EP1580403A1 - Dichtring zur Abdichtung zwischen Aussen- und Innengehäuse einer Turbomaschine - Google Patents

Dichtring zur Abdichtung zwischen Aussen- und Innengehäuse einer Turbomaschine Download PDF

Info

Publication number
EP1580403A1
EP1580403A1 EP05290664A EP05290664A EP1580403A1 EP 1580403 A1 EP1580403 A1 EP 1580403A1 EP 05290664 A EP05290664 A EP 05290664A EP 05290664 A EP05290664 A EP 05290664A EP 1580403 A1 EP1580403 A1 EP 1580403A1
Authority
EP
European Patent Office
Prior art keywords
seal
turbojet
axial wall
section according
wall
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.)
Withdrawn
Application number
EP05290664A
Other languages
English (en)
French (fr)
Inventor
Claude Lejars
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 EP1580403A1 publication Critical patent/EP1580403A1/de
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the invention relates to the sealing between two enclosures of a turbojet engine delimited by crankcases and subjected to pressure different.
  • turbojet section having an outer casing having a radially extending surface inward, an inner casing having a substantially axial wall which extends towards said surface and a seal disposed between said wall and said surface and intended to ensure the seal between the regions to high and low pressures located on either side of said seal.
  • a turbojet engine has an annular channel in which circulates a hot working fluid whose temperature and pressure vary depending on the power demanded from the motor. These variations of temperature causes dilation of the casings surrounding the channel, and certain parts, particularly at the turbine level, subject to highest temperatures require cooling with air fresh under high pressure. Cooling is carried out by a air sampling at a stage of the high pressure compressor. This cooling air circulates in enclosures arranged between a outer casing and an inner casing of the compressor and turbines.
  • FIG. 1 Another technique used in a high compressor pressure, shown in Figure 1, is to position between two radial surfaces provided, facing each other, one on the outer casing and the other on the inner casing, an Omega-type annular seal present in the form of a bellows maintained in compression between said two surfaces.
  • this Omega seal is held radially between two annular complementary axial walls, formed one on the housing inside and the other on the outer casing, of which at least one extends the radial surface of the other housing and may be subject to constraints axial under certain operating conditions of the turbojet engine. This requires additional machining operations to achieve these complementary axial walls which, under certain conditions, prevent free expansion of the inner casing relative to the outer casing.
  • the invention has the primary purpose of sealing between two casings of a turbojet section, through the implementation of of a new type of seal better adapted to the conditions of operation.
  • Another object of the invention is to propose a type of seal which simplify crankcase structure at the location of the zone to quench.
  • the invention achieves its goal by the fact that the seal is realized in the form of a ring annular ferrule having a first substantially cylindrical portion sealingly attached to a face of the axial wall and a second part extending said first part, and located in the space between said axial wall of said surface radial, said second part having, in section along a radial plane containing the axis of the turbojet, a V-shaped profile and having a portion end bearing slidingly and sealingly against said radial surface.
  • the proposed joint is thus in the form of a ring in sheet having a first cylindrical portion which is enclosed on the wall cylindrical inner casing, and a second part consisting of two conical portions connected together, and whose median portion is connected to the first cylindrical part, the free end of the other frustoconical portion being in sliding support on the radial surface of the outer casing.
  • the radial wall of the inner casing and the axial walls complementary to the two state-of-the-art housings no longer utility and can be deleted.
  • the first part of the seal can be fixed on the axial wall of the internal casing by riveting or bolting.
  • the first part preferably includes a redan which cooperates with a complementary projection formed on the adjacent face of the axial wall, which ensures the stop in axial translation of the seal relative to the inner casing.
  • the second part is placed in axial compression during assembly of the inner casing on the outer casing.
  • the end portion of the second part is curved so that its external axial face bears on said surface radial.
  • the seal according to the invention is configured in such a way that the pressure difference between high and low pressure regions positively the end portion of the second part to the surface radial.
  • the tip of the V-shaped section is arranged radially under the axial wall, and vice versa if the low pressure is radially outside the inner casing, the second part is disposed above the axial wall of the inner casing.
