EP2096357B1 - Flammenhalter für Nachverbrennungskanal eines Turboreaktors mit einer Abstandschwelle, sowie Nachverbrennungskanal und Turboreaktor, der einen Nachverbrennungskanal umfasst - Google Patents

Flammenhalter für Nachverbrennungskanal eines Turboreaktors mit einer Abstandschwelle, sowie Nachverbrennungskanal und Turboreaktor, der einen Nachverbrennungskanal umfasst Download PDF

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Publication number
EP2096357B1
EP2096357B1 EP09153848A EP09153848A EP2096357B1 EP 2096357 B1 EP2096357 B1 EP 2096357B1 EP 09153848 A EP09153848 A EP 09153848A EP 09153848 A EP09153848 A EP 09153848A EP 2096357 B1 EP2096357 B1 EP 2096357B1
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EP
European Patent Office
Prior art keywords
arm
flame holder
jet engine
duct
flame
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Active
Application number
EP09153848A
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English (en)
French (fr)
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EP2096357A1 (de
Inventor
Jacques Marcel Arthur Bunel
Yann François Jean-Claude Vuillemont
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 of EP2096357A1 publication Critical patent/EP2096357A1/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means

Definitions

  • the present invention relates to the field of turbojet engines comprising a heating channel of gases from the gas generator.
  • the post-combustion jet engines comprise, from upstream to downstream, a gas generator consisting of a gas turbine engine producing combustion-heated gases, a heating channel and an exhaust nozzle for the gases in the atmosphere.
  • the engine is most often double-stream with a central primary flow and a peripheral secondary flow.
  • the heating channel is provided with a jacket made of material resistant to the gas combustion temperature and suitably cooled.
  • fuel injection means are arranged in the gas stream, associated with means forming flame hangers.
  • the flame catching means 10 are in the form of radial arms arranged in a star with respect to the motor axis and passing through the two primary and secondary flow veins, interconnected by elements in the form of annular sectors 9.
  • the arms 100 cast from the channel-shaped foundry have a section U or V open downstream so as to create a depressed area to stabilize the combustion.
  • fuel injectors 130 are placed inside the cavity formed between the walls, upstream and near the top with air ventilation boxes 120. The air is taken from the secondary flow and distributed by the caissons 120 towards the injectors 130.
  • a thermal protection screen 110 is placed on the cover of this part of the arm 100 containing the fuel injectors 130 and the ventilation box 120.
  • the air ventilation box 120 is centered in the upper part and in the lower part in the cavity of the arm 100. It is held in radial position by means of a pin 5 on the base of the tube which passes through the thermal protection screen 110 and thereby ensures a rotational stop of the box 120 in the arm 100.
  • the thermal protection screen 110 which is generally made of CMC (composite ceramic material) is damaged by matting and delamination which is particularly harmful in vibration operation.
  • the Applicant proposes, in order to fill at least some of these drawbacks, a heater flame hook for which it is not necessary to perform machining in the body of the arm 100 and / or the heat shield 120, which weaken mechanically and / or thermally the flame catch.
  • a flame catch is simple design and easy assembly which reduces its cost.
  • it offers increased thermal and mechanical resistance due to the absence of areas of weakness.
  • the invention relates to a flame-holder for a turbojet's heating channel comprising a trough-shaped channel, a heat shield of the arm cavity and an air supply box housed in the cavity, characterized in that the arm, the protective shield and the air supply box are held together by a monoblock spacer having at least one spacer lug arranged to provide an air gap (e) between the screen thermal protection and at least one wall of the arm.
  • the air gap ear advantageously provides a channel between the shield and the arm to allow the passage of carbureted air.
  • the sole comprises means for holding the box.
  • the soleplate advantageously allows the box to be held without weakening the arm or its thermal protection screen.
  • a fuel injector is placed inside said arm cavity.
  • the sole comprises means for centering the injector.
  • the soleplate advantageously allows the injector to be centered without weakening the arm or its thermal protection screen. This advantageously still allows to maintain a constant distance between the injector and the air box which facilitates the air distribution of the air box towards the injectors.
