EP1306525B1 - Stützträger für den Statorring einer Turbomaschine - Google Patents

Stützträger für den Statorring einer Turbomaschine Download PDF

Info

Publication number
EP1306525B1
EP1306525B1 EP02292633A EP02292633A EP1306525B1 EP 1306525 B1 EP1306525 B1 EP 1306525B1 EP 02292633 A EP02292633 A EP 02292633A EP 02292633 A EP02292633 A EP 02292633A EP 1306525 B1 EP1306525 B1 EP 1306525B1
Authority
EP
European Patent Office
Prior art keywords
pin
holes
sector
inlet nozzle
guide vane
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 - Lifetime
Application number
EP02292633A
Other languages
English (en)
French (fr)
Other versions
EP1306525A1 (de
Inventor
Serge Bongrand
Fabrice Marois
Alain Henri Daniel Bouron
Jacky Naudet
Sébastien Georges Roger Goux
Gabriel Radeljak
Dominique Raulin
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1306525A1 publication Critical patent/EP1306525A1/de
Application granted granted Critical
Publication of EP1306525B1 publication Critical patent/EP1306525B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/30—Retaining components in desired mutual position
    • F05B2260/301—Retaining bolts or nuts

Definitions

  • the subject of this invention is a device for stopping in rotation a sector bearing vanes fixed in a shell forming part of a casing of a turbomachine.
  • the ferrules of the turbomachines are generally composed of two complementary sectors each extending over a half-turn and which are provided with a continuous circular rabbet for receiving stator sectors carrying fixed vanes and which extend over portions of circumference smaller.
  • This device as such leaves the sectors free to slide in the ferrule sliding together in the rabbet, which produces wear and noise during operation.
  • it is planned to add a rotation stop system for these sectors, which has already taken various forms in the known devices. It is first possible to place bars crossing the rabbets between the ferrule sectors, so as to stop the movement of the rectifier sectors.
  • This system is simple but has the disadvantage that it can not install more than two stop means in rotation: it therefore only partially remedies the anarchic movement of the blade sectors.
  • the invention relates to a rotation stop system of a very simple nature and which can equip at a lower cost an already existing machine that has the desire to improve.
  • This system applies individually to the rectifier sectors and thus ensures total immobility of the sectors if it is provided on each of them, without requiring excessive costs.
  • Another advantage of the invention is that the seal between the rectifier sectors is not compromised.
  • the rotational stop device comprises a pair of bores operated in extension in a rectifier sector and the shell respectively, as well as a pin engaged in the bores and means for holding the pin in the bores. holes.
  • the holes may in particular be operated through a rim of the rectifier sector and through a rabbet of the ferrule in which the rim is depressed.
  • the holding means then advantageously comprise a rod engaged under the rim in the rabbet and occupying a recess intersecting the pin; they may also include a tongue protruding from the pawn and abutting against the rectifier sector on one side, the ferrule on the other side.
  • the pin has a non-circular section and is fitted into a bore having a corresponding non-circular section.
  • FIG. 1 shows a portion of a ferrule 15 and a rectifier sector 16; the latter comprises an edge 17 directed in an axial direction engaged in a rebate 18 formed between a hook portion 19, bent in the other axial direction, and a cylindrical main portion 20 of the shell 15.
  • the shell 15 comprises a bore 21 passing through the hook portion 19, and the sector member 16 also includes a bore 22 intersecting the flange 17 and extending the bore 21; Figure 4 helps to better grasp the layout.
  • a pin 23 also seen in Figure 2 is engaged in the holes 21 and 22 and thus ensures the rotation stop sector 16 relative to the shell 15. It is retained in the holes 21 and 22 by a fastening ring 24 engaged at the bottom of the rabbet 18, under the rim 17, from a not shown orifice operated in the hook portion 19, and which passes through a recess 25 of the pin 23.
  • the accidental extraction of the pin 23 can still be prevented by a tongue 26 protruding from the pin 23 and abutting on one side against the ferrule and on the other side against a rectifier sector 16. This can be accomplished by joining the rectifier sector 16 to the ferrule after having put the pin 23 in place in the holes 21 and 22.
  • the ferrule 15 is joined to another ferrule 27 which is radially internal to it, the bore 21 opens on the lower side on the other ferrule 27, and the tongue 26 abuts against the Another ferrule 27, which does not change anything, however.
  • the ring 24 is then slid to the bottom of the rabbet 18; it can extend in front of a series of rectifier sectors 16 and retain as many counters 23.
  • FIG. 3 Another embodiment, whose implantation is also shown in Figure 4, appears in Figure 3 and comprises a pin 30 comprising a pair of side projections 31.
  • the pin 30 is, like the previous one, engaged in a hole 32 operated in a rim 33 of a rectifier sector 34, as well as in a bore 35 extending the former and operated here through the other ferrule 27.
  • the counter 30 When the other ferrule 27 and the rectifier sector 34 are assembled, the counter 30 having previously been engaged in the holes 32 and 35, they include a cavity 36 occupied by the projections 31 by preventing the pin 30 is extracted. This is the same mounting mode for the pins 23 and 30.
  • the pins 23 and 30 have non-circular portions such as plane facets 37 and 38, engaged in one of the holes 21, 22, 32 and 35 to prevent accidental rotation of the pin 23 or 30 which would interfere with the assembly. ; the holes in which these non-circular portions are engaged obviously have a section of complementary shape.
  • the ends of the pins can be tapered to facilitate their insertions in the holes; one of them bears the reference 39 for the pawn 30; it is shaped like a pyramid.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
  • Component Parts Of Construction Machinery (AREA)

