EP1265031A1 - Befestigung von metallischen Aufsätzen auf CMC-Turbomachinenbrennkammerwänden - Google Patents

Befestigung von metallischen Aufsätzen auf CMC-Turbomachinenbrennkammerwänden Download PDF

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Publication number
EP1265031A1
EP1265031A1 EP02291360A EP02291360A EP1265031A1 EP 1265031 A1 EP1265031 A1 EP 1265031A1 EP 02291360 A EP02291360 A EP 02291360A EP 02291360 A EP02291360 A EP 02291360A EP 1265031 A1 EP1265031 A1 EP 1265031A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
walls
axial
external
internal
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
EP02291360A
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English (en)
French (fr)
Other versions
EP1265031B1 (de
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 Moteurs SA
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Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1265031A1 publication Critical patent/EP1265031A1/de
Application granted granted Critical
Publication of EP1265031B1 publication Critical patent/EP1265031B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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 turbomachinery and it is more particularly interested in the problem posed by the mounting of a metal bottom of the combustion chamber of a turbomachine on walls made of CMC type composite material (ceramic matrix composite) from this room.
  • the turbine high pressure including its inlet distributor (HPT nozzle), the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
  • HPT nozzle inlet distributor
  • the system the combustion chamber as well as the casing (also called casing) of this chamber are made of metallic type materials.
  • the use of a chamber entirely metallic proves from a thermal point of view totally unsuitable and it must be resorted to a chamber made from high composite materials CMC type temperature.
  • 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 distributor of the high pressure turbine, the injection system and the remaining casing then produced more conventionally in metallic materials.
  • Gold, metallic materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems, particularly with regard to the connection between composite material walls of the combustion chamber and the chamber bottom metallic.
  • the present invention overcomes these drawbacks by proposing an assembly of metal chamber bottom capable of absorbing induced displacements by the differences in the expansion coefficients between this metallic background and the composite walls of the combustion chamber.
  • An object of the invention is also to produce an assembly having good dynamic strength and good sealing.
  • annular combustion chamber comprising external and internal axial walls of composite material and a chamber bottom of metallic material, said chamber bottom being held in position on said external external and internal walls by fixing means, characterized in that said fixing means pass through annular cavities intended to receive cylindrical end portions of said external and internal axial walls and created between peripheral edges of said chamber bottom and backward facing parts facing them, a determined clearance J between said peripheral edges and the facing faces of said external and internal axial walls being provided so as to allow in operation a free radial expansion of said chamber bottom relative to said axial walls.
  • the fixing means consist of a plurality of bolts, of preferably with captive nut.
  • the external and internal axial walls are provided with a plurality of holes intended to cooperate with said fixing means once these mounted on said chamber bottom.
  • this chamber bottom can further include means for sealing between said bottom of chamber and said axial walls.
  • These sealing means include a seal circular type "lamellae" mounted in a circular groove of said bottom metal chamber and intended to ensure support on said axial wall of the combustion chamber opposite.
  • said circular joint "to slats” has in its downstream part a spoiler intended to provide support O-ring on said axial wall opposite the combustion chamber. He must be segmented and it is kept in abutment against said axial wall by means of a elastic element fixed on said metal chamber bottom. This elastic element consists of a leaf spring.
  • the chamber bottom can integrate in addition internal and external metallic material caps which extend upstream its peripheral edges and allow better control of the dynamic outfit.
  • the fairing (or cap) outer 34 extending upstream (relative to the flow F) the outer wall 26 of the combustion chamber and the internal fairing (or cap) 36 extending upstream (relative to flow F) the internal wall 28 of the combustion are directly integrated into the bottom of the chamber 30 and are therefore made of metallic material (thereby simplifying the general shape of the upstream ends of the combustion chamber which can therefore be formed by simple cylindrical parts).
  • a configuration with a fairing (single monobloc cap in toric shape) connecting the two ends upstream walls of the combustion chamber (and then provided with openings for the passage of the injection nozzles 22) is also possible.
  • the metallic annular bottom 30 of the combustion which has a coefficient of thermal expansion very different from that of external axial 26 and internal 28 walls made of composite material of the combustion, is kept in position on the upstream cylindrical ends of the axial walls by a plurality of fixing means 38, 40 regularly distributed around the longitudinal axis 10.
  • These fixing 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 opposite parts 46, 48 extending the caps 34, 36 towards downstream.
  • the fixing means 38, 40 are formed by a plurality of metal bolts of the captive nut type, i.e. 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 rotation lock of the nut.
  • the tightening when mounting
  • the screw is obtained directly by simply screwing in the screw without the need for the use of special tools for immobilizing the nut in rotation (pliers for example), this being obtained very simply by the single cage Stop.
  • disassembly can also be done very simply so reverse by simply loosening the screw.
  • a clearance J between the internal faces of the external axial 28 and internal 26 walls and the peripheral edges opposite the chamber bottom 30 is calculated so as to allow in operation a free expansion of the metal cap relative to these axial walls of composite material .
  • This play in fact makes it possible to absorb the expansions of the chamber bottom without damaging the axial composite walls which move little radially.
  • the system of double centering of the external 26 and internal 28 walls in the corresponding cavities 42, 44 makes it possible to ensure a relative tightness of the chamber bottom while also serving for the axial maintenance during mounting (cold) as during the flight phases. at cruising speed (hot).
  • these are provided with holes 26a, 28b intended to receive sockets 38d, 40d crossed by the screw axes of the fixing means 38, 40 previously mounted on the chamber bottom, the permanent contact of the screws with the cap 34, 36 limiting the risk of losing the tightening torque during this assembly.
  • These sockets on which the axial walls 26, 28 will slide when the bottom expands chamber 30 further promote the centering and support of these axial walls.
  • FIG. 2 generally illustrates a second embodiment example the detail of which is shown in Figure 2a and in which to ensure better sealing between the external axial wall 26 or internal wall 28 and the chamber bottom 30, a “lamellar” type circular seal 50, 52 is mounted in a circular groove 54, 56 made at the end of the downstream return part 46, 48 of the cap external 34 or internal 36.
  • This seal comprises in its downstream part a spoiler 58, 60 intended to ensure an O-ring support on the opposite axial wall 26, 28 of the combustion chamber.
  • the seal is pressed against the wall by an element elastic 62, 64, preferably a leaf spring, and held in position by a plurality of pins 66, 68 integral with the downstream end of the cap.

