EP1265030B1 - Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff mit flexiblen Verbindungsringen - Google Patents

Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff mit flexiblen Verbindungsringen Download PDF

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Publication number
EP1265030B1
EP1265030B1 EP02291359A EP02291359A EP1265030B1 EP 1265030 B1 EP1265030 B1 EP 1265030B1 EP 02291359 A EP02291359 A EP 02291359A EP 02291359 A EP02291359 A EP 02291359A EP 1265030 B1 EP1265030 B1 EP 1265030B1
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EP
European Patent Office
Prior art keywords
sectorized
combustion chamber
turbomachine
flange
shell
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
EP02291359A
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English (en)
French (fr)
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EP1265030A1 (de
Inventor
Eric Conete
Alexandre Forestier
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
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SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1265030A1 publication Critical patent/EP1265030A1/de
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Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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
    • 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 field of turbomachines and more particularly it relates to the interface between the high pressure turbine and the combustion chamber of turbojet engines provided with a combustion chamber made of CMC (ceramic matrix composite).
  • CMC ceramic matrix composite
  • the high pressure turbine including its inlet nozzle (HPT nozzle), the combustion chamber and the housing (also called envelope) of this chamber are made of metal type materials.
  • HPT nozzle inlet nozzle
  • the combustion chamber and the housing (also called envelope) of this chamber are made of metal type materials.
  • the use of a metal chamber is from a thermal point of view totally inadequate and it must be resorted to a chamber based on CMC type high temperature composite materials.
  • metallic materials However, metal materials and composite materials have very different coefficients of thermal expansion. This results, from an aerodynamic point of view, particularly acute interface problems at the distributor, inlet of the high pressure turbine, and connection with the housing of the chamber.
  • US-A-5,851,679 shows a turbomachine with a chamber of CMC type material.
  • the present invention overcomes these disadvantages by proposing a crankcase-chamber connection having the capacity to absorb the displacements induced by the differences of the expansion coefficients of these parts.
  • An object of the invention is also to provide a structure of simple shape and whose manufacture is particularly easy.
  • a turbomachine comprising, in an envelope of metallic material and in a direction F of gas flow, a fuel injection assembly, a composite material combustion chamber and a sectorized metal material distributor forming the fixed blade inlet stage of a high pressure turbine, characterized in that said combustion chamber is maintained in position by a sectorized flexible ferrule made of metallic material, a first end of which is fixed by first fastening means to said combustion chamber and a second flange end of which is fixed to said envelope by second fixing means. Said first fastening means further ensure the connection of said combustion chamber with said sectorized distributor.
  • connection By this direct connection (integration) of the combustion chamber to the distributor, it avoids any misalignment of the gas stream in operation (thus ensuring a better supply of the high pressure turbine) while improving the sealing chamber-distributor.
  • the connection to the envelope by a sectorized flexible hoop system further provides an appreciable weight gain for the combustion chamber compared to traditional rigid heavy-duty connection devices.
  • the first fixing means consist of a plurality of bolts.
  • the metallic split flexible ferrule comprises ventilation orifices to allow the passage of a cooling fluid and a plurality of parallel sectoring slots ending at the upstream of said ventilation orifices.
  • the sectoring slots are dimensioned to compensate for the thermal expansion existing between the combustion chamber of composite material and the envelope of metallic material.
  • the turbomachine comprises an envelope having outer and inner annular walls of metallic material delimiting between them a space for successively receiving, in the flow direction F of the gases, an injection assembly of a fuel, and on the one hand an annular combustion chamber of composite material formed of an outer axial wall, an inner axial wall and a transverse wall which constitutes the bottom of this combustion chamber, and secondly a segmented annular distributor made of metallic material formed of a plurality of fixed vanes mounted between an external sectorized circular platform and a internal sectorized circular platform, it is expected that downstream ends of said outer and inner axial walls of the combustion chamber are held in position by flexible outer and inner shells of metal material whose first ends are fixed to said external downstream ends and internally by first fixing means and second ends forming flanges are attached to said outer and inner annular envelopes by second fastening means.
  • these first fixing means comprise, on the one hand, first holding means for holding said downstream end portion of the internal axial wall of the combustion chamber between said internal sectorized circular platform of the distributor and said first end of the inner sectorized flexible ferrule and secondly second holding means for holding said end downstream portion of the outer axial wall of the combustion chamber between said outer sectorized circular platform of the distributor and said first end of the ferrule external sectorised flexible.