Claims (3)

  1. Verbindung eines Sektors von Leitapparatschaufeln und einer Turbomaschinenzwinge mit einem Sektor von Schaufeln von Leitapparaten (16, 34), einer Zwinge (15, 27),einer Vorrichtung zur Drehungssperre des Sektors von Leitapparatschaufeln (16, 34) in der Zwinge (15, 27), wobei die Vorrichtung zur Drehungssperre ein Paar von Bohrungen (21, 22, 32, 35) aufweist, die in Verlängerung in dem Sektor bzw. der Zwinge ausgeführt sind, ein Metallstück (23, 30), das in die Bohrungen gesteckt ist, und Mittel (24, 26, 31) zum Halten des Metallstücks in den Bohrungen, dadurch gekennzeichnet, daß die Haltemittel eine Zunge (26, 31) aufweisen, die von dem Metallstück vorspringt und gegen den Sektor von Leitapparatschaufeln auf der einen Seite und gegen die Zwinge auf der anderen Seite stößt.
  2. Verbindung nach Anspruch 1, dadurch gekennzeichnet, daß die Bohrungen durch einen Rand (17) des Sektors von Leitapparatschaufeln (16) und durch einen Falz (17) der Zwinge (15) ausgeführt sind, worin der Rand eingesetzt ist, und daß die Haltemittel einen Stab (24) aufweisen, der unter dem Rand in den Falz gesteckt ist und eine Ausnehmung einnimmt, die das Metallstück schneidet.
  3. Verbindung nach Anspruch 1, dadurch gekennzeichnet, daß das Metallstück einen nicht kreisförmigen Querschnitt (37, 38) aufweist, der in eine der Bohrungen mit einem entsprechenden, nicht kreisförmigen Querschnitt eingepaßt ist.
EP02292633A 2001-10-25 2002-10-24 Stützträger für den Statorring einer Turbomaschine Expired - Lifetime EP1306525B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0113780A FR2831600B1 (fr) 2001-10-25 2001-10-25 Dispositif d'arret en rotation d'un secteur porteur d'aubes fixes dans une virole d'une turbomachine
FR0113780 2001-10-25

Publications (2)

Publication Number Publication Date
EP1306525A1 EP1306525A1 (de) 2003-05-02
EP1306525B1 true EP1306525B1 (de) 2006-12-20

Family

ID=8868693

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02292633A Expired - Lifetime EP1306525B1 (de) 2001-10-25 2002-10-24 Stützträger für den Statorring einer Turbomaschine

Country Status (10)