  • the seal according to the invention is particularly suitable for a high-pressure compressor of a turbojet, but it can also be used for other parts of a turbomachine, particularly at level of stator housings or turbine stators.
  • FIG 1 shows a stator 1 of a high compressor pressure, according to the state of the art, which equips a turbojet engine.
  • This stator 1 comprises an inner casing 2 and an outer casing 3 connected in upstream by bolting flanges 4 and 5 respectively provided on a annular wall 6 of the outer casing 3 and on an annular wall substantially axial 7 of the inner casing 2.
  • the annular wall 7 is extends downstream and its substantially cylindrical end 8 connected, facing a radial surface 9 integral with the outer casing 2, a second radial wall 10 connected itself to an axial wall complementary 11 which extends to the radial surface 9 of the housing 2.
  • the wall axial 11 and the second radial wall 10 houses a joint 13 Omega type which bears on the radial surface 9 of the outer casing 3 and on the face vis-à-vis the radial wall 10 of the inner housing 2.
  • a second axial wall 16 is provided on the outer casing 3 above the groove 12.
  • the Omega 13 seal is intended to seal between the enclosure 14 located under the outer casing 3, where there is a pressure P1, and the enclosure 15 located under the end 8 of the axial wall 7 where there is a pressure P2 less than the pressure P1.
  • Figures 2 and 3 show the changes made to the end 8 of the axial wall 7 and the new seal 20 proposed by the invention for sealing between the end 8 of the axial wall 7 of the inner casing 2 and the radial surface 9 of the outer casing 3.
  • the radial wall 10 and the axial wall complementary 11 have no more utility and can be totally eliminated, which facilitates the machining of the downstream end 8 of the wall 7.
  • the second axial wall 16 of the outer casing 3 can also be deleted.
  • the seal 20 is in the form of an annular ring in sheet metal having two parts 21 and 22 having distinct functions.
  • the first part 21 is substantially cylindrical and its diameter is equal to the outside diameter of the end portion 8 of the wall ring 7 of the inner casing 2, so that it can be fitted on this end portion 8.
  • the second part 22, which constitutes the seal seal itself, is arranged in the space 23 separating the end face 8a of the axial wall 7 and the radial surface 9, and present in section, in a radial plane containing the axis of the turbojet engine, a V-section or flared U-section
  • This second part 22 thus comprises two portions frustoconical 24 and 25 interconnected by a shaped portion 26 of annular gutter.
  • the medial frustoconical portion 24 is connected to the first part 21 by an annular portion 27 whose face convex 27a is located on the side of the chamber 14 in which there is a fluid at the pressure P1 and at the temperature t1, the pressure P1 being greater than the pressure P2 prevailing in the chamber 15 located under the wall axial 7 of the inner casing 2.
  • the other frustoconical portion 25 is slightly curved near its free end, so that its end portion 25a has on its opposite side to the first part 21 a convex annular surface in sliding support on the radial surface 9 of the outer casing 3.
  • the annular volume between the two portions frustoconical 24 and 25 is thus in the enclosure 14 at high pressure, and the pressure differences on both sides of the second part 22 tend to separate the frustoconical portion 24 of the frustoconical portion 25, which ensures the seal between the two enclosures 14 and 15, during the relative axial or radial displacements between the end 8 of the wall axial 7 and the radial surface 9 of the outer enclosure.
  • the first part 21 is fixed by brazing on the external face of the axial wall 7.
  • the first portion 21 advantageously has a redan 30 which cooperates with a complementary projection 31 formed on the outer face of the wall axial 7, to ensure a stop in translation of the seal 20.
  • the first part 21 of the seal 20 and the end 8 of the axial wall 7 of the casing inside 2 have corresponding holes for fastening the seal 20 on the end 8 of the axial wall by bolting or by riveting.
  • the second part 22 is put into compression when mounting the inner casing 2 on the outer casing 3.
  • the geometry of this second part 22 is calculated so as to provide significant flexibility.
  • the section of the seal 20 is sufficiently large to allow to absorb more relative displacements important than those allowed by the current Omega seal and allows the use of a thicker sheet, which reduces the impact to the wear of the faces in contact and makes the seal 20 more tolerant to vibration.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gasket Seals (AREA)
EP05290664A 2004-03-26 2005-03-25 Dichtring zur Abdichtung zwischen Aussen- und Innengehäuse einer Turbomaschine Withdrawn EP1580403A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0403130 2004-03-26
FR0403130A FR2868119B1 (fr) 2004-03-26 2004-03-26 Joint d'etancheite entre les carters interieurs et exterieurs d'une section de turboreacteur