  • the soleplate is welded to the air supply box which makes it possible to prevent any translation of the box into the arm.
  • the sole is in the form of a Y defining a central branch and two lateral branches, the central branch comprising a through hole for holding the box.
  • the shape of the soleplate advantageously makes it possible to overcome the differential expansions between the arm and the sole.
  • the through hole for holding the box advantageously allows to guide and block the air box.
  • the central branch comprises a through hole for centering the injector.
  • the invention relates to a turbojet heater heat pipe comprising at least one such flame catch.
  • the invention also relates to a turbojet engine comprising such a heating channel.
  • the figure 2 represents a part of a turbofan engine.
  • This engine only shows the ogival shape of the exhaust casing 3 at the rear of the gas turbine engine, inside the outer cylindrical casing 4.
  • the engine provides output of the engine turbine gas turbine, a hot primary gas flow, represented by the arrow P.
  • Part of the air sucked by the engine is simply compressed and bypasses the combustion chamber of the engine. This air constitutes the secondary flow, represented by the arrow S.
  • the two streams are mixed here downstream of a confluence section formed of an annular sheet.
  • This engine section is extended, in particular military-type aircraft, by a cylindrical heating channel 1 of the gas before the ejection nozzle. We see the upstream part of the heating channel 1 but not the nozzle. In certain flight phases, it is necessary to provide additional energy to the gases producing the thrust. This is provided by the heating, also called afterburning, gases in the heating channel. Fuel is injected into the gases by injectors such as those shown at 7, radially crossing the two veins, primary and secondary. Downstream of these Injectors, means forming flame hangers 10 are shaped so as to allow the retention of gases the time of their combustion.
  • These means comprise linearly radially star-shaped flame catchers 10 arranged in a plane substantially perpendicular to the motor axis, here immediately downstream of the confluence of the two primary and secondary flows. They are connected by ring sector arms 9 which, according to this type of heating device, are on the side of the secondary vein.
  • the radial flame hooks 10 are formed of radial arms 100 in the form of a chute, with a V or U-shaped cross-section, the edge of which is turned upstream with respect to the direction of flow of the gases.
  • the structure of the flame catch 10 is visible on the section of the figure 5 according to direction II-II of the figure 4 .
  • the arm 100 defines a cavity, between the upstream edge and the free downstream edges of the two walls 101a and 101b, occupied by an air supply box 120 taken from the vein of the secondary flow, a tubular injector 130 of fuel and a 110 thermal protection screen.
  • the screen 110 is shaped curved plate whose concavity is facing downstream.
  • the air supply box 120, the tubular fuel injector 130 and the thermal protection screen 110 are held in the arm 100, at the top, in the heating case and, at the bottom, by a rubber sole. spacing 150 whose role is to prevent them from being in contact, particularly in vibration operation.
  • the soleplate 150 makes it possible to fix the air supply box 120 and the injector 130 in the arm 100 without the need for drilling in zones thermally stressed both of the screen 110 and of the arm 100, which makes it possible to limit wear. .
  • the arm 100 and the tubular fuel injector 130 are directly fixed in the heating case.
  • the spacer sole 150 is substantially in the form of a Y comprising a central branch 150c, extending in its length in a direction X, which extend two lateral branches 150a, 150b substantially parallel.
  • Each lateral branch 150a, 150b, extending in the direction X, is terminated at its end by a circular spacer lug 151a, 151b each comprising a fixing orifice 152a, 152b arranged in the lateral branch 150a, 150b in a direction Y, orthogonal to the direction X.
  • the lateral branches 150a, 150b are of small thickness so as to be able to overcome the differential expansions between the arm 100 CMC and the sole 150 of metal. This also applies to an arm made of metallic material, differential expansions appearing because of the temperature differences between the metal parts.
  • the central branch 150c of the spacer sole 150 wider than the lateral branches 150a, 150b, is pierced at two places in its thickness along a direction Z.
  • a first through-hole 154 is provided at the base of the branch 150c and is intended to maintain an axial portion of the air supply box 120. This orifice will be designated thereafter holding orifice of the caisson 154.
