EP0571244A1 - Abdichtungsstruktur für einen schwenkbaren Schaufel einer Turbomaschine - Google Patents

Abdichtungsstruktur für einen schwenkbaren Schaufel einer Turbomaschine Download PDF

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Publication number
EP0571244A1
EP0571244A1 EP93401205A EP93401205A EP0571244A1 EP 0571244 A1 EP0571244 A1 EP 0571244A1 EP 93401205 A EP93401205 A EP 93401205A EP 93401205 A EP93401205 A EP 93401205A EP 0571244 A1 EP0571244 A1 EP 0571244A1
Authority
EP
European Patent Office
Prior art keywords
ring
pivot
sleeve
groove
turbomachine
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
EP93401205A
Other languages
English (en)
French (fr)
Other versions
EP0571244B1 (de
Inventor
Jean-Louis Charbonnel
Jacky Serge 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 EP0571244A1 publication Critical patent/EP0571244A1/de
Application granted granted Critical
Publication of EP0571244B1 publication Critical patent/EP0571244B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially 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
    • F01D11/003—Preventing or minimising internal leakage of working-fluid, e.g. between stages by packing rings; Mechanical seals
    • 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
    • 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

Definitions

  • the invention relates to a sealing structure for a pivoting blade of a turbomachine.
  • variable pitch vanes that is to say which rotate so as to more or less straighten the gas streams which pass through them. It is thus possible to maintain a satisfactory yield whatever the speed of the machine.
  • Such blades are often encountered in particular in the first stages of a high pressure compressor located downstream of a lower pressure compressor.
  • French Patent No. 2,452,591 describes a device with several seals including a split elastic seal disposed in a groove in the pivot. The insertion of such a split ring in the bearing can however be difficult, and this is why the invention proposes with the invention a structure which allows this insertion very simply and even automatically.
  • the invention therefore relates to a structure comprising a turbomachine blade pivoting around a pivot engaged in a bearing, a split elastic ring being disposed in a groove of the pivot and designed so as to rub against the bearing by at least one first portion of the outer face, characterized by a socket engaged around the pivot on one side of the groove, the socket being movable along the pivot between a position where it covers at least a second portion of the outer face and a position where it is remote from the ring, the groove and the ring being designed so that the ring can be pushed into the groove at the location of the second portion.
  • the simplicity of assembly is further accentuated if the two portions are distinct, adjacent and separated by a shoulder from the outer face or if the sleeve has a flare at an end opposite to the ring, the flare being designed to abut against a surface where the landing opens. If these two characteristics are combined, the first position mentioned corresponds to the stop of the end of the sleeve on the shoulder and the second corresponds to the stop of the flare on the surface where the bearing emerges.
  • the slit is advantageously sinuous or in the form of a labyrinth to limit leaks through it.
  • another sleeve can be threaded between the pivot and the bearing, opposite the first sleeve relative to the split ring. The best support for the pivot is then achieved.
  • FIG. 1 therefore represents the turbomachine, essentially composed of a stator 1 surrounding a rotor 2 to delimit a substantially annular vein 3 through which the gases pass.
  • a low-pressure compressor 4 and a high-pressure compressor 5 occupy two different parts of the annular stream 3 and are each composed of stages of rotor blades 6, integral with the latter, and stages of blades of stator 7 and 8, most of which are fixed vanes 7 but some of which, namely the vanes of the first four stages of the high pressure compressor 5, are variable pitch vanes 8 pivoting around a pivot 9 housed in a through bearing the stator wall 1.
  • the pivot 9 is notched with a groove 10 in which there is a split ring 11 and whose slot is designated by 12. It is a slot 12 labyrinth , that is to say that it is not straight but sinuous and here comprises a part in an arc 13 joining two straight parts 14 and 15 for connection to the two axial edges 16 and 17 of the ring 11.
  • a slot 12 labyrinth that is to say that it is not straight but sinuous and here comprises a part in an arc 13 joining two straight parts 14 and 15 for connection to the two axial edges 16 and 17 of the ring 11.
  • the groove 10 is designed so that the material of the ring 11 located in front of the peripheral portions 20 and 21 is entirely contained in the groove 10 when the slot 12 is closed as a result of the contraction of the ring 11.
  • a contraction can be achieved by a sleeve 22 sliding along the pivot 9 and located between the ring 11 and the blade 8: the bush 22 is placed just before the blade 8 is mounted on the stator 1 so that it occupies a position where it abuts against the crest of the ring 11 and covers one of the peripheral portions 21.
  • the cylindrical part 23 is introduced by sliding freely in the bearing 25 of the stator 1 until the flange 24 abuts against the internal surface 26 of the stator 1, where the bearing 25 opens. It is then retained while the depression of the blade 8 and of the pivot 9 continues, until the blade 8 abuts against the flange 24, but the ring 11 is then entirely escaped from the sleeve 22 , which allowed its expansion, so that the crest portion 19 now touches a part of the surface of the bearing 25 and establishes the desired seal.
  • a second sleeve 27 can be threaded into the bearing 25, on the other side of the previous one with respect to the ring 11: this sleeve 27 can also consist of a cylindrical part 28 and a flared part in a flange 29 intended to serve as a stop on the external surface 30 of the stator 1.
  • the pivot 9 is then well supported and can be screwed by conventional fixing systems outside the stator 1.
  • the bushings 22 and 27 are made of self-lubricating material and are used, as usual, to support bearings for the pivot 9.
EP93401205A 1992-05-20 1993-05-12 Abdichtungsstruktur für einen schwenkbaren Schaufel einer Turbomaschine Expired - Lifetime EP0571244B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9206101A FR2691507B1 (fr) 1992-05-20 1992-05-20 Structure d'etancheite pour une aube pivotante de turbomachine.
FR9206101 1992-05-20

