EP1873458A1 - Anordnung für eine Gasturbinenbrennkammer mit einem Deflektor mit Flansch - Google Patents

Anordnung für eine Gasturbinenbrennkammer mit einem Deflektor mit Flansch Download PDF

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Publication number
EP1873458A1
EP1873458A1 EP07110586A EP07110586A EP1873458A1 EP 1873458 A1 EP1873458 A1 EP 1873458A1 EP 07110586 A EP07110586 A EP 07110586A EP 07110586 A EP07110586 A EP 07110586A EP 1873458 A1 EP1873458 A1 EP 1873458A1
Authority
EP
European Patent Office
Prior art keywords
injection system
chamber bottom
flange
bowl
annular
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.)
Granted
Application number
EP07110586A
Other languages
English (en)
French (fr)
Other versions
EP1873458B1 (de
Inventor
David Locatelli
Romain Lunel
Thomas Noel
Denis Sandelis
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
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1873458A1 publication Critical patent/EP1873458A1/de
Application granted granted Critical
Publication of EP1873458B1 publication Critical patent/EP1873458B1/de
Active legal-status Critical Current
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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
    • F23R3/04—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
    • 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
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation

Definitions

  • the present invention relates to the general field of turbomachine combustion chambers. It relates more particularly to an arrangement of a combustion chamber of the type comprising a chamber bottom pierced with at least one circular opening, an injection system associated with the opening and a deflector mounted on the downstream side of the chamber bottom in the opening.
  • annular turbomachine combustion chamber comprises two longitudinal annular walls (an inner wall and an outer wall) which are connected at their respective upstream end by an equally annular transverse wall forming a chamber bottom. It is provided with a plurality of regularly spaced circular openings and in which are mounted systems for injecting an air / fuel mixture to be burned inside the combustion chamber.
  • the fuel is supplied to the injection systems via injectors integral with the turbomachine casing and whose heads are centered on the injection systems.
  • the air it is introduced into each injection system by means of one or more air spirals opening downstream of the head of the fuel injector.
  • a flared bowl downstream is mounted in each opening to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber.
  • a deflector mounted in each opening of the bottom chamber of the downstream side thereof provides thermal protection of the chamber bottom against the high temperatures of the gases from the combustion of the air / fuel mixture in the combustion chamber.
  • the bowl of the injection system with a flange which projects into the interior of the chamber bottom and which extends parallel thereto.
  • a collar has the main function of protecting the injection system against combustion flames in case of decentering of the injection system relative to the chamber bottom.
  • the collar of the bowl which must pass through the opening of the chamber bottom necessarily has a diameter smaller than that of the opening.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing an arrangement for a turbomachine combustion chamber which makes it possible to effectively protect the injection system against combustion flames regardless of the decentering of the injection system with respect to the room bottom, while ensuring none of its component parts fall into the combustion chamber in the event of breakage of solder or solder.
  • a turbomachine combustion chamber comprising a chamber bottom pierced with at least one substantially circular opening, a deflector mounted on the downstream side of the chamber bottom in the opening via an annular sleeve, an injection system associated with the opening and comprising a downstream flared bowl that passes through the opening, and means for allowing an off-centering of the injection system with respect to the chamber bottom and in which, according to the invention, the deflector comprises an annular flange extending radially inwards and the injection system bowl has at its downstream end an annular groove open towards the outside and aligned radially with the flange of the deflector so that it can retract into said groove in case of decentering of the injection system relative to the chamber bottom.
  • all the constituent parts of the injection system may be of diameter greater than that of the opening of the chamber bottom and mounted upstream, which ensures that none of these parts can pass through the opening and fall inside the combustion chamber especially in case of solder or defective welding.
  • the annular groove of the bowl is formed of two axially spaced lateral walls connected by an annular bottom, the distance between said side walls of the groove being greater than the thickness of the flange of the deflector. so as to allow a circulation of the ventilation air regardless of the decentering of the injection system relative to the chamber bottom.
  • the means making it possible to allow an off-centering of the injection system with respect to the chamber bottom consist of a clamping ring mounted on the upstream side of the chamber bottom and fixed against the sheath. with which they define an open annular groove on the axis side the opening of the chamber bottom, the bowl of the injection system further comprising an annular flange adapted to slide radially in the groove formed by the clamping ring and the sleeve.
  • the flange of the bowl is extended downstream by a substantially cylindrical portion which connects to the groove by an annular shoulder.
  • the shoulder of the bowl is advantageously pierced with a plurality of ventilation holes opening on the upstream side of the chamber bottom and opening on the downstream side thereof facing the flange of the deflector.
  • the radial height of the flange of the deflector is preferably at least equal to that of the flange of the bowl so as to protect the injection system regardless of the decentering of the injection system by compared to the chamber bottom.
  • the injection system further comprises at least one air swirler fixed to the upstream end of the bowl and a centering ring attached to the upstream end of the swirler. air and surrounding a fuel injector.
  • the invention also relates to a combustion chamber and a turbomachine comprising an arrangement as defined above.
  • Figures 1 to 3 partially show a sectional view of a turbomachine combustion chamber 2 equipped with an arrangement according to the invention.
  • such a combustion chamber 2 is formed of an inner longitudinal annular wall and an outer longitudinal annular wall (these walls are not shown in FIG. 1), these walls being connected at their end. respective upstream by a transverse annular wall 4 forming chamber bottom.
  • the chamber bottom 4 has an upstream side 4a and a downstream side 4b, the latter being directed towards the inside of the combustion chamber 2.
  • the chamber bottom is pierced with a plurality of openings 6 which are regularly spaced apart and each having a substantially circular shape of axis XX.
  • An injection system 8 of an air / fuel mixture is associated with each of these openings 6.
  • a deflector 10 protecting the chamber bottom 4 of the combustion flames is also mounted in each of the openings 6 on the downstream side 4b of the chamber bottom via an annular sleeve 12 projecting from the upstream side.
  • the deflector 10 has an annular flange 14 which extends radially inwards (that is to say towards the X-X axis of the opening 6 of the chamber bottom). As explained later, this flange 14 of the baffle has the role of protecting the injection system against combustion flames.
  • Each injection system 8 has an axis of revolution Y-Y and consists in particular of a fuel injector integral with the turbomachine casing (not shown in the figures).
  • the head 16 of the injector is disposed on the upstream side 4a of the chamber bottom 4 and is centered on the Y-Y axis of the injection system via a centering ring 18 which surrounds it.
  • One or more air swivels 20 optionally provided with a venturi 22 are attached to the downstream end of the centering ring 18 of the injection system. This or these air swirlers 20 allow air to enter the injection system in a substantially radial direction and to mix with the fuel delivered by the head 16 of the fuel injector. The air / fuel mixture then enters the combustion chamber 2 to be ignited.
  • Each injection system 8 also comprises a so-called pinch ring 24 which is mounted on the upstream side 4a of the chamber bottom 4 and fixed against the sleeve 12 for holding the deflector 10.
  • This pinch ring 24 is centered on the axis XX of the opening 6 of the chamber bottom and defines with the sleeve 12 an annular groove 26 which is open on the side of the axis XX.
  • Each injection system 8 further comprises a bowl 28 fixed against the downstream end of the air swirler 20 and whose function is to ensure a good distribution of the air / fuel mixture in the primary zone of the combustion chamber.
  • the bowl 28 is mounted in the corresponding opening 6 of the chamber bottom 4 and passes therethrough. It is generally in the form of a ring centered on the YY axis of the injection system and terminates at its downstream end by a U-shaped annular groove 30 which is open towards the outside (ie that is to say on the opposite side to the axis XX of the opening of the chamber bottom) and radially aligned with the flange 14 of the deflector 10.
  • the bowl 28 At its upstream end, the bowl 28 comprises an annular flange 32 mounted on the upstream side 4a of the chamber bottom 4 and able to slide radially inside the groove 26 formed between the clamping ring 24 and the sleeve 12 for holding the deflector 10 so as to allow an off-centering of the injection system 8 with respect to the chamber bottom 4.
  • the head 16 of the fuel injector and the entire injection system 8 are slidably mounted relative to the chamber bottom 4 in order to make up for the thermal expansion gaps between the casing and the combustion chamber. With this type of arrangement, the head 16 of the fuel injector therefore remains permanently centered with respect to the injection system 8.
  • the flange 32 of the bowl is extended downstream by a substantially cylindrical portion 34 of smaller diameter than that of the opening 6 and which is connected to the groove 30 by an annular shoulder 36 on the upstream side thereof.
  • the groove 30 is disposed behind an annular flange 38 which extends radially outwards and whose diameter is smaller than that of the shoulder 36.
  • the groove 30 of the bowl is formed of two annular lateral walls which are spaced axially and connected at their inner end by an annular bottom 40, one of these walls 42 being connected at its outer end to the shoulder 36 and the other wall 44 being connected at its outer end to the flange 38.
  • the flange 38 is the part of the bowl which is located furthest downstream. This flange is extended upstream by a portion 46 which is flared downstream, this flared portion 46 extending itself upstream by a cylindrical portion 48 which is concentric with the cylindrical portion 34 of the bowl (and of smaller diameter than this) and is connected to the air swirler 20.
  • the flared portion 46 of the bowl is pierced with a plurality of air introduction holes 50.
  • the shoulder 36 of the bowl is also pierced with a plurality of ventilation holes 52 opening on the upstream side of the chamber bottom 4 and opening on the downstream side thereof facing the collar 14 of the deflector 10.
  • the air flowing through these ventilation holes 52 is cooled by the upstream flange 14 of the baffle, then flows into the groove 30 of the bowl to create a film of air flowing thereafter radially along the downstream side of the deflector 10 so to cool the latter.
  • FIG. 2 represents one of the two possible cases of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is offset radially outwards with respect to the axis XX of the opening of the chamber bottom).
  • the radial distance separating the shoulder 36 from the bottom 40 of the groove 30 of the bowl is preferably at least equal to the radial height of the flange 14 of the baffle 10 so that this flange can fully retract into the throat of the bowl.
  • the flange 32 of the injection system which is completely retracted into the groove 26 is thus well protected against combustion flames.
  • FIG. 3 represents the other possible case of maximum decentering between the injection system and the chamber bottom (the axis of revolution YY of the injection system is shifted radially inwards with respect to the axis XX of the opening of the chamber floor).
  • the flange 14 of the baffle 10 continues to perform its role of thermal protection of the injection system against combustion flames by completely covering the flange 32. This is due to the fact that the radial height of the flange 14 of the flange deflector is preferably at least equal to that of the flange 32 of the bowl.
  • the distance separating the lateral walls 42, 44 of the groove 30 of the bowl is greater than the thickness of the collar 14 of the deflector 10 so as to allow a circulation of the ventilation air passing through the holes 52 drilled in the shoulder 36 whatever the decentering of the injection system relative to the chamber bottom.
  • the ventilation air through the holes 52 continues to flow inside the groove 30 bypassing the flange 14 of the baffle.
  • the assembly of the arrangement according to the invention is carried out as follows.
  • the sleeve 12 for holding the deflector, the bowl 28, the clamping ring 24, the air swirler 20 and the centering ring 18 are mounted upstream (that is to say by the upstream side 4a of the chamber bottom 4) and fixed to each other (soldered or welded for example).
  • the deflector 10 is mounted in the opening 6 of the chamber bottom 4 downstream (that is to say by the downstream side 4b of the chamber bottom) and then fixed to the sheath 12.
  • the flange 14 thereof may have a smaller diameter than the opening 6 of the chamber bottom 4 which is chosen according to the maximum deviations of possible decentering of the system injection in relation to the chamber bottom so as to permanently ensure thermal protection of the injection system against the combustion flames.
EP07110586A 2006-06-29 2007-06-19 Anordnung für eine Gasturbinenbrennkammer mit einem Deflektor mit Flansch Active EP1873458B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0652718A FR2903172B1 (fr) 2006-06-29 2006-06-29 Agencement pour chambre de combustion de turbomachine ayant un defecteur a collerette

