EP1265033B1 - Brennkammer mit einer Befestigungsanordnung der Kammerendwand - Google Patents

Brennkammer mit einer Befestigungsanordnung der Kammerendwand Download PDF

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Publication number
EP1265033B1
EP1265033B1 EP02291362A EP02291362A EP1265033B1 EP 1265033 B1 EP1265033 B1 EP 1265033B1 EP 02291362 A EP02291362 A EP 02291362A EP 02291362 A EP02291362 A EP 02291362A EP 1265033 B1 EP1265033 B1 EP 1265033B1
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EP
European Patent Office
Prior art keywords
combustion chamber
end wall
chamber according
side walls
fixed
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
EP02291362A
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English (en)
French (fr)
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EP1265033A1 (de
Inventor
Gwénaelle Calvez
Didier Hernandez
Alexandre Forestier
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
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SNECMA SAS
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Publication date
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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
    • 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.
  • a combustion chamber is known from US 5,291,732 .
  • the high pressure turbine in particular its inlet nozzle (HPT nozzle), the injection system, the combustion chamber and the annular envelope of this chamber are made of metal type.
  • HPT nozzle inlet nozzle
  • the injection system, the combustion chamber and the annular envelope of this chamber are made of metal type.
  • 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.
  • the difficulties of implementation and the cost of these materials mean that 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 annular envelope then remaining more typically made of metal materials.
  • metal materials and composite materials have very different coefficients of thermal expansion. This results in particularly acute problems especially at the level of the connection between the composite material walls of the combustion chamber and the metal chamber bottom.
  • the present invention overcomes these disadvantages by proposing a metal chamber bottom assembly having the capacity to absorb the displacements induced by the differences in the coefficients of expansion between this metal bottom and the composite walls of the combustion chamber.
  • annular combustion chamber comprising outer and inner axial walls of composite material and a chamber bottom of metallic material, characterized in that to allow radial free expansion of said chamber bottom with respect to said axial walls, said chamber bottom is held in position between said axial walls by a plurality of flexible tongues fixed on the one hand to said axial walls by fixing means and on the other hand to said bottom chamber by soldering or welding, said chamber bottom comprising besides means for sealing between said chamber bottom and said axial walls.
  • the flexible fastening tabs are made of a metallic material and the fastening means consist of a plurality of bolts, preferably with a prison nut.
  • the sealing means comprise a "slat" type circular seal mounted in a circular groove of said metal chamber bottom and intended to provide a bearing on said axial wall of the combustion chamber opposite.
  • the circular seal is sectored and is held in abutment against said axial wall by means of a resilient element fixed on said metal chamber bottom. This elastic element is constituted by a leaf spring.
  • the sealing means comprise a circular segment mounted against said axial wall and intended to cooperate with a circular groove of said metal chamber bottom.
  • this circular sealing segment is split.
  • the flexible tongues of attachment comprise a first end fixed to one or the other of said axial walls by said fixing means and a second end fixed by soldering or welding to said chamber bottom.
  • the chamber bottom may comprise in addition a metal ring on which are brazed or welded said second ends of said flexible fastening tongues.
  • the flexible fastening tabs comprise a first end attached to one of said axial walls by first connecting means a second end attached to the other of said axial walls by second connecting means and a part central fixed to the bottom of the chamber by soldering or welding.
  • these flexible fastening tabs are disposed between each of the injection nozzles.
  • the metal bottom 30 of the combustion chamber which has a coefficient of thermal expansion very different from that of the axial walls outer 26 and inner 28 of composite material of the combustion chamber, is fixedly held in position between these axial walls by a plurality of flexible tabs 36, 38 regularly distributed between the fuel injection nozzles 22 (see for example the figure 4 ).
  • These fixing tabs are mounted for a first series of them (see the tab referenced 36) between the metal bottom 30 and the outer axial wall 26 and for a second series of them (see the tab referenced 38) between the metal base 30 and the inner axial wall 28.
  • Each flexible fastening tongue is made of a metallic material and is preferably constituted by a thin blade, of constant width or not, having a point of attachment at each of its two ends. .
  • first end 42; 44 of the fastening tongue is fixed integrally and according to its location at one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by first fixing means 46; 48 and the second end 50; 52 is preferably fixed by welding or brazing to a metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber.
  • This attachment absorbs the dilatations of the chamber bottom without damaging the composite axial walls that move little radially.
  • the first fastening means disposed offset from the injection nozzles are advantageously bolt type. And, to facilitate access and assembly / disassembly, these bolts are preferably chosen to type prison nut.
  • the seal between the outer or inner axial wall and the metal ring is provided by a "slat" type circular seal 58; 60 mounted in a circular groove 62; 64 of the metal crown.
  • This advantageously sectored seal comprises in its upstream part a spigot 66; 68 for providing an O-bearing on the facing axial wall 26; 28 of the combustion chamber.
  • the seal is pressed against the wall by an elastic member 70; 72, preferably a leaf spring, and held in position by a plurality of pins 74; 76 integral with the crown.
  • the clearance between the outer peripheral edge 78 of the chamber floor (and the edge corresponding of the metal ring) is calculated so that, in operation, the metal ring does not come to compress the outer axial wall 26 of composite material or simply does not come into contact with it.
  • the seal 60 sealing with the inner axial wall 28 is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.
  • the figure 2 illustrates a first variant embodiment of the attachment of the metal chamber bottom to the axial walls made of composite material of the combustion chamber, in which the chamber bottom and the metal crowns of the fixing tongues form a single piece 80 on which will be soldered or soldered directly the second ends of the tabs 50; 52.
  • This unique piece of course incorporates the previous sealing means.
  • a second variant is illustrated in figures 3 and 4 in which there is only one set of tongues 82, a first end 84 of which is fixed to the outer axial wall 26 by first connecting means 86 and a second end 88 is fixed to the inner axial wall 28 by means of second connecting means 90.
  • first and second connecting means are advantageously of the bolt type.
  • the tongue is further brazed (or welded) to the chamber bottom which may for example be formed by the single piece 80 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.
  • FIG 5 illustrates a second embodiment (see also the detail of Figure Sa) in which the seal between the outer axial wall 26 or inner 28 and the chamber bottom 30 is no longer provided by a "slats" type circular seal But by a split circular segment (open) 92; 94 mounted tight against the axial wall, provided with a sealing system and intended to cooperate with a circular groove 96; 98 of the metal ring 54, 56.
  • the clearance at the bottom of the groove 96 housing the outer segment 92 is calculated so that, in operation, the metal ring does not come into contact with the outer axial wall 26 of material composite, or with the inner face 92a of the segment 92.
  • the segment 94 of the inner wall is prestressed, the hot expansion of the chamber bottom having the effect of detaching the bottom of the inner wall.
  • the first end 42; 44 of the fastening tab 36; 38 is secured integrally and according to its location to one or the other of the outer axial walls 26 or inner 28 of the combustion chamber by the first attachment means 46; 48 and the second end 50; 52 is preferably attached by brazing or welding to the metal ring 54; 56, itself brazed or welded to the metal chamber bottom 30 of the combustion chamber.
  • the figure 6 illustrates a first variant embodiment of the aforementioned assembly wherein the chamber bottom and the metal crowns of the fixing tongues support form a single piece 100 on which will be soldered or soldered directly the second ends of these tabs 50; 52. This unique piece of course integrates the sealing means to previous segments.
  • a second variant is illustrated in figure 7 in which there is only one set of tongues 102, a first end 104 is fixed to the outer axial wall 26 by first connecting means 106 and a second end 108 is fixed to the inner axial wall 28 by second connecting means 110.
  • first and second fixing means are advantageously of the bolt type.
  • the tongue is further brazed (or welded) to the chamber bottom which may, for example, be formed by the single piece 100 of the aforementioned variant. This solder is of course made at the inter-injector spaces between the openings 32.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Gasket Seals (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (13)