  • said first end of the inner sectorized flexible ferrule comprises a downstream part forming a flange and serving as a support for a seal of said inner annular wall of the envelope.
  • said inner annular wall of the casing comprises a flange of which a circular groove may receive an omega-type circular seal intended to seal said wall flange.
  • annular inner envelope and said downstream portion forming a flange.
  • this space 16 comprising, in the gas flow direction, firstly an injection assembly formed of a plurality of injection systems 20 regularly distributed around the conduit 18 and each having a fuel injection nozzle 22 fixed on the outer annular envelope 12 (for the sake of simplification of the drawings the mixer and the deflector associated with each injection nozzle have not been shown), then a combustion chamber 24 made of high temperature composite material, type CMC or others (carbon for example), formed of an outer axial wall 26 and an inner axial wall 28, both coaxial axis 10, and a transverse wall 30 which constitutes the bottom of this chamber of combustion and which comprises flaps 32, 34 fixed by any suitable means, for example metal bolts or refractory screws conical head, on upstream ends 36, 38 of the axial walls 26, 28, the bottom of the chamber 30 being po urvu orifices 40 to allow the injection of the fuel and a part of the oxidant in the combustion chamber 24, and finally an annular distributor 42 of metal material forming an inlet stage of a high pressure turbine (not shown) and conventionally comprising
  • the combustion chamber 26, 28 is held in position by a flexible shell of metal material 56, 60, a first end 56a, 56b is fixed to a downstream end 26a, 26b of the axial wall of the chamber of combustion by first fixing means 50, 52 and a second end flange 56b, 60b is fixed to the casing 12, 14 by second fastening means 54, 58.
  • This flexible ferrule is partially sectorized to compensate for the differences in dilation between the CMC chamber and the metal shell.
  • the first attachment means 50, 52 also ensure the maintenance of the distributor 42 between the walls of the chamber 26, 28.
  • the downstream end of the outer axial wall 26a (respectively internal 28a) of the combustion chamber is mounted between the external platform 46 (respectively internal 48) of the distributor and the first end of the external sectorized flexible shell 60a (respectively internal 56a) of metal material whose second flange end 60b, 56b is fixed to the outer annular envelope 12 (respectively internal 14), the assembly formed of these three elements, the downstream end of the external (internal) axial wall, the external (internal) distributor platform and the first end of the outer (internal) reinforced sectorised flexible shell, being maintained tightened by the first fastening means.
  • first fixing means comprise, on the one hand, first holding means 50 which hold the downstream end 28a of the internal axial wall 28 of the combustion chamber (opposite to the upstream end 38) in a pinch position between the internal sectorized circular platform of the distributor 48 and the first end 56a of the internal metal sectorized flexible ring 56 and secondly second holding means 52 which hold the downstream end 26a of the wall by pinching axial axis of the combustion chamber (opposite to the upstream end 36) between the external sectorized circular platform of the distributor 46 and the first end 60a of the external metalized sectorized flexible ring 60.
  • the second attachment means comprise firstly connecting means 54 for fixing the upstream flange 56b of the inner sectorized flexible ferrule to the inner annular envelope 14 and secondly second connecting means 58 for attaching the upstream flange 60b of the outer sectorized flexible ferrule to the outer annular envelope 12.
  • the first 50 and second 52 holding means as the first 54 and second 58 connecting means are advantageously constituted by a plurality of bolts.
  • the first end 56a of the inner metal flexible ferrule 56 is advantageously provided with a downstream part 66 forming a flange serving as a support for a seal mounted in a flange 64 of this inner annular envelope.
  • Through-holes 68, 70 formed in the external metal 46 and inner metal platforms 48 of the distributor 42 are further provided to ensure cooling of the fixed vanes 44 of the inlet distributor of the rotor of the high-pressure turbine from the compressed oxidant available at the outlet of the diffusion duct 18 and flowing in two streams F1, F2 on either side of the combustion chamber 24. These cooling flows will be previously passed between the different sectors of the inner metalized and metalized flexible rings. external and further by ventilation holes 56c, 60c formed in these ferrules at separation slots 72, 74 between sectors (see for example the figure 3 ). These sectoring slots are dimensioned in a determined manner to compensate for the thermal expansion existing between the combustion chamber made of composite material and the envelope made of metallic material.
  • the flange 64 of the inner annular casing has a circular groove 76 to receive a circular seal of "omega" type sealing 78 intended to ensure the seal between this flange of the inner annular envelope and the downstream flange end 66 of the inner metal ferrule 48.
  • the flow of oxidant compressed in from the compressor and surrounding the chamber by F2 can reach the turbine only through the orifices 70 (after passing through the sectoring slots 72 and ventilation holes 56c).
  • the external circular platform of the distributor 46 comprises a flange 80 provided with a circular groove 82 for receiving a blade seal 84, one end of which will come into contact with the outer annular envelope 12 to ensure a tightness screw. flow F1 which will then be forced to flow through the orifices 68 (also after passing through the sectoring slots 74 and the ventilation holes 60c).