  • a second through-hole for holding 156 is formed in the central branch 150c, between the holding orifice of the caisson 154 and the lateral branches 150a, 150b. This orifice 156 is intended to center the tubular fuel injector 130 in the arm 100. This orifice will be designated hereinafter the centering orifice of the injector 156.
  • the spacer sole 150 also has through-blocking orifices 155 formed in the width of the central branch 150c in the Y direction, orthogonal to the holding orifice of the caisson 154.
  • the outer surface of the box 120 is visible via the blocking orifices 155 whose function will be detailed later. .
  • the air supply box 120 and the tubular fuel injector 130 are centered in the upper part in the flame hook 10 and held in the lower part by the spacer sole 150.
  • the air box 120 has, in the upper part, a rolling head, allowing its centering in the arm.
  • the air supply box 120 is introduced axially, in the Z direction, into the spacing plate 150 via its holding orifice of the box 154 and is locked axially with the soleplate 150 by welding. During the welding step, material is provided on the outer surface of the box 120 which is visible via the locking holes 155.
  • the air box 120 is then fixedly held by the soleplate 150 as shown in FIG. figure 7 .
  • the tubular fuel injector 130 is, for its part, introduced axially in the direction Z into the centering orifice of the injector 156 in order to keep it away from the air supply box 120.
  • the distance between the casing 120 and the injector can be parameterized by adjusting the distance between the centering orifice of the injector 156 and the holding orifice of the casing 154 of the soleplate 150.
  • the circular air gap lugs 151a, 151b of the spacer sole 150 are arranged between the walls of the protective shield 110 and the walls of the arm 100.
  • the lug 151a is interposed between the wall 111a of the protection screen 110 and the wall 101a of the arm 100, the thickness of the lug 151a defining an air gap thickness (e) between said walls 101a, 111a.
  • the gap (e) forms a channel allowing the passage of carbureted air.
  • a cylindrical pin 160 passes successively through the wall 111a of the screen 110, the fixing orifice 152a of the lug and the wall 101a of the arm 100.
  • the lug 160 is retained by a washer 161 welded externally to the arm 100.
  • the assembly formed by the wall 101a of the arm 100, the wall 111a of the screen 110 and the lug 151a is held tight between the welded washer 161 and the head of the cylindrical pin 162.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Gas Burners (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Flammenhalter (10) für Nachverbrennungskanal eines Turboreaktors mit einem Arm (100) in Form einer Rinne, der mit einer Vertiefung, einem Wärmeschutzschirm (110) für die Vertiefung des Armes (100) und einer Kammer (120) zur Luftversorgung versehen ist, die in die Vertiefung eingearbeitet ist, dadurch gekennzeichnet, dass der Arm (100), der Schutzschirm(110) und die Kammer(120) zur Luftversorgung durch eine in einem Stück gefertigte Abstandschwelle (150) zusammengehalten werden, die zumindest ein Abstandschwellenohr (151a, 151b) enthält, das so angeordnet ist, dass zwischen dem Wärmeschutzschirm (110) und zumindest einer Wand des Armes (100) ein Luftspalt (e) bestehen bleibt.
  2. Flammenhalter nach Anspruch 1, bei dem die Schelle (150) eine Vorrichtung zum Festhalten der Kammer (120) enthält.
  3. Flammenhalter nach einem der Ansprüche 1 bis 2, bei dem im Inneren der besagten Vertiefung des Armes (100) eine Treibstoffeinspritzdüse (130) angebracht ist.
  4. Flammenhalter nach Anspruch 3, bei dem die Schwelle (150) eine Vorrichtung zum Zentrieren der Einspritzdüse (130) enthält.
  5. Flammenhalter nach einem der Ansprüche 1 bis 4, bei dem die Schwelle (150) mit der Kammer (120) zur Luftversorgung verschweißt ist.
  6. Flammenhalter nach einem der Ansprüche 1 bis 5, bei dem die Schwelle (150) eine Y-Form mit einem mittleren Ast (150c) und zwei seitlichen Ästen (150a, 150b) aufweist, wobei der mittlere Ast (150c) ein Durchgangsloch (154) zum Festhalten der Kammer (120) aufweist.
  7. Flammenhalter nach Anspruch 6 in Verbindung mit dem Anspruch 3, bei dem der mittlere Ast (150c) ein Durchgangsloch (156) zum Zentrieren der Einspritzdüse (130) enthält.
  8. Nachverbrennungskanal eines Turboreaktors mit zumindest einem Flammenhalter nach einem der Ansprüche 1 bis 7.
  9. Turboreaktor mit einem Nachverbrennungskanal nach Anspruch 8.
EP09153848A 2008-02-29 2009-02-27 Flammenhalter für Nachverbrennungskanal eines Turboreaktors mit einer Abstandschwelle, sowie Nachverbrennungskanal und Turboreaktor, der einen Nachverbrennungskanal umfasst Active EP2096357B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0801138A FR2928202A1 (fr) 2008-02-29 2008-02-29 Accroche flamme pour canal de rechauffe d'un turboreacteur avec une semelle d'ecartement, canal de rechauffe et turboreacteur comprenant un canal de rechauffe.

