EP2609372B1 - Brennkammer für einen flugzeugmotor und verfahren zur befestigung eines injektionssystems in einer brennkammer eines flugzeugmotors - Google Patents

Brennkammer für einen flugzeugmotor und verfahren zur befestigung eines injektionssystems in einer brennkammer eines flugzeugmotors Download PDF

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Publication number
EP2609372B1
EP2609372B1 EP11755413.9A EP11755413A EP2609372B1 EP 2609372 B1 EP2609372 B1 EP 2609372B1 EP 11755413 A EP11755413 A EP 11755413A EP 2609372 B1 EP2609372 B1 EP 2609372B1
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EP
European Patent Office
Prior art keywords
retaining
bushing
retained
collar
peripheral
Prior art date
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Active
Application number
EP11755413.9A
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English (en)
French (fr)
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EP2609372A2 (de
Inventor
Jacques Marcel Arthur Bunel
Brice Arnaud Demoulin
Mario César De Sousa
Guillaume Sevi
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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Publication of EP2609372A2 publication Critical patent/EP2609372A2/de
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Definitions

  • downstream and upstream relate to the direction of flow of the combustion gases inside the cylindrical portion.
  • the retaining ring is positioned in axial abutment against the second flange and the retaining ring is positioned in axial abutment against the first flange, so that the first and second collars are axially clamped between these two rings. These two rings thus prohibit any axial displacement of the second collar relative to the first flange.
  • the inner and outer chamber walls 24 and 26 are joined by a chamber bottom 2 at their upstream ends.
  • a plurality of injection systems 1, typically fourteen to twenty-two, regularly spaced angularly (only one injection system has been shown on the figure 3 ) are provided on the chamber floor 2.
  • each injection system comprises in particular a bowl 7 secured to a swirler 19 which are fixed and a sliding bushing 20 which is able to move in a cavity 28 of the tendon 19.
  • sliding passage 20 comprises a centering cone 21 in which is inserted a fuel injector 29 (shown in FIG. figure 3 ).
  • the deflector 4 comprises a plate 5 and a tubular portion 6.
  • the tubular portion 6 has a symmetry of revolution about a reference axis Y, and more specifically it has a cylindrical shape around the reference axis Y.
  • the plateau 5 serves to protect the chamber bottom 2 of the flames of the combustion chamber.
  • the tubular portion 6 is inserted into an orifice 3 of the chamber bottom 2.
  • the tubular portion 6 comprises a shoulder 30 which bears axially against a downstream wall 31 of the chamber bottom.
  • the deflector 4 is brazed on the chamber bottom 2.
  • the tubular portion 6 has a side wall 33 which extends along the reference axis Y.
  • the side wall 33 is cylindrical about the reference axis Y.
  • the fastening system comprises clamping means.
  • these clamping means comprise a retaining ring 37 and a retaining ring 38.
  • the retaining ring 37 comprises a retaining ring 39 which extends transversely with respect to the reference axis Y.
  • the retaining ring 39 has a symmetry of revolution with respect to the reference axis Y.
  • the ring 39 is inserted radially into the annular groove 35 and bears axially against the first collar 10.
  • the retaining ring 37 also comprises a peripheral retaining skirt 40 which is integral with the retaining ring 39.
  • the retaining peripheral skirt 40 is disposed on the peripheral of the retaining ring 39 and is projecting axially from the retaining ring 39. 39.
  • the retaining peripheral skirt 40 has a cylindrical geometry around the reference axis Y.
  • the retaining ring 38 comprises a retaining ring 43 which bears axially against the second flange 12 and a peripheral retaining skirt 44 projecting axially from the second flange 12.
  • the peripheral retaining skirt 44 is disposed on the periphery of the retaining ring. retaining ring 43.
  • Each latching lug has an upstream surface 55.
  • the retaining ring 43 has an upstream surface 54.
  • the latching lugs 41 and the locking ring retainers are dimensioned so that, when the retaining ring 39 is pressed against the first collar 10 and the retaining ring 43 is pressed against the second flange 12, the upstream surface 55 of each latching lug 41 is aligned axially with the upstream surface 54 of the retaining ring 43.
  • each attachment lug 41 has a chamfer 57 at the intersection between its upstream surface 55 and a second lateral surface 58 of the peripheral groove 42.
  • This chamfer 57 is preferably bevelled.
  • the retaining ring 38 has a chamfer 56 between its upstream surface 54 and the outer surface 59 of the peripheral retaining skirt 44.
  • This chamfer 56 is also preferably bevelled, so that when the peripheral skirt of retained 44 is inserted into the peripheral groove 42, the chamfers 56 and 57 form between them an annular groove 60.
  • the weld bead 45 is preferably deposited in this annular groove 60.
  • peripheral retaining skirt 40 preferably has a radial dimension adjusted relative to the radial dimension of the annular groove 42, so that the peripheral retaining skirt 40 can penetrate into the peripheral groove and, when the skirt retaining device 40 is inserted into the annular groove, it can not, or almost no longer, move radially.
  • the first flange 10 and the second collar 12 are pressed axially against each other. There is no axial play between the retaining ring 37, the retaining ring 38 and the two flanges 10 and 12, so that the injection system 1 is immobilized axially with respect to the deflector 4.
  • the sliding bushing 20 comprises a sole 46 contained in a cavity 28 of the auger. This cavity 28 is delimited by a bottom 47, a closing cup 48 and a side wall 49.
  • the sole 46 is in axial abutment against the bottom 47 of the cavity 28.
  • the immobilizing means preferably comprise a washer 50 in support axial axis on the sole 46 and spring means 51 which are constrained axially between the washer 50 and the closing cup 48. These spring means 51 exert on the sole 46 a sufficient force to prevent any vibration of the sliding bushing in the cavity 28, while allowing the radial movements of the sliding bushing to tolerate differential expansions.
  • these spring means 51 comprise an annular corrugated plate of metal.
  • a first step represented on the figure 7b , the portions of rings which constitute the retaining ring, and which are here half-rings 52, are placed downstream of the first flange, and more precisely in the annular groove 35 of the tubular portion 6 of the baffle.
  • the retaining ring 39 is inserted into the annular groove 35 and the peripheral retaining skirt 40 surrounds the first and second flanges 10 and 12.
  • the two half-rings 52 and the retaining ring 38 are clamped axially, for example with the aid of a clamp or pincer, so as to axially flatten them on both sides. other of the assembly formed by the first and the second flanges 10 and 12.
  • the attachment lugs 41 are welded to the retaining ring 38.
  • the two half-rings 52 and the retaining ring 38 are then secured around the first flange and the second flange in a position such that the two collars are immobilized axially between the two half-rings 52 and the retaining ring 38.
  • the retaining ring 37 ' is split into several ring portions as in the embodiment described with reference to the Figures 3 to 5 .
  • the retaining ring 37 ' has a retaining ring 39' which extends radially.
  • the retaining ring 37 ' has an inner retaining skirt 40' which protrudes axially from the retaining ring 39 '.
  • the retaining ring 37 'further comprises an outer retaining skirt 53 which also protrudes axially from the retaining ring 39'.
  • the inner support skirt 40 'and the outer support skirt 53 define between them a peripheral groove 42' which extends over the circumference of the retaining ring 37 '.
  • the outer support skirt 53 has an upstream end which is substantially aligned with the retaining ring 43 'so as to facilitate the welding of these two elements.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Claims (8)

