EP3084308B1 - Brennkammer in einer turbomaschine - Google Patents

Brennkammer in einer turbomaschine Download PDF

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Publication number
EP3084308B1
EP3084308B1 EP14828233.8A EP14828233A EP3084308B1 EP 3084308 B1 EP3084308 B1 EP 3084308B1 EP 14828233 A EP14828233 A EP 14828233A EP 3084308 B1 EP3084308 B1 EP 3084308B1
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European Patent Office
Prior art keywords
internal
external
revolution
annular
radial
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EP14828233.8A
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English (en)
French (fr)
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EP3084308A1 (de
Inventor
Brice LE PANNERER
Laurent Bernard Cameriano
Pierre-François Simon Paul PIREYRE
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Safran Aircraft Engines SAS
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Safran Aircraft Engines SAS
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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
    • F23R3/28—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
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to an annular turbomachine combustion chamber and a turbomachine equipped with an annular combustion chamber.
  • annular combustion chamber comprises two inner and outer coaxial revolution walls, connected to each other upstream by an annular so-called bottom wall wall having fuel injector head through openings. between the walls of internal and external revolution.
  • Each injector is engaged in centering means which are movable radially in support means integral with support means.
  • the centering means of each injector are formed by a centering ring in which is engaged an injector and having a radial annular flange extending radially outward and slidably mounted in an annular groove means of support.
  • the annular groove of the support means allows a radial displacement of the centering ring housing the injector to compensate for manufacturing tolerances as well as differential expansions in operation.
  • the annular groove of radial displacement of the ring is defined by retaining means axially upstream and downstream of the radial annular flange of the centering ring.
  • the axially downstream retaining means are formed by a downstream radial wall of an annular sheath fixed on the annular chamber bottom, the radial wall being connected to a cylindrical rim extending upstream and on which is attached by welding or brazing a washer attached to the cylindrical rim.
  • This washer is therefore fixed releasably on the support means.
  • this washer In case it is necessary to replace everything or part of the centering means of an injector during a maintenance operation, it is necessary to destroy this washer, which is a delicate operation because the sleeve which is fixed on the annular wall of the chamber bottom must not be damaged . Furthermore, it has been found breaks welding seams, which is not permissible, and does not ensure a perfect mechanical integrity of the fuel injection systems.
  • the invention aims in particular to provide a simple, effective and economical solution to the problems of the prior art described above.
  • the axial retaining means upstream of the centering means are fixed on at least one of the internal and external walls of revolution of the combustion chamber and no longer on the support means, which allows quick and easy assembly and disassembly axial upstream retaining means for carrying out maintenance operations.
  • the removable attachment can be made for example by bolting using the fasteners used to integrally assemble an annular chamber bottom and the inner and outer walls of revolution, which is simple to implement.
  • the annular ring will advantageously comprise a plurality of rings regularly spaced circumferentially from each other and delimiting said orifices of passages of the injectors.
  • the crown thus comprises free spaces between the rings avoiding a significant increase in the mass of the axial retaining means upstream of the centering means.
  • At least some of the rings of the crown are connected to at least one lug extending radially inwards or outwards whose end opposite the ring is connected to a flange. extending axially, preferably downstream, and serving for attachment to the internal or external revolution wall, respectively.
  • the crown comprises a unitary pattern whose successive repetition circumferentially forms the annular ring.
  • the pattern comprises a ring connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the outer radial tab. being connected externally to an outer rim extending downstream and fixed on the outer wall of revolution.