Publications (2)

Publication Number Publication Date
EP2096357A1 EP2096357A1 (de) 2009-09-02
EP2096357B1 true EP2096357B1 (de) 2010-09-15

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EP09153848A Active EP2096357B1 (de) 2008-02-29 2009-02-27 Flammenhalter für Nachverbrennungskanal eines Turboreaktors mit einer Abstandschwelle, sowie Nachverbrennungskanal und Turboreaktor, der einen Nachverbrennungskanal umfasst

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US (1) US8307658B2 (de)
EP (1) EP2096357B1 (de)
DE (1) DE602009000173D1 (de)
FR (1) FR2928202A1 (de)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2950416B1 (fr) * 2009-09-23 2012-04-20 Snecma Dispositif accroche-flammes comprenant un support de bras et un ecran de protection thermique monoblocs
US20140026590A1 (en) * 2012-07-25 2014-01-30 Hannes A. Alholm Flexible combustor bracket
RU2520598C1 (ru) * 2012-11-26 2014-06-27 Открытое акционерное общество "Конструкторское бюро химавтоматики" Устройство крепления теплозащиты к раме двигателя (варианты)
US9879862B2 (en) 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
JP6340918B2 (ja) * 2014-05-23 2018-06-13 株式会社Ihi 推力増強装置
CN104373964B (zh) * 2014-10-20 2016-08-17 北京航空航天大学 内置油杆的凹腔支板火焰稳定器
CA2988555C (en) 2015-06-16 2019-03-26 Ihi Corporation Engine aft section structure
RU2742592C1 (ru) * 2020-06-16 2021-02-08 Акционерное общество "Конструкторское бюро химавтоматики" Хомут кронштейна крепления агрегата к трубопроводу жидкостного ракетного двигателя
CN115164234B (zh) * 2022-05-12 2023-06-13 中国航发四川燃气涡轮研究院 加力燃烧室火焰稳定器

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FR655241A (fr) 1927-04-14 1929-04-16 Thomson Houston Comp Francaise Perfectionnements aux dispositifs de commutation des machines électriques, type métdyne
GB1139005A (en) * 1966-03-25 1969-01-08 Rolls Royce Improvements in or relating to gas turbine by-pass engines
FR1516562A (fr) * 1966-03-25 1968-03-08 Rolls Royce Moteur de turbine à gaz à dérivation
US3698186A (en) * 1970-12-24 1972-10-17 United Aircraft Corp Afterburner combustion apparatus
FR2709342B1 (fr) * 1993-08-25 1995-09-22 Snecma Dispositif de post combustion d'un turboréacteur.
US5396763A (en) * 1994-04-25 1995-03-14 General Electric Company Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield
US5396761A (en) * 1994-04-25 1995-03-14 General Electric Company Gas turbine engine ignition flameholder with internal impingement cooling
FR2869953B1 (fr) * 2004-05-05 2008-07-04 Snecma Moteurs Sa Dispositif d'alimentation en air et en carburant d'un anneau-bruleur dans une chambre de postcombustion
FR2873411B1 (fr) * 2004-07-21 2009-08-21 Snecma Moteurs Sa Turboreacteur avec des moyens de protection pour un dispositif d'injection de carburant, dispositif d'injection et tole de protection pour le turboreacteur
FR2899316B1 (fr) * 2006-03-30 2008-05-16 Snecma Sa Bras accroche-flammes d'une chambre de post-combustion

Also Published As

Publication number Publication date
US8307658B2 (en) 2012-11-13
DE602009000173D1 (de) 2010-10-28
FR2928202A1 (fr) 2009-09-04
EP2096357A1 (de) 2009-09-02
US20090260366A1 (en) 2009-10-22

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