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 Befestigung von metallischen Aufsätzen auf CMC-Turbomaschinenbrennkammerwänden Expired - Lifetime EP1265031B1 (de)

Applications Claiming Priority (2)

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

Publications (2)

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

Family

ID=8863995

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02291360A Expired - Lifetime EP1265031B1 (de) 2001-06-06 2002-06-04 Befestigung von metallischen Aufsätzen auf CMC-Turbomaschinenbrennkammerwänden

Country Status (5)

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

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2887015A1 (fr) * 2005-06-14 2006-12-15 Snecma Moteurs Sa Assemblage d'une chambre de combustion annulaire de turbomachine
EP1767858A1 (de) * 2005-09-23 2007-03-28 Snecma Brennkammer mit Verkleidung für eine Gasturbine
EP1775517A2 (de) * 2005-10-12 2007-04-18 General Electric Company Schraubvorrichtung zum Befestigen eines keramischen Liners an einer metallischen Tragstruktur
FR2896575A1 (fr) * 2006-01-26 2007-07-27 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2905166A1 (fr) * 2006-08-28 2008-02-29 Snecma Sa Chambre de combustion annulaire d'une turbomachine.
FR2914399A1 (fr) * 2007-03-27 2008-10-03 Snecma Sa Carenage pour fond de chambre de combustion.
EP1719949A3 (de) * 2005-04-27 2009-09-02 United Technologies Corporation Passende metallische Tragstruktur einer keramischen Gasturbinenbrennkammerwand
EP3115690A1 (de) * 2015-07-06 2017-01-11 General Electric Company Thermisch gekoppelte cmc-brennkammerauskleidung
EP3139094A1 (de) * 2015-09-02 2017-03-08 General Electric Company Brennkammerbaugruppe für einen turbinenmotor
EP3139092A1 (de) * 2015-09-02 2017-03-08 General Electric Company Brennkammerbaugruppe für einen turbinenmotor
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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
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
US7762076B2 (en) * 2005-10-20 2010-07-27 United Technologies Corporation Attachment of a ceramic combustor can
FR2906350B1 (fr) * 2006-09-22 2009-03-20 Snecma Sa Chambre de combustion annulaire d'une turbomachine
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
US10436446B2 (en) 2013-09-11 2019-10-08 General Electric Company Spring loaded and sealed ceramic matrix composite combustor liner
WO2015050629A1 (en) * 2013-10-04 2015-04-09 United Technologies Corporation Combustor panel with multiple attachments
DE102015212573A1 (de) * 2015-07-06 2017-01-12 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer mit integriertem Turbinenvorleitrad sowie Verfahren zu deren Herstellung
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
US11255547B2 (en) * 2018-10-15 2022-02-22 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine
US11293637B2 (en) * 2018-10-15 2022-04-05 Raytheon Technologies Corporation Combustor liner attachment assembly for gas turbine engine

