EP1265036A1 - Elastische Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff in einem metallischen Gehäuse - Google Patents

Elastische Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff in einem metallischen Gehäuse Download PDF

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Publication number
EP1265036A1
EP1265036A1 EP02291365A EP02291365A EP1265036A1 EP 1265036 A1 EP1265036 A1 EP 1265036A1 EP 02291365 A EP02291365 A EP 02291365A EP 02291365 A EP02291365 A EP 02291365A EP 1265036 A1 EP1265036 A1 EP 1265036A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
seal
turbomachine according
composite material
turbomachine
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
EP02291365A
Other languages
English (en)
French (fr)
Other versions
EP1265036B1 (de
Inventor
Pierre Camy
Benoít Carrere
Eric Conete
Alexandre Forestier
Georges Habarou
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
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 Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1265036A1 publication Critical patent/EP1265036A1/de
Application granted granted Critical
Publication of EP1265036B1 publication Critical patent/EP1265036B1/de
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
    • F23R3/42—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
    • 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
    • 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
    • F05B2230/00—Manufacture
    • F05B2230/60—Assembly methods
    • F05B2230/604—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins
    • F05B2230/606—Assembly methods using positioning or alignment devices for aligning or centering, e.g. pins using maintaining alignment while permitting differential dilatation

Definitions

  • the present invention relates to the specific field of turbomachinery and it is more particularly interested in the problem posed by the assembly of a CMC type composite material combustion chamber (ceramic matrix composite) in the metal casing of a turbomachine.
  • the turbine high pressure in particular its inlet distributor (HPT nozzle), the combustion as well as the casing (also called envelope) of this chamber are made of the same material, generally metallic.
  • HPT nozzle inlet distributor
  • the combustion as well as the casing (also called envelope) of this chamber are made of the same material, generally metallic.
  • the use of a metal chamber proves from a thermal point of view totally unsuitable and it must be resorted to a chamber based on CMC type high temperature composite materials.
  • the difficulties of using these materials and their cost mean that their use is most often limited to the combustion chamber itself, the inlet distributor of the high pressure turbine and the housing then remaining more conventionally made of metallic materials.
  • the materials metallic and composite materials have coefficients of expansion very different thermal. This results in particularly acute problems of connection between the crankcase and the combustion and interface chamber at the distributor, at the inlet of the high pressure turbine.
  • the present invention overcomes these drawbacks by proposing an assembly of the combustion chamber in the crankcase having the capacity to absorb the displacements induced by the differences in the expansion coefficients of these rooms.
  • An object of the invention is also to propose an assembly which allows a simplification of the manufacture of the combustion chamber.
  • a turbomachine comprising, in a annular envelope of metallic material and in a direction F of flow of gas, a fuel injection assembly, a combustion chamber ring of composite material having a longitudinal axis and a distributor ring made of metallic material forming the input stage with fixed blades of a high pressure turbine, characterized in that said combustion chamber in composite material is held in position in said annular casing metallic by a plurality of tongues of elastic material, regularly distributed around said combustion chamber, each of these tabs having three branches connected in a star, the ends of two of these three branches being fixed integrally at a downstream end of said chamber combustion of composite material, opposite to said injection system, by first and second fastening means and the end of the last of these three branches being fixed integrally to said envelope metallic ring by third fastening means, the elasticity of said fastening tabs allow high expansion at high temperatures radial of said combustion chamber with respect to said annular casing.
  • the first, second and third fixing means each preferably consists of a plurality of bolts.
  • the third means of fixing are constituted by a plurality of bolts, the first and second fastening means each preferably consisting of a plurality of crimping elements.
  • the turbomachine of the invention further comprises a closing ring of ceramic composite material fixed integrally to said downstream end of said combustion chamber and intended to form a plane support for a seal ensuring the seal between said chamber combustion and said distributor.
  • This closing ring is preferably brazed on said downstream end of the combustion chamber. It may include a return part arranged in the extension of the wall of the combustion.
  • the support plane of the seal is formed in a plane perpendicular to said longitudinal axis of said combustion chamber.