Country Link
US (1) US7018173B2 (de)
EP (1) EP1306525B1 (de)
JP (1) JP4256778B2 (de)
CA (1) CA2464126C (de)
DE (1) DE60216874T2 (de)
ES (1) ES2273983T3 (de)
FR (1) FR2831600B1 (de)
RU (1) RU2297539C2 (de)
UA (1) UA79757C2 (de)
WO (1) WO2003036050A1 (de)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7094025B2 (en) * 2003-11-20 2006-08-22 General Electric Company Apparatus and methods for removing and installing a selected nozzle segment of a gas turbine in an axial direction
FR2871845B1 (fr) 2004-06-17 2009-06-26 Snecma Moteurs Sa Montage de chambre de combustion de turbine a gaz avec distributeur integre de turbine haute pression
EP1939459B1 (de) * 2006-12-27 2018-04-25 Safran Aero Boosters SA Flanschverbindung mit Klemmbacke, insbesondere für einen Axialverdichter
EP2473712B1 (de) * 2009-09-02 2013-07-03 Siemens Aktiengesellschaft Befestigungsvorrichtung
JP2011169246A (ja) * 2010-02-19 2011-09-01 Mitsubishi Heavy Ind Ltd ガスタービンケーシング構造
FR2972124B1 (fr) * 2011-03-01 2014-05-16 Snecma Procede de realisation d'une piece metallique telle qu'un renfort d'aube de turbomachine
KR20140108109A (ko) 2011-12-29 2014-09-05 엘리오트 컴퍼니 고온 가스 팽창기 입구 케이싱 조립체 및 방법
ITCO20120014A1 (it) * 2012-04-06 2013-10-07 Nuovo Pignone Srl Anello di diaframma di pala statorica, turbina a vapore e metodo
FR2989725B1 (fr) * 2012-04-23 2014-04-11 Snecma Etage de turbine
EP2909463B8 (de) 2012-10-17 2021-04-07 Raytheon Technologies Corporation Turbofan-triebwerk und zugehöriges verfahren zur montage eines vorderen abschnitts eines turbofan-triebwerks
CN104047541B (zh) * 2014-06-19 2015-12-09 西南石油大学 一种新型自动防喷涡轮钻具定子
US10502059B2 (en) 2015-02-02 2019-12-10 United Technologies Corporation Alignment tie rod device and method of utilization
EP3208431B1 (de) * 2016-02-16 2022-01-05 MTU Aero Engines AG Verbindungsanordnung für gehäuseelement eines turbinenzwischengehäuses
GB2588929B (en) * 2019-11-14 2023-09-27 Cummins Ltd Pin member for turbine

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2955800A (en) * 1957-05-28 1960-10-11 Gen Motors Corp Turbomachine stator assembly
GB1387866A (en) * 1972-06-21 1975-03-19 Rolls Royce Aerofoil members for gas turbine engines
US4868963A (en) * 1988-01-11 1989-09-26 General Electric Company Stator vane mounting method and assembly
US5211536A (en) * 1991-05-13 1993-05-18 General Electric Company Boltless turbine nozzle/stationary seal mounting
FR2780443B1 (fr) * 1998-06-25 2000-08-04 Snecma Anneau de stator de turbine haute pression d'une turbomachine
US6095750A (en) * 1998-12-21 2000-08-01 General Electric Company Turbine nozzle assembly

Also Published As

Publication number Publication date
RU2297539C2 (ru) 2007-04-20
US20040240992A1 (en) 2004-12-02
JP2005506485A (ja) 2005-03-03
FR2831600A1 (fr) 2003-05-02
CA2464126C (fr) 2011-05-31
JP4256778B2 (ja) 2009-04-22
DE60216874T2 (de) 2007-08-02
RU2004115731A (ru) 2005-05-20
EP1306525A1 (de) 2003-05-02
FR2831600B1 (fr) 2004-01-02
WO2003036050A1 (fr) 2003-05-01
ES2273983T3 (es) 2007-05-16
DE60216874D1 (de) 2007-02-01
CA2464126A1 (fr) 2003-05-01
US7018173B2 (en) 2006-03-28
UA79757C2 (en) 2007-07-25