  1. Verbrennungskammer eines Luftfahrzeugmotors, umfassend wenigstens:
    - eine Ablenkeinheit (4), umfassend wenigstens einen röhrenförmigen Teil (6), wobei sich der röhrenförmige Teil (6) gemäß einer Referenzachse (Y) erstreckt, wobei der röhrenförmige Teil (6) einen ersten vorgeschalteten Endteil (9) umfasst, der durch einen ersten, hervorstehenden, radialen Kragen (10) umgeben ist;
    - ein Einspritzsystem, umfassend wenigstens eine Schale (7), ihrerseits umfassend einen zylindrischen Teil (8), der in einem röhrenförmigen Teil (6) eingefügt ist, wobei der zylindrische Teil (8) ein zweites vorgeschaltetes Ende (11) umfasst, das von dem ersten vorgeschalteten Ende (9) des röhrenförmigen Teils (6) mündet, wobei das zweite vorgeschaltete Ende (11) des zylindrischen Teils (8) durch einen zweiten, radialen, hervorstehenden Kragen (12) umgeben ist, wobei der zweite Kragen (12) axial gegen den ersten Kragen (10) aufgestützt ist;
    wobei die Verbrennungskammer dadurch gekennzeichnet ist, dass sie darüber hinaus umfasst:
    - Eingangsspannmittel, die den ersten und den zweiten Kragen (10, 12) axial jeweils gegeneinander einspannen und die einen Haltering (37) in axialem Aufstützen gegen den ersten Kragen (10) und einen Rückhaltering (38) im axialen Aufstützen gegen den zweiten Kragen (12) einspannen, wobei der Haltering (37) und der Rückhaltering (38) angepasst sind um ineinander einzugreifen, und
    - Befestigungsmittel, die die eingespannten Einspannmittel auf jeder Seite des ersten und des zweiten Kragens (10, 12) halten, wobei der Haltering (37) in wenigstens zwei Ringabschnitte (52) aufgespalten ist und wenigstens umfasst:
    ∘ einen Festhaltering (39) in axialem Aufstützen gegen den ersten Kragen (10) und
    ∘ eine umlaufende Halteschürze (40) in axialem Hervorstehen aus dem Festhaltering (39), wobei die umlaufende Halteschürze (40) den ersten und den zweiten Kragen (10, 12) radial umgeben, und
    - wobei der Rückhaltering (38) wenigstens umfasst:
    ∘ einen Ring zum Zurückhalten (43) in axialem Aufstützen gegen den zweiten Kragen (12) und
    ∘ eine umlaufende Rückhalteschürze (44) in axialem Aufstützen des Rings zum Zurückhalten (43), wobei die umlaufende Rückhalteschürze (44) die umlaufende Halteschürze (40) radial umgibt;
    wobei die Befestigungsmittel den Haltering (37) und den Rückhaltering (38) derart fest befestigen, dass der Festhaltering (39) und der Ring zum Zurückhalten (43) den ersten und den zweiten Kragen (10, 12) axial untereinander eingespannt halten.
  2. Verbrennungskammer gemäß dem voranstehenden Anspruch, dadurch gekennzeichnet, dass der röhrenförmige Teil (6) darüber hinaus eine laterale Wand (33) aufweist, wobei ein Absatz (34) radial von dieser lateralen Wand (33) hervorsteht, wobei eine ringförmige Auskehlung (35) zwischen dem ersten Kragen (10) und dem Absatz (34) definiert sind, wobei der Festhaltering (39) in die ringförmige Auskehlung (35) eingefügt ist.
  3. Verbrennungskammer gemäß irgendeinem der Ansprüche 1 oder 2, dadurch gekennzeichnet, dass die Befestigungsmittel umfassen:
    - wenigstens zwei Befestigungsklauen (41), die fest mit dem Haltering (37) verbunden sind, wobei die genannten Befestigungsklauen (41) mit der umlaufenden Halteschürze (40) eine umlaufende Auskehlung (42) definieren, in der die umlaufende Rückhalteschürze eingefügt ist,
    - wenigstens eine Schweißnaht (45), die jede Befestigungsklaue (41) fest mit dem Rückhaltering (38) befestigt.
  4. Verbrennungskammer gemäß irgendeinem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass der erste und zweite Kragen (10, 12) gegen die umlaufende Halteschürze (40) radial zum Anschlag kommen.
  5. Verbrennungskammer gemäß irgendeinem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die umlaufende Halteschürze (40) eine geringere Höhe h1 als die Höhe h2 der Gruppe aufweist, die durch den ersten Kragen (10) und den zweiten Kragen (12) gebildet wird.
  6. Luftfahrzeugmotor, umfassend wenigstens eine Verbrennungskammer gemäß irgendeinem der voranstehenden Ansprüche.