  • the pattern comprises at least three rings whose circumferential end rings of the pattern are connected to at least one radial tab carrying at its end opposite the ring a flange extending downstream and fixed on the inner or outer wall of revolution, the ring or rings circumferentially interposed between the two rings of circumferential ends of the pattern being connected to said end rings by circumferential arms.
  • the rings of circumferential ends of the pattern are each connected to two inner and outer radial tabs, the inner radial tab being internally connected to an inner flange extending downstream and fixed on the inner wall of revolution and the tab outer radial being externally connected to an outer flange extending downstream and fixed to the outer wall of revolution.
  • the annular ring may be a one-piece piece or comprise a plurality of crown portions which are juxtaposed circumferentially.
  • the use of several crown portions, although requiring several independent assembly operations, may make it possible to have to change only one crown portion rather than the entire crown during a maintenance operation.
  • the support means comprise axial retaining means downstream of the centering means, said support means being fixed on an annular chamber bottom.
  • the upstream axial retaining means are fixed on the inner and outer walls of revolution by means of the same fasteners of said internal and external walls of revolution to an annular chamber bottom, which makes it possible to use pre-existing fixing zones and avoids the modifications of the walls of internal and external revolution.
  • the fasteners are for example bolts which provide a more robust link means of axial retention upstream with respect to welds as in the prior art.
  • the invention also relates to a turbomachine, such as a turbojet or a turboprop, comprising a combustion chamber as described above.
  • the invention also relates to an axial retaining member of the fuel injector centering means in an annular turbomachine combustion chamber according to claim 11.
  • FIG. 1 represents the upstream part of a combustion chamber 10 in a turbomachine according to the known technique comprising two walls of internal revolution 12 and external 14 extending around the axis 16 of the combustion chamber and fixed at their upstream ends on an annular chamber bottom 18 extending between the walls of internal revolution 12 and external 14 and traversed by fuel injectors 19.
  • the annular chamber bottom 18 comprises a radial annular wall 20 connected at its outer periphery to an outer cylindrical rim 22 extending upstream and fixed by bolting elements 24 on the upstream end of the outer wall of revolution 14
  • the radial wall 20 of the annular chamber bottom 18 is connected at its inner periphery to an internal cylindrical rim 26 extending upstream and fixed by bolting elements 28 to the upstream end of the internal wall of revolution 12 .
  • the upstream end of the outer wall of revolution 14 is arranged radially between the end external downstream 34 of the fairing 30 and the external cylindrical rim 22 of the annular chamber bottom 18.
  • the upstream end of the inner wall of revolution 12 is arranged radially between the inner downstream end 32 of the fairing 30 and the inner cylindrical rim 26 of the annular chamber bottom 18.
  • the annular chamber bottom 18 comprises a plurality of openings for the passage of the injector heads 19 for the spraying of fuel between the walls of internal revolution 12 and external 14 and downstream of the chamber bottom 18.
  • Each injector 19 is engaged axially in centering means 36 of the injector 19, which centering means 36 are freely movable in the radial direction in support means 38 integral with the annular chamber bottom 18.
  • each injector 19 comprise a radial annular wall 40 fixed on the inner periphery and facing upstream of the passage opening of an injector 19.
  • the radial annular wall 40 also comprises a cylindrical flange 42 extending upstream.
  • a plate 44 or washer is fixed by welding or brazing its outer periphery on the upstream end of the cylindrical rim 42 of the sheath.
  • each injector 19 comprise a cylindrical ring 46 traversed axially by the head and comprising an annular flange 48 extending radially outwards and mounted to slide radially in the groove delimited upstream by the washer 44, downstream. by the radial annular wall 40. The bottom of the groove is delimited by the cylindrical rim 42.