Citations (3)

* Cited by examiner, † Cited by third party
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
EP1152191A2 (de) * 2000-05-05 2001-11-07 General Electric Company Brennkammer mit Brennkammerwand aus Verbundwerkstoff mit keramischer Matrix

Patent Citations (3)

* Cited by examiner, † Cited by third party
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
EP1152191A2 (de) * 2000-05-05 2001-11-07 General Electric Company Brennkammer mit Brennkammerwand aus Verbundwerkstoff mit keramischer Matrix

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7647779B2 (en) 2005-04-27 2010-01-19 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
EP1719949A3 (de) * 2005-04-27 2009-09-02 United Technologies Corporation Passende metallische Tragstruktur einer keramischen Gasturbinenbrennkammerwand
US8122727B2 (en) 2005-04-27 2012-02-28 United Technologies Corporation Compliant metal support for ceramic combustor liner in a gas turbine engine
EP2458282A1 (de) * 2005-04-27 2012-05-30 United Technologies Corporation Nachgebende Metallstütze für Brennkammerwand aus Keramik in einem Gasturbinenmotor
EP1734305A3 (de) * 2005-06-14 2013-05-01 Snecma Ringförmige Brennkammer für eine Turbine
EP1734305A2 (de) * 2005-06-14 2006-12-20 Snecma Ringförmige Brennkammer für eine Turbine
US7849696B2 (en) 2005-06-14 2010-12-14 Snecma Assembling an annular combustion chamber of a turbomachine
FR2887015A1 (fr) * 2005-06-14 2006-12-15 Snecma Moteurs Sa Assemblage d'une chambre de combustion annulaire de turbomachine
FR2891351A1 (fr) * 2005-09-23 2007-03-30 Snecma Chambre de combustion de moteur a turbine a gaz avec carenage
US7617688B2 (en) 2005-09-23 2009-11-17 Snecma Combustion chamber of a gas turbine engine with an upstream fairing for separating the gas stream, annular wall forming a cap of the upstream fairing of the chamber, and gas turbine engine with the chamber
EP1767858A1 (de) * 2005-09-23 2007-03-28 Snecma Brennkammer mit Verkleidung für eine Gasturbine
EP1775517A3 (de) * 2005-10-12 2007-04-25 General Electric Company Schraubvorrichtung zum Befestigen eines keramischen Liners an einer metallischen Tragstruktur
EP1775517A2 (de) * 2005-10-12 2007-04-18 General Electric Company Schraubvorrichtung zum Befestigen eines keramischen Liners an einer metallischen Tragstruktur
FR2896575A1 (fr) * 2006-01-26 2007-07-27 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2905166A1 (fr) * 2006-08-28 2008-02-29 Snecma Sa Chambre de combustion annulaire d'une turbomachine.
US8387395B2 (en) 2006-08-28 2013-03-05 Snecma Annular combustion chamber for a turbomachine
EP1898155A1 (de) * 2006-08-28 2008-03-12 Snecma Ringförmige Brennkammer eines Turbotriebwerks
US7861531B2 (en) 2007-03-27 2011-01-04 Snecma Fairing for a combustion chamber end wall
EP1978305A1 (de) 2007-03-27 2008-10-08 Snecma Verkleidung für den Boden einer Brennkammer
FR2914399A1 (fr) * 2007-03-27 2008-10-03 Snecma Sa Carenage pour fond de chambre de combustion.
US10801729B2 (en) 2015-07-06 2020-10-13 General Electric Company Thermally coupled CMC combustor liner
EP3115690A1 (de) * 2015-07-06 2017-01-11 General Electric Company Thermisch gekoppelte cmc-brennkammerauskleidung
EP3139094A1 (de) * 2015-09-02 2017-03-08 General Electric Company Brennkammerbaugruppe für einen turbinenmotor
EP3139092A1 (de) * 2015-09-02 2017-03-08 General Electric Company Brennkammerbaugruppe für einen turbinenmotor
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US11898494B2 (en) 2015-09-02 2024-02-13 General Electric Company Piston ring assembly for a turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine

Also Published As

Publication number Publication date
FR2825786B1 (fr) 2003-10-17
JP2003021335A (ja) 2003-01-24
US20020184886A1 (en) 2002-12-12
FR2825786A1 (fr) 2002-12-13
EP1265031B1 (de) 2007-09-12
DE60222324D1 (de) 2007-10-25
DE60222324T2 (de) 2008-06-12
JP3984104B2 (ja) 2007-10-03
US6655148B2 (en) 2003-12-02

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