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

Claims (11)

  1. Turbomaschine, die in einem Gehäuse aus metallischem Material (12, 14) und entlang einer Strömungsrichtung F der Gase eine Einheit zum Einspritzen eines Treibstoffs (20, 22), eine Brennkammer aus Verbundwerkstoff (24) sowie ein in Sektoren unterteiltes Leitrad aus metallischem Material (42), das die Eintrittsstufe mit Leitschaufeln (44) einer Hochdruckturbine bildet, umfaßt, dadurch gekennzeichnet, daß die Brennkammer durch einen flexiblen, in Sektoren unterteilten Ring aus metallischem Material (56, 60) in Position gehalten wird, von dem ein erstes Ende (56a, 60a) durch erste Befestigungsmittel (50, 52) an der Brennkammer befestigt ist und von dem ein einen Flansch bildendes zweites Ende (56b, 60b) durch zweite Befestigungsmittel (54, 58) an dem Gehäuse befestigt ist.
  2. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß die ersten Befestigungsmittel ferner die Verbindung der Brennkammer mit dem in Sektoren unterteilten Leitrad sicherstellen.
  3. Turbomaschine nach Anspruch 1 oder Anspruch 2, dadurch gekennzeichnet, daß die ersten Befestigungsmittel von einer Vielzahl von Bolzen gebildet sind.
  4. Turbomaschine nach Anspruch 1, dadurch gekennzeichnet, daß der flexible, in Sektoren unterteilte Metallring Belüftungsöffnungen (56c, 60c) aufweist, um den Durchgang eines Kühlfluids zu ermöglichen.
  5. Turbomaschine nach Anspruch 4, dadurch gekennzeichnet, daß der flexible, in Sektoren unterteilte Metallring eine Vielzahl von parallelen Sektorisierungsschlitzen (72, 74) aufweist, die im Bereich der am weitesten stromaufwärts gelegenen Belüftungsöffnungen enden.
  6. Turbomaschine nach Anspruch 5, dadurch gekennzeichnet, daß die Sektorisierungsschlitze bemessen sind, um die zwischen der Brennkammer aus Verbundwerkstoff und dem Gehäuse aus metallischem Material vorhandene Wärmeausdehnung zu kompensieren.
  7. Turbomaschine mit einem Gehäuse, das eine ringförmige Außenwand (12) und eine ringförmige Innenwand (14) aus metallischem Material aufweist, die zwischen sich einen Raum (16) begrenzen, um nacheinander in Strömungsrichtung F der Gase eine Einheit zum Einspritzen eines Treibstoffs (20, 22) sowie einerseits eine ringförmige Brennkammer (24) aus Verbundwerkstoff, die von einer axialen Außenwand (26), von einer axialen Innenwand (28) und von einer querverlaufenden Wand (30), welche den Boden dieser Brennkammer bildet, gebildet ist, und andererseits ein ringförmiges, in Sektoren unterteiltes Leitrad (42) aus metallischem Material, das von einer Vielzahl von Leitschaufeln (44) gebildet ist, die zwischen einer kreisförmigen, in Sektoren unterteilten Außenplattform (46) und einer kreisförmigen, in Sektoren unterteilten Innenplattform (48) angebracht sind, aufzunehmen, dadurch gekennzeichnet, daß stromabwärtige Enden (26a, 28a) der axialen Außenwand und der axialen Innenwand der Brennkammer durch flexible, in Sektoren unterteilte Außen- und Innenringe aus metallischem Material (56, 60) in Position gehalten werden, von denen erste Enden (56a, 60a) durch erste Befestigungsmittel (50, 52) an den stromabwärtigen äußeren und inneren Enden befestigt sind und von denen Flansche bildende zweite Enden (56b, 60b) durch zweite Befestigungsmittel (54, 58) an den ringförmigen Außen- und Innengehäusen befestigt sind.