  • the weld seams of the washers 44 holding upstream centering means can be weakened and are thus likely to break in operation, which impacts the injection of fuel between the walls of internal revolution 12 and external 14.
  • the invention overcomes this problem by removably fixing the axial retaining means on at least one of the inner wall 12 and outer wall 14 so as to facilitate the dismounting of the removable fastening means.
  • the axial retaining means comprise an annular ring 50 whose inner periphery is fixed on the internal wall of revolution 12 and whose outer periphery is fixed on the outer wall of revolution 14.
  • the ring 50 may be a one-piece piece comprising a plurality of rings 52 each formed of a radial annular wall forming a passage opening 53 of an injector 19 intended to come axially opposite an annular flange 48 of a centering ring 36 of an injector 19 so as to form an axial stop upstream of said annular collar 48.
  • Each ring 52 is connected to two tabs, one of which extends radially inwards and the other 56 extends radially outwards.
  • the radially outer ends of the outer tabs 56 are connected to an outer cylindrical rim 58 extending axially downstream.
  • the radially inner ends of the inner tabs 54 are connected to an inner cylindrical rim 60 extending axially downstream.
  • the annular ring 50 is thus formed of a plurality of unitary patterns repeating successively in the circumferential direction and integral with each other. Each pattern is then formed of a ring 52, two inner radial tabs 54 and outer 56 and inner cylindrical rim portions 62 and outer 64.
  • Each inner cylindrical rim 60 and outer 58 comprises orifices 66 for the passage of a fixing screw, these orifices 66 being regularly distributed around the axis 16 of the combustion chamber.
  • Each pattern thus comprises two orifices 66 whose centers are aligned with the center of the ring 50 and located in the same radial plane containing the axis 16 of the combustion chamber.
  • the outer cylindrical rim 58 of the ring 50 is attached to the outer cylindrical rim 22 of the chamber bottom 18 and is fixed to the outer wall of revolution 14 by means of the fixing screws 24.
  • the internal cylindrical rim 60 of the ring 50 is attached to the inner cylindrical rim 26 of the chamber bottom 18 and is fixed to the upstream end of the internal wall of revolution 12 by means of the fixing screws 28.
  • the assembly and disassembly of the crown 50 are thus simple and easy to perform when a maintenance operation is necessary.
  • the double internal and external fixation of the ring 50 on the inner and outer walls 12 of revolution 14 ensures good mechanical strength to the crown and ensures its integrity in operation.
  • a ring 68 In a second embodiment of a ring 68 according to the invention, it is formed of a plurality of independent patterns 70 juxtaposed circumferentially to form the annular ring 68.
  • Each portion of internal cylindrical rim 72 or outer 74 of a pattern at its circumferential ends which are arranged with clearance vis-a-vis the circumferential ends of the inner cylindrical rim portions 72 or outer 74, respectively, adjacent patterns.
  • the figure 5 represents a third embodiment of an annular ring 76 according to the invention, formed of a circumferential repetition of a plurality of H-shaped patterns 78 integral with each other and each comprising three rings 80, 82 successive.
  • Each pattern 78 thus comprises two circumferential end rings 82, each connected to two tabs extending radially inward 84 and outward 86.
  • the outer radial tabs 86 of the circumferential end rings 82 of each pattern 78 are connected to an outer cylindrical rim 88 extending downstream and the inner radial lugs 84 of the circumferential end rings 82 of each pattern 78 are connected to an inner cylindrical rim 90 extending downstream.
  • Ring 80 of each pattern 78 which is interspaced circumferentially between two circumferential end rings 82 is devoid of radial tabs and is connected to the circumferential end rings 82 by circumferential joining arms 92.
  • the figure 6 represents a fourth embodiment of an annular ring 94 according to the invention, formed of a circumferential repetition of several units 96 independent of each other and juxtaposed circumferentially without contact.
  • Each pattern 96 includes an inner cylindrical rim portion 98 and an outer cylindrical rim portion 100 for attachment of each pattern 96 to the internal and external 12 and outer revolution walls 14.
  • the crown may comprise only one cylindrical fixing flange on one of the walls of internal or external revolution.
  • this type of embodiment is less reliable than those shown in the figures of fact of the double internal and external fixation of the annular ring.