  • the support plane of the seal is formed in a plane parallel to said longitudinal axis of said combustion chamber.
  • the seal is preferably the “omega” joint type.
  • the support plane of the seal is formed in an inclined plane relative to said axis longitudinal of said combustion chamber.
  • the seal sealing is preferably of the type "lamellar" seal held against said closing ring by means of an elastic element integral with said dispenser.
  • this seal may include a plurality of leakage orifices calibrated.
  • Passage orifices 54, 56 formed in the metal platforms external 46 and internal 48 of the distributor 42 are further provided to ensure cooling of the stationary vanes 44 of the distributor at the inlet of the turbine rotor high pressure from the compressed oxidizer available at the outlet of the diffusion 18 and flowing in two streams F1, F2 on either side of the combustion 24.
  • These fixing tabs are mounted for a first part of them (see tab referenced 58) between the annular envelope external 12 and the external axial wall 26 of the combustion chamber and for a second part (like the tongue 60) between the internal annular envelope 14 and the internal axial wall 28 of the combustion chamber.
  • Each flexible fixing tab made of metallic material for example the tongue 58 shown in Figure 3, consists of three branches connected in a star to present a general shape of Y with three attachment points, the ends 62a, 62b; 64a, 64b of two of these three branches being fixed integrally at a downstream end, opposite the injection system 20, forming flange 68, 70 (i.e.
  • a closing ring made of ceramic composite material 84, 86 is fixedly held, for example by soldering, against the flange 68, 70 of the chamber combustion to form a support surface for a circular seal “omega” type 88, 90 mounted in a groove 92, 94 of each of the platforms external 46 and internal 48 of the dispenser and intended to ensure sealing between the combustion chamber 24 and the distributor 42.
  • this ferrule allows for its sufficient thickness to "drown" the screw heads of the first 72a, 74a and seconds 72b, 74b fixing means.
  • FIG. 4 illustrates a second embodiment of the invention in which the downstream end of the combustion chamber no longer has a flange configuration, perpendicular to the longitudinal axis of the chamber combustion, but on the contrary a configuration either parallel to this axis or inclined with respect to it (this inclination can go up to 90 °).
  • These non-perpendicular configurations of the downstream end of the chamber provide improvement in the manufacturing of the chamber walls by allowing in particular better densification of the material on the shelves.
  • the downstream end 70 of the internal axial wall 28 of the combustion chamber has a configuration parallel to the axis longitudinal 10 of this chamber (see the detail in FIG. 6) and comes to bear radial, via the ferrule made of composite material 86, against the circular platform internal 48 of the distributor.
  • this platform is provided with a groove 94 in which is housed a gasket 90 of type "omega" intended to ensure the seal between the combustion chamber 24 and the distributor 42, at the level of the internal axial wall of this chamber.
  • a gasket 90 of type "omega" intended to ensure the seal between the combustion chamber 24 and the distributor 42, at the level of the internal axial wall of this chamber.
  • a ferrule made of composite material 84 is preferably brazed on the downstream end to form a support plane for a seal ensuring the seal between the combustion chamber 24 and the distributor 42, at the level this time from the outer axial wall of this chamber.
  • the joint now consists of a circular joint of "slat" type 106 held against an elastic element 108, preferably a leaf spring, integral with the distributor.
  • FIG. 5A illustrates another variant of an embodiment of the invention in which the attachment of the tabs 58 to the downstream end of the combustion chamber 68 is effected by a crimped connection, the bolts 72a, 72b being replaced by crimping elements 72c, 72d.
  • the closing ring 84 is advantageously provided with a chamber 84a return part arranged in the extension of the outer wall 26 of the combustion chamber.
  • orifices of leakage calibrated 110 are provided at the seal 106.
  • Figure 4 shows a configuration with one end downstream of the parallel internal axial wall and a downstream end of the external wall inclined by about 45 °, it is of course quite possible to predict the reverse configuration with a downstream end of the parallel external axial wall and a downstream end of the inclined inner wall.
  • the flexibility of the fixing tabs 58, 60 makes it possible to support the difference in thermal expansion occurring at high temperatures between the combustion chamber made of composite material and the annular casing while ensuring the maintenance and positioning of this chamber.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gasket Seals (AREA)
EP02291365A 2001-06-06 2002-06-04 Elastische Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff in einem metallischen Gehäuse Expired - Lifetime EP1265036B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107361A FR2825781B1 (fr) 2001-06-06 2001-06-06 Montage elastique de chambre ce combustion cmc de turbomachine dans un carter metallique
FR0107361 2001-06-06

