EP1265031B1 - Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine - Google Patents

Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine Download PDF

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Publication number
EP1265031B1
EP1265031B1 EP02291360A EP02291360A EP1265031B1 EP 1265031 B1 EP1265031 B1 EP 1265031B1 EP 02291360 A EP02291360 A EP 02291360A EP 02291360 A EP02291360 A EP 02291360A EP 1265031 B1 EP1265031 B1 EP 1265031B1
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EP
European Patent Office
Prior art keywords
combustion chamber
axially
chamber according
wall
side walls
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
EP02291360A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1265031A1 (fr
Inventor
Gwénaelle Calvez
Didier Hernandez
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
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Filing date
Publication date
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Publication of EP1265031A1 publication Critical patent/EP1265031A1/fr
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Anticipated expiration legal-status Critical
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation

Definitions

  • the present invention relates to the specific field of turbomachines and is more particularly concerned with the problem posed by the mounting of a metal bottom of a combustion chamber of a turbomachine on the walls of composite material of the CMC type (ceramic matrix composite ) of this room.
  • the high pressure turbine including its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the casing (also called envelope) of this chamber are made in metallic type materials.
  • HPT nozzle inlet nozzle
  • the injection system the combustion chamber
  • the casing also called envelope
  • metallic type materials metallic type materials.
  • the use of an all-metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on of high temperature composite materials of the CMC type.
  • these materials being very expensive and of low resistance to high mechanical stress, their use is most often limited to the combustion chamber itself and more particularly to its only axial walls, the inlet valve of the high pressure turbine, the injection system and the housing then remaining more typically made of metal materials.
  • the present invention overcomes these drawbacks by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences of the coefficients of expansion between this metallic background and the composite walls of the combustion chamber.
  • An object of the invention is also to provide a mounting having a good dynamic behavior and a good seal.
  • annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said outer and inner axial walls by fixing means, characterized in that said securing means traverses annular cavities for receiving end cylindrical portions of said outer and inner axial walls and created between peripheral edges of said chamber bottom and downstream facing return portions thereof, a determined clearance J between said peripheral edges and the opposite faces of said external and internal axial walls being provided so as to allow radial free expansion of said chamber bottom with respect to said axial walls in operation, said chamber bottom further comprising means to seal between said chamber bottom and said axial walls.
  • the fastening means are constituted by a plurality of bolts, preferably with a prison nut.
  • the outer and inner axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.
  • the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a support on said axial wall of the combustion chamber opposite.
  • said "slatted" circular seal comprises in its downstream part a spoiler intended to provide an O-bearing on said axial wall facing the combustion chamber. It must be sectored and it is held in abutment against said axial wall by means of an elastic element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.
  • the chamber base can further incorporate inner and outer caps made of metallic material which extend its peripheral edges upstream and allow better control of the dynamic behavior.
  • the outer fairing (or cap) 34 extending upstream (with respect to the flow F) the outer wall 26 of the combustion chamber and the inner fairing (or cap) 36 extending towards the upstream (with respect to the flow F) the internal wall 28 of the combustion chamber are directly integrated in the chamber bottom 30 and are thus made of metal material (simplifying all the general shape of the upstream ends of the combustion chamber) which can therefore consist of simple cylindrical parts).
  • a configuration with a fairing (single pack single piece toric) connecting the two ends of the upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.
  • the metal annular bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the external axial walls 26 and internal 28 of composite material of the combustion chamber, is held in position on the ends cylindrical upstream of the axial walls by a plurality of fastening means 38, 40 regularly distributed about the longitudinal axis 10.
  • These fastening means pass through annular cavities 42, 44, intended to receive the cylindrical end portions of these axial walls. , and created between peripheral edges of the chamber bottom 30 and return portions facing 46, 48 extending the caps 34, 36 downstream.
  • the fastening means 38, 40 are formed by a plurality of metal bolts of prison nut type, that is to say each comprising a screw 38a, a nut 38b and a stop cage 38c fixed on the chamber bottom 30 (advantageously by spot welding) and ensuring a locking in rotation of the nut.
  • the tightening (during assembly) is obtained directly by only screwing the screw without the need for the use of special tools for the immobilization in rotation of the nut (clamp for example), this being obtained very simply by the single stop cage.
  • disassembly can also be done very simply in reverse by simply loosening the screw.
  • a clearance J between the inner faces of the external axial walls 28 and inner 26 and the peripheral edges facing the chamber bottom 30 is calculated so as to allow in operation free expansion of the metal cap with respect to these axial walls of composite material .
  • This game makes it possible to absorb the dilatations of the chamber bottom without damaging the composite axial walls that move little radially.
  • the double-centering system of the outer and inner walls 28 and 28 in the corresponding cavities 42, 44 makes it possible to ensure relative sealing of the chamber bottom while also serving for axial retention during assembly (cold) as during flight phases. in cruising mode (hot).
  • FIG. 2 generally illustrates a second exemplary embodiment whose detail is shown in FIG. 2a and in which to guarantee a better seal between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a circular seal of the type "Slats" 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return portion 46, 48 of the outer cap 34 or inner 36.
  • This seal comprises in its downstream portion a spoiler 58, 60 for providing a toric support on the wall axial facing 26, 28 of the combustion chamber.
  • the seal is pressed against the wall by an elastic element 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 secured to the downstream end of the cap.
  • the clearance between the peripheral edges of the chamber bottom and the inner faces of the axial walls is determined to allow the expansion of the chamber bottom to be absorbed without damaging the axial walls made of composite material.
  • the seal sealing with the outer axial wall is prestressed cold and the sealant with the inner wall is brought into contact only. Hot, it is the opposite because of the differences in expansion between the metal chamber bottom and the inner and outer walls.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP02291360A 2001-06-06 2002-06-04 Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine Expired - Lifetime EP1265031B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107374 2001-06-06
FR0107374A FR2825786B1 (fr) 2001-06-06 2001-06-06 Fixation de casquettes metalliques sur des parois de chambre de combustion cmc de turbomachine