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

Claims (11)

  1. Ringförmige Brennkammer in einem Turbotriebwerk, enthaltend Treibstoffinjektoren (19), Zentriereinrichtungen (36) und zwei koaxial verlaufende Rotationswände, nämlich eine innere (12) und eine äußere (14), zwischen denen die Treibstoffinjektoren (19) ausmünden, die jeweils mit den Zentriereinrichtungen (36) in Eingriff stehen, die in radialer Richtung in Trageinrichtungen (38) verlagerbar sind, wobei die Kammer auch Halteeinrichtungen (50, 68) zum axialen Halten der Zentriereinrichtung in Richtung stromaufwärts enthalten, wobei die Halteeinrichtungen zum axialen Halten in Richtung stromaufwärts abnehmbar an zumindest eine aus innerer (12) und äußerer (14) Rotationswand befestigt sind, wobei die Halteeinrichtungen zum axialen Halten einen radial verlaufenden ringförmigen Kranz (50, 68, 76, 94) enthalten, der radial innen und/oder außen an zumindest eine aus innerer (12) und äußerer (14) Rotationswand befestigt ist und eine ringförmige Reihe von Öffnungen (53) zum Durchtritt der Injektoren (19) aufweist, wobei der Rand einer jeden Öffnung (53) dazu ausgelegt ist, einen axialen Anaschlag in Richtung stromaufwärts für einen radial verlaufenden, ringförmigen Kragen (48) der Zentriereinrichtungen eines der Treibstoffinjektoren (19) zu bilden,
    dadurch gekennzeichnet, dass
    der ringförmige Kranz (50, 68, 76, 94) mehrere Ringe (52) enthält, die gleichmäßig umlaufend voneinander beabstandet sind und die Öffnungen zum Durchtritt der Injektoren eingrenzen.
  2. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass zumindest bestimmte der Ringe (52) des ringförmigen Kranzes (50, 68, 76, 94) mit zumindest einer Lasche (54, 56, 84, 86) verbunden sind, die sich radial nach innen bzw. nach außen erstreckt und deren dem Ring (52) entgegengesetztes Ende mit einer Randleiste verbunden ist, die sich axial erstreckt und der Befestigung an die innere (12) bzw. äußere Rotationswand dient.
  3. Brennkammer nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass der Kranz (50, 68, 76, 94) ein einheitliches Muster (70, 76, 96) enthält, dessen aufeinanderfolgende Wiederholung in Umfangsrichtung den ringförmigen Kranz (50, 68, 76, 94) bildet.
  4. Brennkammer nach Anspruch 3, dadurch gekennzeichnet, dass das Muster (70, 76, 96) einen Ring (52) enthält, der mit zwei radialen Laschen, einer inneren (54) und einer äußeren (56), verbunden ist, wobei die radial innere Lasche (54) innen mit einer inneren Randleiste (60, 72) verbunden ist, die sich nach stromabwärts erstreckt und an die innere Rotationswand (12) befestigt ist, und wobei die radial äußere Lasche (56) außen mit einer äußeren Randleiste (58, 74) verbunden ist, die sich nach stromabwärts erstreckt und an die äußere Rotationswand (14) befestigt ist.
  5. Brennkammer nach Anspruch 3, dadurch gekennzeichnet, dass das Muster (76, 96) zumindest drei Ringe (80, 82) enthält, wobei die Umfangsendringe (82) des Musters (76, 96) mit zumindest einer radialen Lasche (84, 86) verbunden sind, die an ihrem dem Ring entgegengesetzten Ende eine Randleiste (88, 90, 98, 100) trägt, die sich nach stromabwärts erstreckt und an die innere (12) bzw. äußere (14) Rotationswand befestigt ist, wobei der bzw. die Umfangszwischenringe zwischen den beiden Umfangsendringen (82) des Musters mit den Umfangsendringen (82) durch umlaufende Arme (92) verbunden sind.
  6. Brennkammer nach Anspruch 5, dadurch gekennzeichnet, dass die Umfangsendringe (82) des Musters jeweils mit zwei radialen Laschen, nämlich einer inneren (84) und einer äußeren (86), verbunden sind, wobei die radial innere Lasche (84) innen mit einer inneren Randleiste verbunden ist, die sich nach stromabwärts erstreckt und an die innere Rotationswand (12) befestigt ist, und wobei die radial äußere Lasche (86) außen mit einer äußeren Randleiste verbunden ist, die sich nach stromabwärts erstreckt und an die äußere Rotationswand (11) befestigt ist.