  1. Ringförmige Brennkammer (24) mit einer axialen Außenwand (26) und einer axialen Innenwand (28) aus Verbundwerkstoff sowie einem Kammerboden (30, 80, 100) aus metallische Material , dadurch gekennzeichnet, daß - um eine freie radiale Ausdehnung des Kammerbodens gegenüber den axialen Wänden zu ermöglichen - der Kammerboden zwischen der axialen Außenwand und der axialen Innenwand durch eine Vielzahl flexibler Zungen (36, 38; 82; 102), die einerseits an den axialen Wänden durch Befestigungsmittel (46, 48; 86, 90; 106, 110) befestigt und andererseits am Kammerboden festgelötet oder festgeschweißt sind, in Position gehalten ist, wobei der Kammerboden ferner Mittel (58, 60; 92, 94) aufweist, um die Dichtigkeit zwischen dem Kammerboden und den axialen Wänden zu gewährleisten.
  2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die flexiblen Befestigungszungen aus einem metallischen Material bestehen.
  3. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die Befestigungsmittel von einer Vielzahl von Bolzen, vorzugsweise mit Käfigmutter gebildet sind.
  4. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die Dichtungsmittel eine Runddichtung vom Typ "Lamellen"-Runddiehtung (58, 60) aufweisen, die in einer umlaufenden Nut (62, 64) des Metallkammerbodens angebracht und dazu bestimmt ist, eine Anlage an der gegenüberliegenden axialen Wand der Brennkammer (26, 28) zu gewährleisten.
  5. Brennkammer nach Anspruch 4, dadurch gekennzeichnet, daß die Runddichtung in Sektoren unterteilt ist.
  6. Brennkammer nach Anspruch 4, dadurch gekennzeichnet, daß die Runddichtung mittels eines an dem Metallkammerboden befestigten Federelementes (70, 72) an der axialen Wand in Anlage gehalten ist.
  7. Brennkammer nach Anspruch 6, dadurch gekennzeichnet, daß das Federelement von einer Blattfeder gebildet ist.
  8. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, das die Dichtungsmittel einen Ring (92, 94) umfassen, der an der axialen Wand angebracht und dazu bestimmt ist, mit einer umlaufender Nut (96, 98) des Metallkammerbodens zusammenzuwirken.
  9. Brennkammer nach Anspruch 8, dadurch gekennzeichnet, daß der Dichtungsring geschlitzt ist.
  10. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die flexiblen Befestigungszungen (36, 38) ein erstes Ende (42, 44), das durch die Befestigungsmittel an der einen oder der anderen der axialen Wände befestigt ist, sowie ein zweites Ende (50, 52), das an dem Kammerboden festgelötet oder festgeschweißt ist, aufweist.
  11. Brennkammer nach Anspruch 10, dadurch gekennzeichnet, daß der Kammerboden ferner einen Metallkranz (54, 56) aufweist, an dem die zweiten Enden der flexiblen Befestigungszungen angelötet oder abgeschweißt sind.
  12. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, daß die flexiblen Befestigungszungen (82, 102) ein erstes Ende (84, 104), das durch erste Verbindungsmittel (86, 106) an einer der axialen Wände befestigt ist, ein zweites Ende (88, 108), das durch weite Verbindungsmittel (90, 110) an der anderen der axialen Wände befestigt ist, sowie einen am Kammerboden (80, 100) festgelöteten oder festgeschweißten mittleren Teil umfaßt.
  13. Brennkammer nach Anspruch 12, dadurch gekennzeichnet, daß die flexiblen Befestigungszungen zwischen jeder der Einspritzdüsen (22) angeordnet sind.
EP02291362A 2001-06-06 2002-06-04 Brennkammer mit einer Befestigungsanordnung der Kammerendwand Expired - Lifetime EP1265033B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107368 2001-06-06
FR0107368A FR2825779B1 (fr) 2001-06-06 2001-06-06 Chambre de combustion munie d'un systeme de fixation de fond de chambre