Similar Documents

Publication Publication Date Title
EP1306525B1 (de) Stützträger für den Statorring einer Turbomaschine
EP0488874B1 (de) Gebläserotor mit Schaufeln ohne Plattform und Stromlinien rekonstruierenden Füllstücken
EP0083289B1 (de) Rotorrad eines Turbostrahltriebwerkes mit einer Vorrichtung zum axialen und radialen Befesten der Rotorschaufeln am Rotorrad
EP0202993B1 (de) Scheibenbremsenfeder
EP1921273B1 (de) Aufhängevorrichtung eines Turbinenleitkranzes
EP1564372A1 (de) Auswuchteinrichtung für die Turbinenrotorscheiben eines Gasturbinentriebwerks
EP0214876B1 (de) Mehrzweck-Labyrinthträgerscheibe für einen Turbomaschinenrotor
FR2868814A1 (fr) Dispositif d'assemblage de brides annulaires, en particulier dans une turbomachine
FR2887940A1 (fr) Bague de retenue pour arbre
FR2776012A1 (fr) Joint d'etancheite d'un etage d'aubes circulaire
EP0607082B1 (de) Turbomaschinenrotor mit Schaufelnbefestigung durch Stifte
FR2686941A1 (fr) Ailette de rotor comportant des talons anti-oscillants et rotor de moteur a turbine a gaz comportant de telles ailettes.
FR2844962A1 (fr) Dispositif de fixation de lames a des flasques solidaires en rotation d'un arbre rotatif et machine agricole equipee d'un tel dispositif
FR2685614A1 (fr) Bracelet a maillons notamment pour montre.
EP1855011B1 (de) Anordnung für den Verdichter eines Luftschiffmotors mit Schaufelrädern, befestigtem Hammer und geneigtem Fuss
FR2710103A1 (fr) Flasque de rotor de turbomachine et assemblage de ce flasque avec un rotor.
EP1515002B1 (de) Verdrehsicherung für Turbinenstatorschaufeln in der Gehäusetrennebene
FR2758364A1 (fr) Disque aubage a aubes tripodes
FR2593867A1 (fr) Moyen de retenue de broches d'ancrage de sabots de frein
EP2060744A1 (de) Turbinen- oder Kompressorstufe eines Turbotriebwerks
EP0112749B1 (de) Belagträger für Scheibenbremse mit Antiklapperfeder
WO1986004396A1 (fr) Dispositif d'action centrifuge notamment pour friction d'embrayage
EP3721742B1 (de) Automatisch aufklappender sonnenschirm
FR2832179A1 (fr) Stator d'une machine et procedes de montage et demontage
FR2771147A1 (fr) Frein a disque a etrier flottant a une seule colonnette

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: 20021130

AK Designated contracting states

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR IE IT LI LU MC NL PT SE SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK RO SI

RIN1 Information on inventor provided before grant (corrected)

Inventor name: MAROIS, FABRICE

Inventor name: RADELJAK, GABRIEL

Inventor name: NAUDET, JACKY

Inventor name: BONGRAND, SERGE

Inventor name: BOURON, ALAIN, HENRI, DANIEL

Inventor name: GOUX, SEBASTIEN, GEORGES, ROGER

Inventor name: RAULIN, DOMINIQUE

AKX Designation fees paid

Designated state(s): DE ES FR GB IT SE

17Q First examination report despatched

Effective date: 20050513

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE ES FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20061220

REF Corresponds to:

Ref document number: 60216874

Country of ref document: DE

Date of ref document: 20070201

Kind code of ref document: P

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: ES

Ref legal event code: FG2A

Ref document number: 2273983

Country of ref document: ES

Kind code of ref document: T3

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

Effective date: 20070921

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

Ref country code: ES

Payment date: 20121005

Year of fee payment: 11

REG Reference to a national code

Ref country code: ES

Ref legal event code: FD2A

Effective date: 20150710

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

Ref country code: ES

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

Effective date: 20131025

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 14

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 15

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 16

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 17

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

Ref country code: IT

Payment date: 20210922

Year of fee payment: 20

Ref country code: FR

Payment date: 20210922

Year of fee payment: 20

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

Ref country code: SE

Payment date: 20210921

Year of fee payment: 20

Ref country code: GB

Payment date: 20210922

Year of fee payment: 20

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

Ref country code: DE

Payment date: 20210921

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 60216874

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20221023

REG Reference to a national code

Ref country code: SE

Ref legal event code: EUG

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 EXPIRATION OF PROTECTION

Effective date: 20221023