  7. Brennkammer nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass der ringförmige Kranz (50, 68, 76, 94) ein einstückiges Teil ist oder mehrere Kranzabschnitte enthält, die umlaufend nebeneinandergeordnet sind.
  8. Brennkammer nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Trageinrichtungen Halteeinrichtungen zum axialen Halten der Zentriereinrichtungen in Richtung stromabwärts enthalten, wobei die Trageinrichtungen an einen Boden (18) der ringförmigen Kammer befestigt sind.
  9. Brennkammer nach einem der vorangehenden Ansprüche, dadurch gekennzeichnet, dass die Halteeinrichtungen zum axialen Halten in Richtung stromaufwärts an die innere und äußere Rotationswand bzw. Rotationswände mittels derselben Befestigungsglieder für die innere und äußere Rotationswand an einen Boden der ringförmigen Kammer befestigt sind.
  10. Turbotriebwerk, wie etwa Turbostrahltriebwerk oder Turboprop-Triebwerk, dadurch gekennzeichnet, dass es eine Brennkammer nach einem der vorangehenden Ansprüche enthält.
  11. Halteglied zum axialen Halten von Zentriereinrichtungen (36) von Treibstoffinjektoren (19) in einer ringförmigen Brennkammer von Turbotriebwerken, enthaltend
    einen radial verlaufenden ringförmigen Kranz (50, 68, 76, 94), der:
    - radial innen und/oder außen an zumindest eine aus einer inneren (12) und einer äußeren (14) Rotationswand der ringförmigen Brennkammer des Turbotriebwerks zu befestigen ist und
    - eine ringförmige Reihe von Öffnungen (53) zum Durchtritt der Treibstoffinjektoren (19) aufweist, wobei ein Rand einer jeden Öffnung (53) dazu ausgelegt ist, einen axialen Anaschlag in Richtung stromaufwärts für einen radial verlaufenden, ringförmigen Kragen (48) der Zentriereinrichtungen eines der Injektoren (19) zu bilden,
    dadurch gekennzeichnet, dass
    es mehrere Ringe (52, 82) enthält, die gleichmäßig umlaufend voneinander beabstandet sind und die Öffnungen zum Durchtritt der Injektoren eingrenzen, und von denen zumindest bestimmte zwei Laschen (54, 56, 84, 86) tragen, die sich diametral einander entgegengesetzt von dem Ring (52, 82) ausgehend erstrecken, wobei die beiden Laschen (54, 56, 84, 86) jeweils eine Randleiste enthalten, die sich entlang der Achse des Rings (52, 82) erstreckt.
EP14828233.8A 2013-12-20 2014-12-17 Brennkammer in einer turbomaschine Active EP3084308B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1363348A FR3015639B1 (fr) 2013-12-20 2013-12-20 Chambre de combustion dans une turbomachine
PCT/FR2014/053401 WO2015092284A1 (fr) 2013-12-20 2014-12-17 Chambre de combustion dans une turbomachine

Publications (2)

Publication Number Publication Date
EP3084308A1 EP3084308A1 (de) 2016-10-26
EP3084308B1 true EP3084308B1 (de) 2019-09-11

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EP14828233.8A Active EP3084308B1 (de) 2013-12-20 2014-12-17 Brennkammer in einer turbomaschine

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Country Link
US (1) US10458654B2 (de)
EP (1) EP3084308B1 (de)
FR (1) FR3015639B1 (de)
WO (1) WO2015092284A1 (de)

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US11131458B2 (en) * 2018-04-10 2021-09-28 Delavan Inc. Fuel injectors for turbomachines

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Also Published As

Publication number Publication date
US20180163965A1 (en) 2018-06-14
FR3015639A1 (fr) 2015-06-26
FR3015639B1 (fr) 2018-08-31
EP3084308A1 (de) 2016-10-26
WO2015092284A1 (fr) 2015-06-25
US10458654B2 (en) 2019-10-29

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