Publications (2)

Publication Number Publication Date
EP1265033A1 EP1265033A1 (de) 2002-12-11
EP1265033B1 true EP1265033B1 (de) 2008-10-22

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EP02291362A Expired - Lifetime EP1265033B1 (de) 2001-06-06 2002-06-04 Brennkammer mit einer Befestigungsanordnung der Kammerendwand

Country Status (5)

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US (1) US6647729B2 (de)
EP (1) EP1265033B1 (de)
JP (1) JP3967633B2 (de)
DE (1) DE60229464D1 (de)
FR (1) FR2825779B1 (de)

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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
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
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
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
US20060030315A1 (en) * 2004-08-06 2006-02-09 Christopher Smith Method and system for provisioning wireless services using SIM information
FR2885201B1 (fr) * 2005-04-28 2010-09-17 Snecma Moteurs Chambre de combustion aisement demontable a performance aerodynamique amelioree
FR2887015B1 (fr) 2005-06-14 2010-09-24 Snecma Moteurs Assemblage d'une chambre de combustion annulaire de turbomachine
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2897418B1 (fr) * 2006-02-10 2013-03-01 Snecma Chambre de combustion annulaire d'une turbomachine
FR2897923B1 (fr) * 2006-02-27 2008-06-06 Snecma Sa Chambre de combustion annulaire a fond amovible
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
FR2931929B1 (fr) * 2008-05-29 2010-06-04 Snecma Chambre de combustion annulaire de moteur a turbine a gaz
FR2935753B1 (fr) * 2008-09-08 2011-07-01 Snecma Propulsion Solide Liaisons souples a butee pour fixation de piece en cmc
US8863527B2 (en) * 2009-04-30 2014-10-21 Rolls-Royce Corporation Combustor liner
EP3044511B1 (de) * 2013-09-11 2021-10-06 Raytheon Technologies Corporation Brennkammer, gasturbinenmotor mit einer solchen brennkammer, und verfahren
US10519794B2 (en) * 2016-07-12 2019-12-31 General Electric Company Sealing system for sealing against a non-cylindrical surface
US10393381B2 (en) * 2017-01-27 2019-08-27 General Electric Company Unitary flow path structure
US10247019B2 (en) 2017-02-23 2019-04-02 General Electric Company Methods and features for positioning a flow path inner boundary within a flow path assembly
US10731859B2 (en) 2017-07-21 2020-08-04 Delavan Inc. Fuel nozzles
US11525577B2 (en) * 2020-04-27 2022-12-13 Raytheon Technologies Corporation Extended bulkhead panel

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Publication number Publication date
JP3967633B2 (ja) 2007-08-29
DE60229464D1 (de) 2008-12-04
FR2825779B1 (fr) 2003-08-29
US6647729B2 (en) 2003-11-18
EP1265033A1 (de) 2002-12-11
US20020184887A1 (en) 2002-12-12
JP2002372241A (ja) 2002-12-26
FR2825779A1 (fr) 2002-12-13

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