  8. Turbomaschine nach Anspruch 7, dadurch gekennzeichnet, daß die ersten Befestigungsmittel einerseits erste Haltemittel (50) zum Halten des stromabwärtigen Endes der axialen Innenwand der Brennkammer zwischen der kreisförmigen, in Sektoren unterteilten Innenplattform des Leitrades und dem ersten Ende des flexiblen, in Sektoren unterteilten Innenrings, sowie andererseits zweite Haltemittel (52) zum Halten des stromabwärtigen Endes der axialen Außenwand der Brennkammer zwischen der kreisförmigen, in Sektoren unterteilten Außenplattform des Leitrades und dem ersten Ende des flexiblen, in Sektoren unterteilten Außenrings umfassen.
  9. Turbomaschine nach Anspruch 8, dadurch gekennzeichnet, daß die ersten und zweiten Haltemittel von einer Vielzahl von Bolzen gebildet sind.
  10. Turbomaschine nach Anspruch 7, dadurch gekennzeichnet, daß das erste Ende des flexiblen in Sektoren unterteilten Innenrings einen stromabwärtigen Teil aufweist, der einen Flansch (66) bildet und einer Dichtung (78) der ringförmigen Innenwand des Gehäuses als Auflage dient.
  11. Turbomaschine nach Anspruch 10, dadurch gekennzeichnet, daß die ringförmige Innenwand des Gehäuses einen Flansch (64) aufweist, von dem eine kreisförmige Nut (76) eine Runddichtung vom Typ "Omega" (78) aufnimmt, die dazu bestimmt ist, die Dichtigkeit zwischen diesem Flansch der ringförmigen Innenwand des Gehäuses und dem einen Flansch bildenden stromabwärtigen Teil sicherzustellen.
EP02291359A 2001-06-06 2002-06-04 Befestigung einer Turbinenbrennkammer aus keramischem Matrix-Verbundwerkstoff mit flexiblen Verbindungsringen Expired - Lifetime EP1265030B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0107375 2001-06-06
FR0107375A FR2825787B1 (fr) 2001-06-06 2001-06-06 Montage de chambre de combustion cmc de turbomachine par viroles de liaison souples

Publications (2)

Publication Number Publication Date
EP1265030A1 EP1265030A1 (de) 2002-12-11
EP1265030B1 true EP1265030B1 (de) 2008-07-09

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US (1) US6823676B2 (de)
EP (1) EP1265030B1 (de)
JP (1) JP3984101B2 (de)
DE (1) DE60227455D1 (de)
FR (1) FR2825787B1 (de)

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Also Published As

Publication number Publication date
US6823676B2 (en) 2004-11-30
FR2825787A1 (fr) 2002-12-13
JP3984101B2 (ja) 2007-10-03
DE60227455D1 (de) 2008-08-21
JP2002372242A (ja) 2002-12-26
EP1265030A1 (de) 2002-12-11
US20030000223A1 (en) 2003-01-02
FR2825787B1 (fr) 2004-08-27

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