Publications (2)

Publication Number Publication Date
EP0571244A1 true EP0571244A1 (de) 1993-11-24
EP0571244B1 EP0571244B1 (de) 1995-07-26

Family

ID=9429957

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93401205A Expired - Lifetime EP0571244B1 (de) 1992-05-20 1993-05-12 Abdichtungsstruktur für einen schwenkbaren Schaufel einer Turbomaschine

Country Status (5)

Country Link
US (1) US5324165A (de)
EP (1) EP0571244B1 (de)
JP (1) JP2618181B2 (de)
DE (1) DE69300297T2 (de)
FR (1) FR2691507B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2362927A (en) * 2000-03-07 2001-12-05 Elta Fans Ltd A hub for a fan blade

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2869417B2 (ja) * 1992-09-22 1999-03-10 吉富製薬株式会社 遺伝子操作により得られるヒト血清アルブミン
FR2742799B1 (fr) * 1995-12-20 1998-01-16 Snecma Palier d'extremite interne d'aube pivotante
US5931636A (en) * 1997-08-28 1999-08-03 General Electric Company Variable area turbine nozzle
US5941537A (en) * 1997-09-05 1999-08-24 General Eletric Company Pressure actuated static seal
US6210106B1 (en) * 1999-04-30 2001-04-03 General Electric Company Seal apparatus for gas turbine engine variable vane
US6682299B2 (en) * 2001-11-15 2004-01-27 General Electric Company Variable stator vane support arrangement
US6887035B2 (en) * 2002-10-23 2005-05-03 General Electric Company Tribologically improved design for variable stator vanes
GB0504588D0 (en) * 2005-03-05 2005-04-13 Rolls Royce Plc Pivot ring
US20080000396A1 (en) * 2006-06-12 2008-01-03 Tabor Keith S Shipping container
EP1925783B1 (de) * 2006-11-22 2012-05-02 Siemens Aktiengesellschaft Verstellbarer Leitschaufelzusammenbau
CA2900221C (en) 2013-02-26 2021-01-19 Ted Joseph Freeman Adjustable turbine vanes with sealing device and corresponding method
JP6185781B2 (ja) * 2013-07-23 2017-08-23 三菱日立パワーシステムズ株式会社 軸流圧縮機
CN104196751B (zh) * 2014-01-23 2016-08-10 南京航空航天大学 用于压气机/风扇静子封严与吸气控制角区分离结构
DE102016215807A1 (de) * 2016-08-23 2018-03-01 MTU Aero Engines AG Innenring für einen Leitschaufelkranz einer Strömungsmaschine
DE102017109952A1 (de) * 2017-05-09 2018-11-15 Rolls-Royce Deutschland Ltd & Co Kg Rotorvorrichtung einer Strömungsmaschine
DE102018210601A1 (de) * 2018-06-28 2020-01-02 MTU Aero Engines AG Segmentring zur montage in einer strömungsmaschine
DE102018213604A1 (de) * 2018-08-13 2020-02-13 Rolls-Royce Deutschland Ltd & Co Kg Leitschaufelbaugruppe mit Dichtelement
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
CN114215789A (zh) * 2021-12-06 2022-03-22 中国航发沈阳发动机研究所 一种双层机匣的引气结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2245068A1 (de) * 1972-09-08 1974-03-21 Bbc Sulzer Turbomaschinen Mehrstufiger axialverdichter
GB2016091A (en) * 1978-03-09 1979-09-19 Mtu Muenchen Gmbh Variable nozzle vane assembly
FR2452591A1 (fr) * 1974-12-13 1980-10-24 Gen Electric Structure d'aube directrice de turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3210045A (en) * 1963-05-09 1965-10-05 Nydqvist & Holm Ab Device for wicket guide stems for water turbines, pump turbines or pumps
US4792277A (en) * 1987-07-08 1988-12-20 United Technologies Corporation Split shroud compressor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2245068A1 (de) * 1972-09-08 1974-03-21 Bbc Sulzer Turbomaschinen Mehrstufiger axialverdichter
FR2452591A1 (fr) * 1974-12-13 1980-10-24 Gen Electric Structure d'aube directrice de turbomachine
GB2016091A (en) * 1978-03-09 1979-09-19 Mtu Muenchen Gmbh Variable nozzle vane assembly

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2362927A (en) * 2000-03-07 2001-12-05 Elta Fans Ltd A hub for a fan blade

Also Published As

Publication number Publication date
DE69300297D1 (de) 1995-08-31
DE69300297T2 (de) 1996-02-01
JPH0650103A (ja) 1994-02-22
EP0571244B1 (de) 1995-07-26
US5324165A (en) 1994-06-28
FR2691507A1 (fr) 1993-11-26
FR2691507B1 (fr) 1994-07-08
JP2618181B2 (ja) 1997-06-11

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