Publications (1)

Publication Number Publication Date
EP1580403A1 true EP1580403A1 (de) 2005-09-28

Family

ID=34855167

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290664A Withdrawn EP1580403A1 (de) 2004-03-26 2005-03-25 Dichtring zur Abdichtung zwischen Aussen- und Innengehäuse einer Turbomaschine

Country Status (6)

Country Link
US (1) US20050242522A1 (de)
EP (1) EP1580403A1 (de)
JP (1) JP2005282571A (de)
CA (1) CA2500965A1 (de)
FR (1) FR2868119B1 (de)
RU (1) RU2005108415A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027874A1 (fr) * 2014-11-03 2016-05-06 Airbus Operations Sas Ensemble de propulsion comportant un joint

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2938873B1 (fr) * 2008-11-21 2014-06-27 Turbomeca Organe de positionnement pour segment d'anneau
EP2530249A1 (de) 2011-05-30 2012-12-05 Siemens Aktiengesellschaft Kolbendichtungsring
US9017015B2 (en) * 2011-10-27 2015-04-28 General Electric Company Turbomachine including an inner-to-outer turbine casing seal assembly and method
FR2986836B1 (fr) * 2012-02-09 2016-01-01 Snecma Tole annulaire anti-usure pour une turbomachine
US9828867B2 (en) * 2012-12-29 2017-11-28 United Technologies Corporation Bumper for seals in a turbine exhaust case
WO2014133616A1 (en) * 2013-03-01 2014-09-04 Rolls-Royce North American Technologies,Inc. Gas turbine engine impeller system for an intermediate pressure (ip) compressor
WO2014137430A1 (en) * 2013-03-08 2014-09-12 Rolls-Royce North American Technologies, Inc. Gas turbine engine centrifugal compressor with seal between two diffuser parts
US10184354B2 (en) * 2013-06-19 2019-01-22 United Technologies Corporation Windback heat shield
FR3080503B1 (fr) * 2018-04-20 2020-03-20 Renault S.A.S Ensemble statorique pour machine electrique
CN110318829A (zh) * 2019-07-19 2019-10-11 中国航发沈阳发动机研究所 一种弹性片封严结构
CN115405370B (zh) * 2022-11-03 2023-03-10 中国航发沈阳发动机研究所 一种半弹性涡轮外环结构

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2468738A1 (fr) * 1979-11-01 1981-05-08 United Technologies Corp Organe d'etancheite pour une turbine a gaz
US4336943A (en) * 1980-11-14 1982-06-29 United Technologies Corporation Wedge-shaped seal for flanged joints
EP0177650A1 (de) * 1983-08-22 1986-04-16 Heat Transfer Technology Limited Abdichtung eines Zylinderendes
WO1998053228A1 (en) * 1997-05-21 1998-11-26 Allison Advanced Development Company Interstage vane seal apparatus
US6164656A (en) * 1999-01-29 2000-12-26 General Electric Company Turbine nozzle interface seal and methods
EP1130219A1 (de) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbinenanlage mit Dichtungen zwischen Plattenelementen
US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
US20040031271A1 (en) * 2002-08-15 2004-02-19 Power Systems Mfg, Llc Convoluted seal with enhanced wear capability
EP1515003A1 (de) * 2003-09-11 2005-03-16 Siemens Aktiengesellschaft Gasturbine und Dichtungsmittel für eine Gasturbine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4199151A (en) * 1978-08-14 1980-04-22 General Electric Company Method and apparatus for retaining seals
US4477086A (en) * 1982-11-01 1984-10-16 United Technologies Corporation Seal ring with slidable inner element bridging circumferential gap
US5149250A (en) * 1991-02-28 1992-09-22 General Electric Company Gas turbine vane assembly seal and support system
CA2070511C (en) * 1991-07-22 2001-08-21 Steven Milo Toborg Turbine nozzle support
US5562408A (en) * 1995-06-06 1996-10-08 General Electric Company Isolated turbine shroud

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2468738A1 (fr) * 1979-11-01 1981-05-08 United Technologies Corp Organe d'etancheite pour une turbine a gaz
US4336943A (en) * 1980-11-14 1982-06-29 United Technologies Corporation Wedge-shaped seal for flanged joints
EP0177650A1 (de) * 1983-08-22 1986-04-16 Heat Transfer Technology Limited Abdichtung eines Zylinderendes
WO1998053228A1 (en) * 1997-05-21 1998-11-26 Allison Advanced Development Company Interstage vane seal apparatus
US6164656A (en) * 1999-01-29 2000-12-26 General Electric Company Turbine nozzle interface seal and methods
EP1130219A1 (de) * 2000-03-02 2001-09-05 Siemens Aktiengesellschaft Turbinenanlage mit Dichtungen zwischen Plattenelementen
US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine
US20040031271A1 (en) * 2002-08-15 2004-02-19 Power Systems Mfg, Llc Convoluted seal with enhanced wear capability
EP1515003A1 (de) * 2003-09-11 2005-03-16 Siemens Aktiengesellschaft Gasturbine und Dichtungsmittel für eine Gasturbine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3027874A1 (fr) * 2014-11-03 2016-05-06 Airbus Operations Sas Ensemble de propulsion comportant un joint

Also Published As

Publication number Publication date
RU2005108415A (ru) 2006-09-27
JP2005282571A (ja) 2005-10-13
FR2868119B1 (fr) 2006-06-16
CA2500965A1 (fr) 2005-09-26
US20050242522A1 (en) 2005-11-03
FR2868119A1 (fr) 2005-09-30

Similar Documents

Publication Publication Date Title
EP1580403A1 (de) Dichtring zur Abdichtung zwischen Aussen- und Innengehäuse einer Turbomaschine
CA2802821C (fr) Secteur angulaire de redresseur pour compresseur de turbomachine
EP2334909B1 (de) Dichtung zwischen einer brennkammer und einem turbinenleitapparat in einem turbomotor
EP1607682B1 (de) Gasturbine
EP1818615B1 (de) Ringförmige Brennkammer eines Turbotriebwerks
EP3591178B1 (de) Abdichtungsmodul für turbomaschine
CA2868452C (fr) Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
EP1517005A1 (de) Gasturbine mit einem Abdichtdelement mit Lamellenstruktur
FR2979663B1 (fr) Systeme et procede pour realiser l'etancheite d'un trajet d'ecoulement
FR2967457A1 (fr) Ensemble d'etancheite pour piece de transition
FR2967716A1 (fr) Segment de distributeur de turbomachine ayant un diaphragme integre
EP1517006A1 (de) Gasturbine mit Bürstendichtung
FR2971022A1 (fr) Etage redresseur de compresseur pour une turbomachine
EP1519009A1 (de) Turbomaschine mit Luftentnahme für die Kabine über ein Kugelgelengrohr
FR2992018A1 (fr) Montage d'un distributeur de turbine haute-pression sur une chambre a combustion d'une turbomachine
FR3094031A1 (fr) Ensemble pour une turbomachine
FR2886338A1 (fr) Collecteur d'echappement a double paroi pour moteur a combustion interne
FR2961556A1 (fr) Isolation du carter externe d'une turbine de turbomachine vis-a-vis d'un anneau sectorise
FR3111964A1 (fr) Assemblage d’une pièce de chambre de combustion par recouvrement par une autre pièce
CA2433549A1 (fr) Stator de compresseur axial de turbine a gaz
WO2023242496A1 (fr) Ensemble pour turbomachine
FR3116305A1 (fr) Arbre de liaison d’un corps haute pression d’une turbomachine
FR3126023A1 (fr) Carter d’échappement d’une turbomachine
FR3141207A1 (fr) Anneau d’étanchéité pour turbine démontable par l’amont
FR3093131A1 (fr) Ensemble 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: 20050402

AK Designated contracting states

Kind code of ref document: A1

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

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid

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

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

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20071002