EP1580402B1 - Turbomachine comprenant deux sous-ensembles assemblés sous contraint axiale - Google Patents

Turbomachine comprenant deux sous-ensembles assemblés sous contraint axiale Download PDF

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Publication number
EP1580402B1
EP1580402B1 EP05290663A EP05290663A EP1580402B1 EP 1580402 B1 EP1580402 B1 EP 1580402B1 EP 05290663 A EP05290663 A EP 05290663A EP 05290663 A EP05290663 A EP 05290663A EP 1580402 B1 EP1580402 B1 EP 1580402B1
Authority
EP
European Patent Office
Prior art keywords
turboshaft engine
annular
engine according
subassemblies
chamber
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.)
Active
Application number
EP05290663A
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German (de)
English (en)
French (fr)
Other versions
EP1580402A1 (fr
Inventor
Claude Lejars
Marica Mesic
Bruce Pontoizeau
Alexandre Roy
Patrice Suet
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 EP1580402A1 publication Critical patent/EP1580402A1/fr
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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
    • F01D11/005—Sealing means between non relatively rotating elements

Definitions

  • the invention generally relates to a turbomachine, in particular a turbocharger charged with supplying combustion air, under pressure, to the combustion chamber of a jet engine. It relates more particularly to an improvement reinforcing the tightness of the junction between two subassemblies of such a machine, for example the junction under stress between a housing and a fixed blade support of the stator.
  • the stator is assembled to an outer casing.
  • two subassemblies, the housing and the stator are shaped to define between them an annular chamber in which is inserted a seal. It is supported between two annular walls vis-à-vis belonging respectively to the two subassemblies.
  • the two annular parts in contact with the two subassemblies are applied against each other with axial stress.
  • a turbomachine according to the prior art is known in the document FR 2646221 .
  • the constraint can be expressed in millimeters, this value designating the axial interference that would exist between the two subsets, if they were not abutting under stress. Hitherto, relatively low stresses have been implemented, conventionally of the order of 0.3 mm. More recently, this mounting stress has been raised to 0.75 mm.
  • the chamber housing the seal can open under the effect of deformation of thermal origin. Moreover, in operation the seal undergoes deformations and wear that can go as far as the loss of fragments which, driven by the pressure difference, are jammed between the facing faces of the annular chamber. These faces are damaged and air leaks increase.
  • the invention aims to prevent the opening of the chamber to prevent the release of pieces of the seal and the degradation of the surfaces against which it rests.
  • the invention relates to a turbomachine comprising at least two subsets assembled to one another and defining between them an annular chamber housing a seal, wherein two annular contacting parts respectively belonging to the two sub-assemblies. sets and defining said chamber are urged towards each other, in a manner known per se, with axial constraint and characterized in that an annular spacer is inserted between their abutting surfaces.
  • the axial stress can be significantly increased. It may especially be between 1.5 and 3 mm. A presently preferred stress value is close to 2.25 mm.
  • This strong mounting constraint makes it possible to absorb variations of thermal origin and thus prevents the opening of the chamber and the destruction of the seal.
  • This piece is inexpensive and easy to change if it is damaged. Therefore, both sub-assemblies are protected and no longer risk being damaged.
  • the arrangement is such that the contact area between the two abutting subsets is increased. This results in a decrease in the matting pressure and a better behavior vis-à-vis the relative displacements between the subsets.
  • the invention is particularly applicable to the connection between an outer casing and a stator element carrying the blades of a turbocharger.
  • FIG. 1 a portion of a turbocharger 11 forming part of an aircraft engine reactor.
  • Two subassemblies 14,16 are assembled under axial stress by defining between them an annular chamber 18 inside which is inserted a seal 20.
  • the subassembly 14 constitutes an outer casing while the subassembly 16 constitutes the support of a plurality of vanes 22 of the turbocharger.
  • the unrepresented blades are located between the blades.
  • the fixed blade support consists of several segments 26 assembled end to end, each segment carrying a series of blades. The entire support is fixed to an inner casing 27.
  • This inner casing extends radially outwards by three annular rings, a first ring 30 is fixed by a bolt assembly 31 to a first inner frame 32 of the outer casing, a second ring 34 bears unrestrained against a second frame 36 of the outer casing, extending inwardly.
  • the third ring 37 is fixed by a set of bolts 38 to an inner frame 39 of the outer casing 14.
  • the second ring 34 comprises a flat annular surface 40 extending radially inwards, extended by an axial cylindrical portion 42 bearing by its circular field 43 against said second frame 36. More particularly, it comprises another flat annular surface 45 facing that of the crown, surmounted by an approximately tubular protrusion 46 coming to cover play with an outer cylindrical portion of the second ring.
  • This arrangement therefore defines the annular chamber 18 within which the gasket 20 which is supported between the two flat surfaces 40, 45 is installed.
  • the sizing of the subassemblies 14, 16 is such that the mounting is performed with a constraint caused by the tightening of the bolts 31.
  • the invention appears in FIG. 3 and proposes to arrange an annular spacer 50 between the abutting surfaces of the two subassemblies, that is to say here between the circular field 43 of the ring 34 and the circular end of the flat surface 45 of the frame 36.
  • This piece 50 increases the mounting stress which can now be between 1.5 mm and 3 mm, typically around 2.25 mm.
  • the intermediate part 50 is shaped to increase the contact surface at the end of at least one of the annular parts, in this case more particularly the flat surface 45 of said second frame 36.
  • the axial cylindrical portion 42 of the ring gear makes it possible to guide the positioning of the intermediate piece 50 because the latter comprises a cylindrical surface 52 fitting on said cylindrical portion 42.
  • a radial portion 54 of the intermediate piece takes bearing against the flat surface 45 of said second chord.
  • the radial section of the insert 50 is in the shape of an L.
  • the insert can undergo a surface treatment, before mounting, reinforcing its strength.
  • the treatment may especially relate to the radial portion 54. It is therefore not necessary to apply a treatment of this kind to the crown or chord.
  • the spacer 50a is extended by a deflector portion 56, inwardly.
  • this part has a substantially conical shape.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05290663A 2004-03-26 2005-03-25 Turbomachine comprenant deux sous-ensembles assemblés sous contraint axiale Active EP1580402B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0403128 2004-03-26
FR0403128A FR2868125B1 (fr) 2004-03-26 2004-03-26 Turbomachine comprenant deux sous-ensembles assembles sous contrainte axiale