  7. Befestigungsverfahren eines Einspritzsystems (1) in einer Verbrennungskammer eines Luftfahrzeugmotors gemäß dem Gegenstand des Anspruchs 1, wobei die Verbrennungskammer eine Ablenkeinheit (4) umfasst, umfassend wenigstens einen röhrenförmigen Teil (6), wobei der röhrenförmige Teil (6) sich gemäß einer Referenzachse (Y) erstreckt, wobei der röhrenförmige Teil (6) ein erstes vorgeschaltetes Ende (9) umfasst, das durch einen ersten, radialen, hervorstehenden Kragen (10) umgeben ist, wobei das Einspritzsystem (1) wenigstens eine Schale (8) umfasst, die selbst einen zylindrischen Teil (8) umfasst, der in den röhrenförmigen Teil (6) eingefügt ist, wobei der zylindrische Teil (8) ein zweites vorgeschaltetes Ende (11) umfasst, das von dem ersten vorgeschalteten Ende (9) des röhrenförmigen Teils (6) einmündet, wobei das zweite vorgeschaltete Ende (11) des zylindrischen Teils (8) durch einen zweiten, radialen, hervorstehenden Kragen (12) umgeben ist, wobei der zweite Kragen (12) in axialem Aufstützen gegen den ersten Kragen (10) ist, wobei das Befestigungsverfahren die folgende Schritte umfasst:
    - (a) Es werden Einspannmittel auf jeder Seite des ersten und des zweiten Kragens (10, 12) angeordnet, wobei diese Einspannmittel einen Haltering 37) umfassen, der axial gegen den ersten Kragen (10) und einen Rückhaltering (38) platziert ist, der axial aufstützend gegen den zweiten Kragen (12) platziert ist, wobei der Haltering (37) und der Rückhaltering (38) angepasst sind, um ineinander derart einzugreifen, dass die Spannmittel den ersten und den zweiten Kragen (10, 12) gegeneinander axial einspannen; und
    - (b) Es werden Einspannmittel auf jeder Seite des ersten und des zweiten Kragens (10, 12) derart eingespannt, dass die Einspannmittel auf jeder Seite des ersten und des zweiten Kragens (10, 12) axial eingespannt gehalten sind,
    dadurch gekennzeichnet, dass der Schritt (a) sich wie folgt zusammensetzt:
    - Es werden mehrere Ringabschnitt (52) nach dem ersten Kragen (10) eingefügt, wobei die Ringabschnitte den Haltering (37) bilden, wobei der genannte Haltering (37) wenigstens einen Haltering (39) und eine umlaufende Halteschürze (40), die von dem Haltering (39) axial hervorsteht, bilden, wobei die Ringabschnitte derart positioniert sind, dass der erste Kragen (10) axial gegen den Festhaltering (39) zum Aufstützen kommt und dass die umlaufende Halteschürze (40) den ersten und den zweiten Kragen (10 12) radial umgibt,
    - Es wird der Rückhaltering (38) aufstützend gegen den zweiten Kragen (12) platziert, wobei der genannte Rückhaltering (38) einen Ring zum Festhalten (43) in axialem Aufstützen gegen den zweiten Kragen (12) umfasst, wobei der Rückhaltering (38) eine umlaufende Rückhalteschürze (44) in axialem Aufstützen des Rings zum Zurückhalten (43) umfasst, wobei die umlaufende Rückhalteschürze (44) die umlaufende Halteschürze (40) umgibt,
    - Es werden der erste und der zweite Kragen (10, 12) zwischen den Ringabschnitten (52) einerseits und dem Rückhaltering (38) andererseits axial eingespannt.
  8. Verfahren gemäß dem voranstehenden Anspruch, bei dem die Ringabschnitte (52) darüber hinaus wenigstens jeweils eine Befestigungsklaue (41) umfassen, wobei die genannten Befestigungsklauen mit der umlaufenden Halteschürze eine umlaufende Auskehlung definieren, in der die umlaufende Rückhalteschürze eingefügt ist, dadurch gekennzeichnet, dass der Schritt (b) ein Schweißschritt der Befestigungsklauen an dem Rückhaltering ist.
EP11755413.9A 2010-08-27 2011-08-12 Brennkammer für einen flugzeugmotor und verfahren zur befestigung eines injektionssystems in einer brennkammer eines flugzeugmotors Active EP2609372B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1056831A FR2964177B1 (fr) 2010-08-27 2010-08-27 Chambre de combustion de moteur d?aeronef et procede de fixation d?un systeme d?injection dans une chambre de combustion de moteur d?aeronef
PCT/FR2011/051909 WO2012025682A2 (fr) 2010-08-27 2011-08-12 Chambre de combustion de moteur d'aeronef et procede de fixation d'un systeme d'injection dans une chambre de combustion de moteur d'aeronef

