Motors Corporation Montage von verstellbaren Leitschaufeln in einer Stufe eines Axialkompressors
GB2289726A (en) * 1994-05-25 1995-11-29 Gen Electric Stator vane support
GB2289726B (en) * 1994-05-25 1998-02-04 Gen Electric Stator vane housing
CN101970804B (zh) * 2008-03-19 2014-01-29 斯奈克玛 用于涡轮机的扇形分配器
WO2009125078A2 (fr) 2008-03-19 2009-10-15 Snecma Distributeur sectorisé pour une turbomachine
WO2009125078A3 (fr) * 2008-03-19 2009-11-26 Snecma Distributeur sectorisé pour une turbomachine
CN101970804A (zh) * 2008-03-19 2011-02-09 斯奈克玛 用于涡轮机的扇形分配器
US8602726B2 (en) 2008-03-19 2013-12-10 Snecma Sectored distributor for turbomachine
FR2928961A1 (fr) * 2008-03-19 2009-09-25 Snecma Sa Distributeur sectorise pour une turbomachine.
FR2994453A1 (fr) * 2012-08-08 2014-02-14 Snecma Ensemble a faible usure pour couronne aubagee de stator de turbomachine d'aeronef
EP3176384A1 (de) * 2015-12-04 2017-06-07 MTU Aero Engines GmbH Innenring, zugehöriger innenringsektor, leitschaufelkranz und strömungsmaschine
US10626742B2 (en) 2015-12-04 2020-04-21 MTU Aero Engines AG Inner ring and guide vane cascade for a turbomachine
FR3083564A1 (fr) * 2018-07-05 2020-01-10 Safran Aircraft Engines Turbine comportant un element abradable a position radiale ajustable
FR3085060A1 (fr) * 2018-08-17 2020-02-21 Safran Aircraft Engines Anneau de guidage d'aubes a calage variable et procede de montage dudit anneau
GB2577795A (en) * 2018-08-17 2020-04-08 Safran Guiding ring for variable-pitch blades and method of mounting said rings
US11149571B2 (en) 2018-08-17 2021-10-19 Safran Aircraft Engines Guiding ring for variable-pitch blades and method of mounting said ring
GB2577795B (en) * 2018-08-17 2021-12-15 Safran Aircraft Engines Guiding ring for variable-pitch blades and method of mounting said ring
CN110656981A (zh) * 2019-10-09 2020-01-07 莱芜钢铁集团有限公司 一种trt静叶可调机构定位方法
CN110656981B (zh) * 2019-10-09 2022-03-25 莱芜钢铁集团有限公司 一种trt静叶可调机构定位方法
EP3913194A1 (de) * 2020-05-21 2021-11-24 Raytheon Technologies Corporation Verstellbare leitschaufeleinheit und verfahren zum betreiben einer verstellbaren leitschaufeleinheit
US11566535B2 (en) 2020-05-21 2023-01-31 Raytheon Technologies Corporation Low friction, wear resistant variable vane bushing
RU223040U1 (ru) * 2023-10-25 2024-01-29 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Направляющий аппарат компрессора газотурбинного двигателя с уплотнением

Also Published As

Publication number Publication date
FR2556410B1 (fr) 1986-09-12
EP0146449B1 (de) 1986-11-12
US4604030A (en) 1986-08-05
JPS60145500A (ja) 1985-07-31
DE3461318D1 (en) 1987-01-02
FR2556410A1 (fr) 1985-06-14

Similar Documents

Publication Publication Date Title
EP0146449B1 (de) Einrichtung für die Zentrierung eines inneren Statorringes, unterstützt durch bewegliche Schaufeln
EP3737837B1 (de) Turbinenringanordnung
CA2591770C (fr) Stator de turbomachine comportant un etage d'aubes de redresseurs actionnees par une couronne rotative a centrage automatique
EP3781792B1 (de) Keramische leitschaufel mit einer gedichteten zange um spannungen abzufedern
EP1870600B1 (de) Lager für den Drehzapfen einer Leitschaufel einer Turbomaschine mit variablem Einstellwinkel, zugehörige Leitschaufel und Turbomaschine
EP1717450B1 (de) Verstellbare Leitschaufel, Verfahren zur Reparatur einer Schaufel
EP2315642B1 (de) Verfahren zum reparieren oder nachbearbeiten einer turbomaschinenrotor
EP0395498A1 (de) Verstellvorrichtung für schwenkbare Leitschaufeln mit eingebautem Drehteller
EP3870807B1 (de) Turbinenringanordnung mit einer gewölbten und rechteckigen auflagefläche
FR2961847A1 (fr) Roue mobile a aubes en materiau composite pour moteur a turbine a gaz a liaison pied d'aube/disque par serrage
EP2053203B1 (de) Verbesserung eines Stellrings für die Anstellung von Leitradschaufeln eines Turbotriebwerks
EP3230602B1 (de) Ring zur steuerung einer phase von leitschaufeln mit variablen einstellungen für einen turbinenmotor
WO2021084203A1 (fr) Turbine de turbomachine a distributeur en cmc avec reprise d'effort
EP1469165B1 (de) Verminderung des Blattspitzenspiels bei einer Gasturbine
EP2058477A1 (de) Verbindung von radialen Streben mit einem kreisförmigen Gehäuse durch Stifte und Abstandshalter
EP0716220A1 (de) Ungeteilter Leitkranz für eine Turbomaschine
FR3072719A1 (fr) Anneau de commande d'un etage d'aubes a calage variable pour une turbomachine
EP1331402B1 (de) Steuereinrichtung für Statorschaufel
EP0148052B1 (de) Mittel zur Montage einer Abdichtung auf einer Turbomaschinenwelle
FR2983924A1 (fr) Carter annulaire pour un compresseur de turbomachine
FR3079553A1 (fr) Ensemble pour turbomachine
EP3983650B1 (de) Turbomaschinenturbine mit cmc-leitschaufel mit lastverteilung
EP4330557A1 (de) Turbinenmotoranordnung mit einem gehäuse und einem aerodynamischen behandlungselement an den schaufelspitzen sowie zugehöriger turbinenmotor
WO2024126947A2 (fr) Dispositif d'usinage et procédé de réparation d'une pièce annulaire
WO2023131759A1 (fr) Turbine pour turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19841201

AK Designated contracting states

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19860430

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REF Corresponds to:

Ref document number: 3461318

Country of ref document: DE

Date of ref document: 19870102

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20021017

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20021120

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20030130

Year of fee payment: 19

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20031122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040602

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20031122

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20040730

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST