EP0506516A1 - Verbrennungsluftzufuhreinrichtung für eine Brennkammer einer Turbomaschine - Google Patents

Verbrennungsluftzufuhreinrichtung für eine Brennkammer einer Turbomaschine Download PDF

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Publication number
EP0506516A1
EP0506516A1 EP92400715A EP92400715A EP0506516A1 EP 0506516 A1 EP0506516 A1 EP 0506516A1 EP 92400715 A EP92400715 A EP 92400715A EP 92400715 A EP92400715 A EP 92400715A EP 0506516 A1 EP0506516 A1 EP 0506516A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
sleeve
enclosure
combustion
wall
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
EP92400715A
Other languages
English (en)
French (fr)
Other versions
EP0506516B1 (de
Inventor
Gérard Yves Georges Barbier
Xavier Marie Henri Bardey
Michel André Albert Desaulty
Serge Marcel Meunier
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0506516A1 publication Critical patent/EP0506516A1/de
Application granted granted Critical
Publication of EP0506516B1 publication Critical patent/EP0506516B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow

Definitions

  • FR-A-2 028 599 describes several variants of devices for adjusting the oxidant flow.
  • the invention relates to a device for adjusting the oxidant flow rate which is both simple and precise.
  • the subject of the invention is therefore a combustion chamber of a turbo-machine comprising: a combustion chamber, which is delimited by a wall and inside which combustion of a fuel is carried out; a peripheral enclosure, which surrounds said combustion enclosure and which is capable of containing an oxidizer under pressure; and, a plurality of oxidant intake orifices which pass through said wall and which are capable of establishing communication between the peripheral enclosure and the combustion enclosure.
  • At least one of said oxidant intake orifices is associated with a sleeve; which passes through it and is adjusted to it; which commnicates with the peripheral enclosure by an inlet opening device and with the combustion enclosure by a delivery opening device, the inside of the sleeve providing mutual communication between said inlet opening devices and repression; and which has a pivot axis about which it is pivotally mounted; however, that at least one of said inlet and outlet opening devices is asymmetrical with respect to said pivot axis.
  • the main advantage of the invention lies in the modulation of the distribution of the air flow in the different orifices of the flame tube, depending on the speed, by means of mobile elements which is the solution offering the most potential gains. on the different performances. It makes it possible to adjust the richness and the residence time in the primary zone according to the thermodynamic conditions, in order to be placed as close as possible to the optimal operating point.
  • the combustion chamber of FIG. 1 is of the annular type, of axis 1, and comprises an internal wall 2 and an external wall 3, which define between them the combustion chamber 4, as well as a casing 5, inside which said combustion chamber 4 is contained, this casing 5 being itself delimited by an internal envelope 6 and by an external envelope 7 .
  • the combustion chamber 4 is provided, at one of its ends, with a fuel injection device 8 combined with a device 9 for admitting primary oxidizer, and comprises, at its other end , an orifice 10 for discharging the burnt gases.
  • the casing 5 also contains, during the operation of the combustion chamber, a compressed oxidizer, such as compressed air, coming from a source of compressed oxidizer symbolized by the arrow F, generally constituted by an air compressor. .
  • orifices 11 for additional oxidant intake, connecting the casing 5 to the combustion chamber 4, orifices 11 for admission of secondary oxidant and / or dilution.
  • Other orifices 12 also establish communication between the casing 5 and the combustion chamber 4 and will more particularly be described below.
  • the orifice 12 in FIGS. 2 and 3 crosses the external wall 3 which has an opening 13 for this purpose.
  • a cylindrical duct 14 has a first transverse end shaped as a flange 15 perpendicular to the axis 16 of said duct 14, comprising an opening 26, and a second transverse end, contained in a plane P inclined relative to the axis 16 of the casing 14 and therefore comprising, seen in section, a sort of spout 17, and an opening 36.
  • a plate 18, forming a support washer, is screwed (19) to the outside face of the internal wall 3 and has an orifice 20.