Publications (2)

Publication Number Publication Date
EP1580402A1 EP1580402A1 (fr) 2005-09-28
EP1580402B1 true EP1580402B1 (fr) 2007-07-18

Family

ID=34855166

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05290663A Active EP1580402B1 (fr) 2004-03-26 2005-03-25 Turbomachine comprenant deux sous-ensembles assemblés sous contraint axiale

Country Status (9)

Country Link
US (1) US7571614B2 (ru)
EP (1) EP1580402B1 (ru)
JP (1) JP4643326B2 (ru)
CA (1) CA2500947C (ru)
DE (1) DE602005001641T2 (ru)
ES (1) ES2290863T3 (ru)
FR (1) FR2868125B1 (ru)
RU (1) RU2380546C2 (ru)
UA (1) UA86354C2 (ru)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2898641B1 (fr) * 2006-03-17 2008-05-02 Snecma Sa Habillage de carter dans un turboreacteur
US8393855B2 (en) * 2007-06-29 2013-03-12 General Electric Company Flange with axially curved impingement surface for gas turbine engine clearance control
US8197186B2 (en) * 2007-06-29 2012-06-12 General Electric Company Flange with axially extending holes for gas turbine engine clearance control
US8998573B2 (en) * 2010-10-29 2015-04-07 General Electric Company Resilient mounting apparatus for low-ductility turbine shroud
EP2886802B1 (fr) * 2013-12-20 2019-04-10 Safran Aero Boosters SA Joint de virole interne de dernier étage de compresseur de turbomachine axiale
US10202863B2 (en) 2016-05-23 2019-02-12 United Technologies Corporation Seal ring for gas turbine engines
US10392967B2 (en) 2017-11-13 2019-08-27 General Electric Company Compliant seal component and associated method

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
LU86209A1 (fr) * 1985-12-12 1987-01-13 Euratom Systeme d'etancheite entre deux brides metalliques
FR2646221B1 (fr) * 1989-04-19 1991-06-14 Snecma Joint d'etancheite, dispositif le comportant et application a une turbomachine
FR2695164B1 (fr) * 1992-08-26 1994-11-04 Snecma Turbomachine munie d'un dispositif empêchant une circulation longitudinale de gaz autour des étages d'aubes de redressement.
JPH076407B2 (ja) * 1992-08-26 1995-01-30 ゼネラル・エレクトリック・カンパニイ ターボシャフトエンジン
FR2766517B1 (fr) * 1997-07-24 1999-09-03 Snecma Dispositif de ventilation d'un anneau de turbomachine
JPH11343809A (ja) * 1998-06-02 1999-12-14 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンのタービンシュラウド部のシール構造
US6402466B1 (en) * 2000-05-16 2002-06-11 General Electric Company Leaf seal for gas turbine stator shrouds and a nozzle band
US6450762B1 (en) * 2001-01-31 2002-09-17 General Electric Company Integral aft seal for turbine applications
US6612809B2 (en) * 2001-11-28 2003-09-02 General Electric Company Thermally compliant discourager seal
RU2302534C2 (ru) * 2001-12-11 2007-07-10 Альстом (Свитзерлэнд) Лтд. Газотурбинное устройство
US6568903B1 (en) * 2001-12-28 2003-05-27 General Electric Company Supplemental seal for the chordal hinge seals in a gas turbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US7571614B2 (en) 2009-08-11
RU2005108494A (ru) 2006-09-27
FR2868125B1 (fr) 2006-07-21
EP1580402A1 (fr) 2005-09-28
CA2500947C (fr) 2012-11-20
JP4643326B2 (ja) 2011-03-02
ES2290863T3 (es) 2008-02-16
DE602005001641D1 (de) 2007-08-30
US20050260066A1 (en) 2005-11-24
DE602005001641T2 (de) 2008-06-05
RU2380546C2 (ru) 2010-01-27
JP2005291203A (ja) 2005-10-20
CA2500947A1 (fr) 2005-09-26
UA86354C2 (ru) 2009-04-27
FR2868125A1 (fr) 2005-09-30

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