Publications (2)

Publication Number Publication Date
EP1265031A1 EP1265031A1 (fr) 2002-12-11
EP1265031B1 true EP1265031B1 (fr) 2007-09-12

Family

ID=8863995

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02291360A Expired - Lifetime EP1265031B1 (fr) 2001-06-06 2002-06-04 Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine

Country Status (5)

Country Link
US (1) US6655148B2 (ja)
EP (1) EP1265031B1 (ja)
JP (1) JP3984104B2 (ja)
DE (1) DE60222324T2 (ja)
FR (1) FR2825786B1 (ja)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6904757B2 (en) * 2002-12-20 2005-06-14 General Electric Company Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor
US6895761B2 (en) * 2002-12-20 2005-05-24 General Electric Company Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor
FR2855249B1 (fr) * 2003-05-20 2005-07-08 Snecma Moteurs Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre
US7237389B2 (en) * 2004-11-18 2007-07-03 Siemens Power Generation, Inc. Attachment system for ceramic combustor liner
US7647779B2 (en) 2005-04-27 2010-01-19 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
FR2887015B1 (fr) * 2005-06-14 2010-09-24 Snecma Moteurs Assemblage d'une chambre de combustion annulaire de turbomachine
FR2891351B1 (fr) 2005-09-23 2007-12-07 Snecma Chambre de combustion de moteur a turbine a gaz avec carenage
US7546743B2 (en) * 2005-10-12 2009-06-16 General Electric Company Bolting configuration for joining ceramic combustor liner to metal mounting attachments
US7762076B2 (en) * 2005-10-20 2010-07-27 United Technologies Corporation Attachment of a ceramic combustor can
FR2896575B1 (fr) * 2006-01-26 2013-01-18 Snecma Chambre de combustion annulaire d'une turbomachine
FR2905166B1 (fr) * 2006-08-28 2008-11-14 Snecma Sa Chambre de combustion annulaire d'une turbomachine.
FR2906350B1 (fr) * 2006-09-22 2009-03-20 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.
US9127565B2 (en) * 2008-04-16 2015-09-08 Siemens Energy, Inc. Apparatus comprising a CMC-comprising body and compliant porous element preloaded within an outer metal shell
CA2922569C (en) 2013-09-11 2018-02-20 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
US20160245518A1 (en) * 2013-10-04 2016-08-25 United Technologies Corporation Combustor panel with multiple attachments
US10801729B2 (en) * 2015-07-06 2020-10-13 General Electric Company Thermally coupled CMC combustor liner
DE102015212573A1 (de) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US10168051B2 (en) * 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US10197278B2 (en) 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US10281153B2 (en) * 2016-02-25 2019-05-07 General Electric Company Combustor assembly
US10393380B2 (en) * 2016-07-12 2019-08-27 Rolls-Royce North American Technologies Inc. Combustor cassette liner mounting assembly
US20180051880A1 (en) * 2016-08-18 2018-02-22 General Electric Company Combustor assembly for a turbine engine
US10837640B2 (en) 2017-03-06 2020-11-17 General Electric Company Combustion section of a gas turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
US11293637B2 (en) * 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11255547B2 (en) * 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine

Family Cites Families (3)

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Publication number Priority date Publication date Assignee Title
US3911672A (en) * 1974-04-05 1975-10-14 Gen Motors Corp Combustor with ceramic liner
US5291732A (en) * 1993-02-08 1994-03-08 General Electric Company Combustor liner support assembly
US6397603B1 (en) * 2000-05-05 2002-06-04 The United States Of America As Represented By The Secretary Of The Air Force Conbustor having a ceramic matrix composite liner

Also Published As

Publication number Publication date
EP1265031A1 (fr) 2002-12-11
DE60222324D1 (de) 2007-10-25
DE60222324T2 (de) 2008-06-12
JP3984104B2 (ja) 2007-10-03
FR2825786A1 (fr) 2002-12-13
US6655148B2 (en) 2003-12-02
US20020184886A1 (en) 2002-12-12
FR2825786B1 (fr) 2003-10-17
JP2003021335A (ja) 2003-01-24

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