Publications (2)

Publication Number Publication Date
EP2609372A2 EP2609372A2 (de) 2013-07-03
EP2609372B1 true EP2609372B1 (de) 2019-07-03

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EP11755413.9A Active EP2609372B1 (de) 2010-08-27 2011-08-12 Brennkammer für einen flugzeugmotor und verfahren zur befestigung eines injektionssystems in einer brennkammer eines flugzeugmotors

Country Status (4)

Country Link
US (1) US9310083B2 (de)
EP (1) EP2609372B1 (de)
FR (1) FR2964177B1 (de)
WO (1) WO2012025682A2 (de)

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US9388986B2 (en) 2012-03-30 2016-07-12 Solar Turbines Incorporated Air blocker ring assembly with leading edge configuration
US20130255263A1 (en) * 2012-03-30 2013-10-03 Solar Turbines Incorporated. Air blocker ring assembly with radial retention
US10094566B2 (en) * 2015-02-04 2018-10-09 General Electric Company Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation
GB201506017D0 (en) * 2015-04-09 2015-05-27 Rolls Royce Plc Fuel injector system
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
US10690347B2 (en) * 2017-02-01 2020-06-23 General Electric Company CMC combustor deflector
US10563868B2 (en) 2017-05-08 2020-02-18 General Electric Company Coupling method and structure for a propulsion system hot section
GB201802251D0 (en) 2018-02-12 2018-03-28 Rolls Royce Plc An air swirler arrangement for a fuel injector of a combustion chamber
US11466858B2 (en) * 2019-10-11 2022-10-11 Rolls-Royce Corporation Combustor for a gas turbine engine with ceramic matrix composite sealing element

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FR2941288B1 (fr) * 2009-01-16 2011-02-18 Snecma Dispositif d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine

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Also Published As

Publication number Publication date
FR2964177B1 (fr) 2012-08-24
WO2012025682A3 (fr) 2012-05-10
US9310083B2 (en) 2016-04-12
WO2012025682A2 (fr) 2012-03-01
US20130152603A1 (en) 2013-06-20
FR2964177A1 (fr) 2012-03-02
EP2609372A2 (de) 2013-07-03

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