Publications (2)

Publication Number Publication Date
EP1873458A1 true EP1873458A1 (de) 2008-01-02
EP1873458B1 EP1873458B1 (de) 2011-08-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP07110586A Active EP1873458B1 (de) 2006-06-29 2007-06-19 Anordnung für eine Gasturbinenbrennkammer mit einem Deflektor mit Flansch

Country Status (5)

Country Link
US (1) US7823392B2 (de)
EP (1) EP1873458B1 (de)
CA (1) CA2592626C (de)
FR (1) FR2903172B1 (de)
RU (1) RU2435105C2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010136287A2 (en) * 2009-05-27 2010-12-02 Siemens Aktiengesellschaft Burner, operating method and assembly method
WO2012025682A2 (fr) 2010-08-27 2012-03-01 Snecma 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
FR2970551A1 (fr) * 2011-01-14 2012-07-20 Snecma Nez d'injecteur demontable pour injecteur de carburant de chambre annulaire de combustion de turbomachine d'aeronef
FR2987428A1 (fr) * 2012-02-23 2013-08-30 Snecma Liaison mecanique amelioree entre un nez d'injecteur et une bague de traversee d'un systeme d'injection pour chambre de combustion de turbomachine

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US7628019B2 (en) * 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
FR2952166B1 (fr) * 2009-11-05 2012-01-06 Snecma Dispositif melangeur de carburant pour chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
US20120137691A1 (en) * 2010-12-01 2012-06-07 Bottcher Andreas Gas turbine assembly and method therefor
US9488105B2 (en) 2010-12-01 2016-11-08 Siemens Aktiengesellschaft Gas turbine assembly and method therefor
FR2986856B1 (fr) * 2012-02-15 2018-05-04 Safran Aircraft Engines Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine
JP2015512500A (ja) * 2012-03-29 2015-04-27 アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ ガスタービン燃焼器
GB201321193D0 (en) * 2013-12-02 2014-01-15 Rolls Royce Plc A combustion chamber assembly
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
RU2677914C1 (ru) * 2018-04-10 2019-01-22 Анатолий Иванович Софронов Турбодвигатель внутреннего сгорания
FR3082284B1 (fr) * 2018-06-07 2020-12-11 Safran Aircraft Engines Chambre de combustion pour une turbomachine
FR3083264B1 (fr) * 2018-06-29 2021-06-18 Safran Aircraft Engines Dispositif de guidage dans une chambre de combustion
FR3103540B1 (fr) * 2019-11-26 2022-01-28 Safran Aircraft Engines Système d'injection de carburant d'une turbomachine, chambre de combustion comprenant un tel système et turbomachine associée

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EP0833107A1 (de) * 1996-09-26 1998-04-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aerodynamisches Einspritzsystem zur Einspritzung eines Brennstoff-Luft-Gemisches
FR2825778A1 (fr) * 2001-06-06 2002-12-13 Snecma Moteurs Liaison coulissante entre un systeme d'injection d'une chambre de combustion et un fond de cette chambre de combustion
EP1314933A1 (de) * 2001-11-21 2003-05-28 Hispano Suiza Mehrstufiges Einspritzsystem eines Luft/Brennstoff-Gemisches in einer Gasturbinenbrennkammer

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Publication number Priority date Publication date Assignee Title
EP0833107A1 (de) * 1996-09-26 1998-04-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Aerodynamisches Einspritzsystem zur Einspritzung eines Brennstoff-Luft-Gemisches
FR2825778A1 (fr) * 2001-06-06 2002-12-13 Snecma Moteurs Liaison coulissante entre un systeme d'injection d'une chambre de combustion et un fond de cette chambre de combustion
EP1314933A1 (de) * 2001-11-21 2003-05-28 Hispano Suiza Mehrstufiges Einspritzsystem eines Luft/Brennstoff-Gemisches in einer Gasturbinenbrennkammer

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010136287A2 (en) * 2009-05-27 2010-12-02 Siemens Aktiengesellschaft Burner, operating method and assembly method
WO2010136287A3 (en) * 2009-05-27 2012-05-18 Siemens Aktiengesellschaft Burner, operating method and assembly method
CN102597632A (zh) * 2009-05-27 2012-07-18 西门子公司 燃烧器、操作方法和组装方法
RU2541482C2 (ru) * 2009-05-27 2015-02-20 Сименс Акциенгезелльшафт Горелка и газовая турбина, содержащая такую горелку
US9127842B2 (en) 2009-05-27 2015-09-08 Siemens Aktiengesellschaft Burner, operating method and assembly method
CN102597632B (zh) * 2009-05-27 2016-08-24 西门子公司 燃烧器、操作方法和组装方法
WO2012025682A2 (fr) 2010-08-27 2012-03-01 Snecma 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
FR2964177A1 (fr) * 2010-08-27 2012-03-02 Snecma 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
WO2012025682A3 (fr) * 2010-08-27 2012-05-10 Snecma 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
US9310083B2 (en) 2010-08-27 2016-04-12 Snecma Combustion chamber for an aircraft engine, and method for attaching an injection system in a combustion chamber of an aircraft engine
FR2970551A1 (fr) * 2011-01-14 2012-07-20 Snecma Nez d'injecteur demontable pour injecteur de carburant de chambre annulaire de combustion de turbomachine d'aeronef
FR2987428A1 (fr) * 2012-02-23 2013-08-30 Snecma Liaison mecanique amelioree entre un nez d'injecteur et une bague de traversee d'un systeme d'injection pour chambre de combustion de turbomachine

Also Published As

Publication number Publication date
CA2592626C (fr) 2014-04-08
RU2007124389A (ru) 2009-01-10
FR2903172A1 (fr) 2008-01-04
US7823392B2 (en) 2010-11-02
CA2592626A1 (fr) 2007-12-29
US20080000447A1 (en) 2008-01-03
FR2903172B1 (fr) 2008-10-17
RU2435105C2 (ru) 2011-11-27
EP1873458B1 (de) 2011-08-10

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