Publications (2)

Publication Number Publication Date
EP1265036A1 true EP1265036A1 (de) 2002-12-11
EP1265036B1 EP1265036B1 (de) 2008-10-22

Family

ID=8863985

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02291365A Expired - Lifetime EP1265036B1 (de) 2001-06-06 2002-06-04 Elastische Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff in einem metallischen Gehäuse

Country Status (5)

Country Link
US (1) US6732532B2 (de)
EP (1) EP1265036B1 (de)
JP (1) JP4031292B2 (de)
DE (1) DE60229466D1 (de)
FR (1) FR2825781B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2423601A1 (de) * 2010-08-24 2012-02-29 Nuovo Pignone S.p.A. Konzentrische Brennkammerwandhalterung und Verfahren

Families Citing this family (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2840974B1 (fr) * 2002-06-13 2005-12-30 Snecma Propulsion Solide Anneau d'etancheite pour cahmbre de combustion et chambre de combustion comportant un tel anneau
US6775985B2 (en) * 2003-01-14 2004-08-17 General Electric Company Support assembly for 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
FR2860039B1 (fr) * 2003-09-19 2005-11-25 Snecma Moteurs Realisation de l'etancheite dans un turboreacteur pour le prelevement cabine par joints double sens a lamelles
FR2871847B1 (fr) * 2004-06-17 2006-09-29 Snecma Moteurs Sa Montage d'un distributeur de turbine sur une chambre de combustion a parois en cmc dans une turbine a gaz
FR2871846B1 (fr) * 2004-06-17 2006-09-29 Snecma Moteurs Sa Chambre de combustion en cmc de turbine a gaz supportee dans un carter metallique par des organes de liaison en cmc
GB2422874A (en) * 2005-02-05 2006-08-09 Alstom Technology Ltd Gas turbine burner expansion bar structure
US7546743B2 (en) * 2005-10-12 2009-06-16 General Electric Company Bolting configuration for joining ceramic combustor liner to metal mounting attachments
FR2892181B1 (fr) * 2005-10-18 2008-02-01 Snecma Sa Fixation d'une chambre de combustion a l'interieur de son carter
US7493771B2 (en) * 2005-11-30 2009-02-24 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7637110B2 (en) * 2005-11-30 2009-12-29 General Electric Company Methods and apparatuses for assembling a gas turbine engine
US7523616B2 (en) * 2005-11-30 2009-04-28 General Electric Company Methods and apparatuses for assembling a gas turbine engine
FR2897418B1 (fr) 2006-02-10 2013-03-01 Snecma Chambre de combustion annulaire d'une turbomachine
US8863528B2 (en) * 2006-07-27 2014-10-21 United Technologies Corporation Ceramic combustor can for a gas turbine engine
FR2919380B1 (fr) * 2007-07-26 2013-10-25 Snecma Chambre de combustion d'une turbomachine.
US20090067917A1 (en) * 2007-09-07 2009-03-12 The Boeing Company Bipod Flexure Ring
JP5276345B2 (ja) * 2008-03-28 2013-08-28 三菱重工業株式会社 ガスタービン及びガスタービンの燃焼器挿入孔形成方法
US8919134B2 (en) * 2011-01-26 2014-12-30 United Technologies Corporation Intershaft seal with support linkage
US9335051B2 (en) * 2011-07-13 2016-05-10 United Technologies Corporation Ceramic matrix composite combustor vane ring assembly
CN104246196A (zh) * 2012-04-27 2014-12-24 通用电气公司 连接燃气涡轮发动机环形部件
US9435266B2 (en) 2013-03-15 2016-09-06 Rolls-Royce North American Technologies, Inc. Seals for a gas turbine engine
JP6228685B2 (ja) 2013-09-11 2017-11-08 ゼネラル・エレクトリック・カンパニイ ばねで荷重されシールされるセラミックマトリックス複合材燃焼器ライナ
US9404421B2 (en) 2014-01-23 2016-08-02 Siemens Energy, Inc. Structural support bracket for gas flow path
US20170059165A1 (en) * 2015-08-28 2017-03-02 Rolls-Royce High Temperature Composites Inc. Cmc cross-over tube

Citations (5)

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Publication number Priority date Publication date Assignee Title
US2509503A (en) * 1946-02-12 1950-05-30 Lucas Ltd Joseph Combustion chamber for prime movers
GB2035474A (en) * 1978-11-09 1980-06-18 Sulzer Ag Seals
GB1570875A (en) * 1977-03-16 1980-07-09 Lucas Industries Ltd Combustion equipment
EP1035377A2 (de) * 1999-03-08 2000-09-13 Mitsubishi Heavy Industries, Ltd. Abdichtung für das Endstück einer Gasturbinenbrennkammer
US6131384A (en) * 1997-10-16 2000-10-17 Rolls-Royce Deutschland Gmbh Suspension device for annular gas turbine combustion chambers

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US2268464A (en) * 1939-09-29 1941-12-30 Bbc Brown Boveri & Cie Combustion chamber
US4688378A (en) * 1983-12-12 1987-08-25 United Technologies Corporation One piece band seal
US4821522A (en) * 1987-07-02 1989-04-18 United Technologies Corporation Sealing and cooling arrangement for combustor vane interface
US5291733A (en) * 1993-02-08 1994-03-08 General Electric Company Liner mounting 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
US6334298B1 (en) * 2000-07-14 2002-01-01 General Electric Company Gas turbine combustor having dome-to-liner joint

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2509503A (en) * 1946-02-12 1950-05-30 Lucas Ltd Joseph Combustion chamber for prime movers
GB1570875A (en) * 1977-03-16 1980-07-09 Lucas Industries Ltd Combustion equipment
GB2035474A (en) * 1978-11-09 1980-06-18 Sulzer Ag Seals
US6131384A (en) * 1997-10-16 2000-10-17 Rolls-Royce Deutschland Gmbh Suspension device for annular gas turbine combustion chambers
EP1035377A2 (de) * 1999-03-08 2000-09-13 Mitsubishi Heavy Industries, Ltd. Abdichtung für das Endstück einer Gasturbinenbrennkammer

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2423601A1 (de) * 2010-08-24 2012-02-29 Nuovo Pignone S.p.A. Konzentrische Brennkammerwandhalterung und Verfahren

Also Published As

Publication number Publication date
US6732532B2 (en) 2004-05-11
FR2825781B1 (fr) 2004-02-06
FR2825781A1 (fr) 2002-12-13
EP1265036B1 (de) 2008-10-22
DE60229466D1 (de) 2008-12-04
US20020184890A1 (en) 2002-12-12
JP4031292B2 (ja) 2008-01-09
JP2003021334A (ja) 2003-01-24

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