  • a tubular section 21 has its internal wall 22 adjusted and made integral with the external face 23 of the cylindrical conduit 14; has its outer wall 24 rotatably mounted inside the orifice 20 of the plate 18; and is provided with a transverse flange 25, perpendicular to the axis 16 of the cylindrical conduit 14.
  • Figures 4 and 5 is similar to that of Figures 2 and 3 except the following feature: the cylindrical duct 14 is extended, beyond the flange 15, outside of the combustion chamber 4, by a section 27, the end of which constitutes a bottom 28 for closing off this section, and the cylindrical wall of which is crossed by an orifice 29 for communication of the casing 5 with the interior 12 of the section 27 and of the conduit 14.
  • the compressed oxidizer is admitted into the casing 5 according to a flow of direction L (substantially parallel to the direction H of gas flow inside the combustion chamber 4) and passes through the orifice 12 of the duct 14, either according to the arrow M (FIG. 4), on the one hand, by penetrating inside the orifice 12, passing directly through the orifice 29 located, like the spout 17, upstream from the axis 16 relative to the direction H of gas flow, on the other hand, arriving inside the combustion chamber 4 substantially in the same direction as direction H, ie according to arrow N (FIG. 5), on the one hand , bypassing the wall of the section 27 to penetrate inside the orifice 12 by crossing the orifice?
  • the spout 17 may be on the side opposite to the orifice 29.
  • a jacket for adjusting the flow rate passing through the orifice 12 may be provided.
  • the tubular section 21 extends beyond the plate 18 to near an external transverse rim 31 extending the bottom 28 of the section 27.
  • the tubular section 21 has an orifice 32 permanently disposed opposite the orifice 29 of the tubular section 27.
  • the jacket 30 has an orifice 33 which can be arranged opposite the orifices 29 and 32. This jacket can on the other hand be oriented around the axis 16, by means of a lever 34, which is integral with it and which passes through a lumen 35 formed in the wall of the section 27 and opposite to the orifice 32, and partially, or even completely, block the orifices 32 and 29 in certain embodiments.
  • a device for adjusting the value of the flow rate passing through the orifice 12 which is added to the possibility of orienting the assembly of the duct 14, the tubular section 21 and the jacket 30 around the axis 16.
  • the realization of figure 6 is c ompatible with the addition of a spout at the internal end of the duct 14, similar to the spout 17 of Figures 2 and 3, and, 4 and 5.
  • the rotation controls of the various cylindrical conduits 14 are advantageously coupled, for example by means of individual rack and pinion systems, to a single motor device for adjusting the rotations of all the conduits 14 simultaneously.
  • a single motor device for adjusting the orientations of all the liners 30 of the embodiment according to FIG. 6 is simultaneously coupled to the various levers 34 for adjusting the orientation of said liners and allows simultaneous adjustments of the oxidant flow rates passing through. the holes 12.
  • FIGS. 2 and 3 makes it possible to modify the direction of introduction (arrows J or K) of the oxidizer admitted into the combustion chamber 4 relative to the direction H of general flow of gases inside said combustion chamber 4.
  • the transit time of the oxidizer is therefore adjustable by this means, this adjustment being useful to enable satisfactory operation to be obtained at very different gaits, previously almost incompatible, such as those of operations at full load and in slow motion.
  • the gradient for adjusting the transit time of the gases inside the combustion chamber 4 is increased compared to that obtained with the embodiment of FIGS. 2 and 3.
  • FIG. 6 also makes it possible to adjust the value at the flow rate of oxidant admitted into the combustion chamber 4. It is recalled that this solution is moreover compatible with those providing for a spout 17 (FIGS. 2 to 5) to the internal end of the cylindrical duct 14.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Exhaust Gas After Treatment (AREA)
EP92400715A 1991-03-20 1992-03-18 Verbrennungsluftzufuhreinrichtung für eine Brennkammer einer Turbomaschine Expired - Lifetime EP0506516B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9103374A FR2674317B1 (fr) 1991-03-20 1991-03-20 Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
FR9103374 1991-03-20

Publications (2)

Publication Number Publication Date
EP0506516A1 true EP0506516A1 (de) 1992-09-30
EP0506516B1 EP0506516B1 (de) 1994-11-30

Family

ID=9410929

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92400715A Expired - Lifetime EP0506516B1 (de) 1991-03-20 1992-03-18 Verbrennungsluftzufuhreinrichtung für eine Brennkammer einer Turbomaschine

Country Status (4)

Country Link
US (1) US5235805A (de)
EP (1) EP0506516B1 (de)
DE (1) DE69200735T2 (de)
FR (1) FR2674317B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0676590A1 (de) * 1994-04-08 1995-10-11 ROLLS-ROYCE plc Gasturbinenbrennkammer
WO2012113553A1 (de) * 2011-02-25 2012-08-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer
WO2015197954A1 (fr) * 2014-06-24 2015-12-30 Turbomeca Ensemble pour chambre de combustion de turbomachine comprenant un bossage et un élément annulaire
RU167336U1 (ru) * 2016-04-06 2017-01-10 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Жаровая труба камеры сгорания газотурбинного двигателя

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DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
GB9919981D0 (en) * 1999-08-24 1999-10-27 Rolls Royce Plc Combustion apparatus
US6351949B1 (en) * 1999-09-03 2002-03-05 Allison Advanced Development Company Interchangeable combustor chute
US6331110B1 (en) * 2000-05-25 2001-12-18 General Electric Company External dilution air tuning for dry low NOx combustors and methods therefor
US6499993B2 (en) 2000-05-25 2002-12-31 General Electric Company External dilution air tuning for dry low NOX combustors and methods therefor
GB2379499B (en) 2001-09-11 2004-01-28 Rolls Royce Plc Gas turbine engine combustor
US7000396B1 (en) * 2004-09-02 2006-02-21 General Electric Company Concentric fixed dilution and variable bypass air injection for a combustor
WO2007003031A1 (en) * 2005-07-05 2007-01-11 Véronneau, Stéphane Combustor configurations
US20090260340A1 (en) * 2008-04-17 2009-10-22 General Electric Company Combustor of a Turbine, a Method of Retro-Fitting a Combustor of a Turbine and a Method of Building a Combustor of a Turbine
US8590313B2 (en) * 2008-07-30 2013-11-26 Rolls-Royce Corporation Precision counter-swirl combustor
US9010123B2 (en) * 2010-07-26 2015-04-21 Honeywell International Inc. Combustors with quench inserts
US9062884B2 (en) * 2011-05-26 2015-06-23 Honeywell International Inc. Combustors with quench inserts
US20130283806A1 (en) * 2012-04-26 2013-10-31 General Electric Company Combustor and a method for repairing the combustor
US20130305729A1 (en) * 2012-05-21 2013-11-21 General Electric Company Turbomachine combustor and method for adjusting combustion dynamics in the same
DE102012022259A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
EP2735796B1 (de) * 2012-11-23 2020-01-01 Ansaldo Energia IP UK Limited WAND EINER HEIßGASDURCHGANGSKOMPONENTE EINER GASTURBINE UND VERFAHREN ZUM VERSTÄRKEN DES BETRIEBSVERHALTENS EINER GASTURBINE
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US10151486B2 (en) * 2014-01-03 2018-12-11 United Technologies Corporation Cooled grommet for a combustor wall assembly
EP2957833B1 (de) 2014-06-17 2018-10-24 Rolls-Royce Corporation Brennkammeranordnung mit rinnen
WO2016013585A1 (ja) * 2014-07-25 2016-01-28 三菱日立パワーシステムズ株式会社 燃焼器用筒体、燃焼器及びガスタービン
US9909549B2 (en) 2014-10-01 2018-03-06 National Technology & Engineering Solutions Of Sandia, Llc Ducted fuel injection
US10788212B2 (en) * 2015-01-12 2020-09-29 General Electric Company System and method for an oxidant passageway in a gas turbine system with exhaust gas recirculation
US20160209035A1 (en) * 2015-01-16 2016-07-21 Solar Turbines Incorporated Combustion hole insert with integrated film restarter
KR101843961B1 (ko) * 2015-05-27 2018-03-30 두산중공업 주식회사 회전가능한 공기유도캡이 마련된 연소기 챔버.
US10161626B2 (en) 2015-07-01 2018-12-25 National Technology & Engineering Solutions Of Sandia, Llc Ducted fuel injection
US10138855B2 (en) 2015-07-01 2018-11-27 National Technology & Engineering Solutions Of Sandia, Llc Ducted fuel injection with ignition assist
JP2019505721A (ja) * 2016-01-13 2019-02-28 ナショナル テクノロジー アンド エンジニアリング ソリューションズ オブ サンディア， エルエルシー ダクト式燃料噴射システム及び方法
US11137144B2 (en) 2017-12-11 2021-10-05 General Electric Company Axial fuel staging system for gas turbine combustors
US11187415B2 (en) * 2017-12-11 2021-11-30 General Electric Company Fuel injection assemblies for axial fuel staging in gas turbine combustors
US11255543B2 (en) * 2018-08-07 2022-02-22 General Electric Company Dilution structure for gas turbine engine combustor
US11248789B2 (en) 2018-12-07 2022-02-15 Raytheon Technologies Corporation Gas turbine engine with integral combustion liner and turbine nozzle
US11572835B2 (en) * 2021-05-11 2023-02-07 General Electric Company Combustor dilution hole
US11959643B2 (en) * 2021-06-07 2024-04-16 General Electric Company Combustor for a gas turbine engine
CN114484497A (zh) * 2021-11-30 2022-05-13 北京动力机械研究所 一种紧凑一体化设计的冷却掺混斗

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FR2284089A1 (fr) * 1974-09-06 1976-04-02 Mitsubishi Heavy Ind Ltd Appareil de combustion d'un combustible
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Publication number Priority date Publication date Assignee Title
FR2284089A1 (fr) * 1974-09-06 1976-04-02 Mitsubishi Heavy Ind Ltd Appareil de combustion d'un combustible
EP0182687A1 (de) * 1984-10-30 1986-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injektionssystem mit variabler Geometrie
EP0248731A1 (de) * 1986-06-04 1987-12-09 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0676590A1 (de) * 1994-04-08 1995-10-11 ROLLS-ROYCE plc Gasturbinenbrennkammer
US5590530A (en) * 1994-04-08 1997-01-07 Rolls-Royce Plc Fuel and air mixing parts for a turbine combustion chamber
WO2012113553A1 (de) * 2011-02-25 2012-08-30 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenbrennkammer
WO2015197954A1 (fr) * 2014-06-24 2015-12-30 Turbomeca Ensemble pour chambre de combustion de turbomachine comprenant un bossage et un élément annulaire
CN106471312A (zh) * 2014-06-24 2017-03-01 赛峰直升机发动机公司 包括凸台和环形元件的用于涡轮发动机燃烧室的组件
CN106471312B (zh) * 2014-06-24 2019-03-01 赛峰直升机发动机公司 包括凸台和环形元件的用于涡轮发动机燃烧室的组件
US10941943B2 (en) 2014-06-24 2021-03-09 Safran Helicopter Engines Assembly for turbomachine combustion chamber comprising a boss and an annular element
RU167336U1 (ru) * 2016-04-06 2017-01-10 Публичное акционерное общество "Научно-производственное объединение "Сатурн" Жаровая труба камеры сгорания газотурбинного двигателя

Also Published As

Publication number Publication date
DE69200735D1 (de) 1995-01-12
FR2674317A1 (fr) 1992-09-25
DE69200735T2 (de) 1995-04-27
FR2674317B1 (fr) 1993-05-28
US5235805A (en) 1993-08-17
EP0506516B1 (de) 1994-11-30

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