EP2012061B2 - Brennkammer eines Gasturbinentriebwerks - Google Patents

Brennkammer eines Gasturbinentriebwerks Download PDF

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Publication number
EP2012061B2
EP2012061B2 EP08159737.9A EP08159737A EP2012061B2 EP 2012061 B2 EP2012061 B2 EP 2012061B2 EP 08159737 A EP08159737 A EP 08159737A EP 2012061 B2 EP2012061 B2 EP 2012061B2
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EP
European Patent Office
Prior art keywords
edge
deflectors
combustion chamber
seal cover
edges
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.)
Active
Application number
EP08159737.9A
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English (en)
French (fr)
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EP2012061A1 (de
EP2012061B1 (de
Inventor
Patrice Commaret
Didier Hernandez
Romain Lunel
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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Safran Aircraft Engines SAS
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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2012061A1 publication Critical patent/EP2012061A1/de
Application granted granted Critical
Publication of EP2012061B1 publication Critical patent/EP2012061B1/de
Publication of EP2012061B2 publication Critical patent/EP2012061B2/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
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • 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

Definitions

  • the present invention relates to the technical field of combustion chambers for a gas turbine engine. It targets in particular the back of the room. Finally, it relates to a gas turbine engine such as a turbojet engine equipped with such a combustion chamber.
  • a diverging conventional combustion chamber is illustrated on the figure 1 , which is an axial section showing one half of the combustion chamber, the other half of this being deduced by symmetry with respect to the axis of the engine (not shown).
  • the combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an external casing 132 and an internal casing 134, into which is introduced an oxidizer, ambient air, compressed coming from upstream of a compressor (not shown) via an annular diffusion duct 136.
  • This divergent combustion chamber 110 has two concentric walls: one external 112 and the other internal 114, which are coaxial and substantially conical. The walls flare from upstream to downstream. The external 112 and internal 114 walls of the combustion chamber 110 are connected together, upstream of the combustion chamber by a chamber bottom 116.
  • the chamber bottom 116 is a frustoconical annular piece, which extends between two substantially transverse planes flaring from downstream to upstream.
  • the chamber bottom 116 is connected to each of the two external 112 and internal 114 walls of the combustion chamber 110.
  • the chamber bottom 116 has a low taper. It is provided with injection systems 118 through which injectors 120 pass which introduce fuel to the upstream end of the combustion chamber 110 where the combustion reactions take place.
  • deflectors 122 are interposed between the hearth and the walls of the chamber bottom. These deflectors 122, one of which is shown in the figure 3 are substantially flat plates fixed by brazing on the chamber bottom 116 with a central opening 122a for the passage of the injection system.
  • the deflectors include two lateral walls 122b 122c along the radial edges, turned towards the wall of the chamber bottom and two tongues 122e 122f for guiding air along the transverse edges turned towards the hearth and creating a space with the walls 114 and 112 , internal respectively external, of the chamber.
  • the deflectors are cooled by the impacts of cooling air jets entering the combustion chamber 110 through cooling orifices 124 drilled in the chamber bottom 116.
  • the air forming these jets, flowing upstream downstream, is guided by chamber fairings 126, crosses the chamber bottom 116 through the cooling orifices, and comes to impact the upstream face of the deflectors 122.
  • the air is then guided radially inward and outward of the hearth to initiate the film for cooling the walls 114 and 112 respectively.
  • This guidance along the deflectors is provided by the side walls oriented radially. These walls also have a sealing function. By being in contact with or ensuring minimal play with the chamber bottom, they prevent air from interfering between two adjacent deflectors, entering the hearth and disturbing combustion. These disturbances have an impact on pollution and should be avoided. In fact, the performance in discharging pollutants, CO and CHx are liable to be degraded by the parasitic introduction of this cold air, particularly at engine idling speed where the clearance is greater.
  • convergent combustion chambers In the context of other engine architectures where the gas flow is globally convergent between the outlet of the compressor and the inlet of the turbine, so-called convergent combustion chambers are available, the external and internal walls of the combustion chamber are inclined by widening from downstream to upstream, and not from upstream to downstream as with the first combustion chambers mentioned above, said to be divergent. These converging combustion chambers can have a greater cone angle than the cone angle of the diverging combustion chambers.
  • Such a significant inclination of the combustion chamber has repercussions on the taper of the chamber bottom and on the position of the deflectors relative to the chamber bottom.
  • a combustion chamber is partially illustrated in the figure 2 , in axial section. In this figure appear an axial direction 100 parallel to the axis of the turbojet, the main direction 200 of the combustion chamber 210, and the angle ⁇ between these two axes 100, 200. Due to the significant inclination of the chamber combustion chamber 210, the chamber bottom 216 has a taper angle greater than for a converging combustion chamber bottom. When not only the inclination of the chamber bottom 216 is large, but also the injectors 220 are present in reduced number and / or that the combustion chamber 210 has a small diameter, this affects the distance between the chamber bottom and the plane deflectors.
  • the geometry of the chamber bottom can also make it difficult to make the necessary adjustments and tolerances between the wall of the chamber bottom and the deflectors.
  • the optimal functioning of the room is no longer guaranteed.
  • the variation in the clearance between the deflectors on the one hand and the deflectors and the chamber bottom on the other is large enough so that the solution using lateral walls along the radial edges of the deflectors is no longer satisfactory.
  • the present invention aims to provide an alternative to this solution.
  • the invention thus provides a combustion chamber as defined in claim 1.
  • the solution of the invention therefore consists in sealing the space between the deflectors so as not to be dependent on the geometry of the combustion chamber and of the chamber bottom in particular and to be able to absorb the dimensional variations linked to the operation of the room between the idle speed and full throttle.
  • the present invention also relates to a gas turbine engine comprising a combustion chamber as described above.
  • the deflector 10 comprises a flat part 10a with a central opening 10b corresponding to the housing of an injection system not shown. On the figure 5 , the opening is bordered by a collar 10b1 with shoulder for fixing in the chamber bottom.
  • the deflector comprises two longitudinal edges which are oriented in a radial direction relative to the axis of the motor, when it is in position. The longitudinal edge 10c and the edge 10d are straight.
  • the deflector 10 also comprises two transverse edges 10e and 10f both rounded to follow the curvature of the combustion chamber and curved in the direction of the interior of the combustion chamber for guiding the air.
  • Edge 10c left on the figure 4 , is straight and follows the radial profile of the deflector.
  • the edge 10d on the other side includes a rear recess relative to the face visible on the figure 4 , formed by a tongue 10d1 which extends the rear face of the wall of the deflector. This recess forms a longitudinal housing 10d10 for the edge 10'c of the adjacent deflector 10 '.
  • This deflector 10 ' is identical to the deflector 10. It includes a flat part 10'a, two longitudinal edges 10'c and 10'd and two rounded and curved transverse edges 10'e and 10'f.
  • the edge 10'd includes a longitudinal tab 10'd1 providing a housing 10'd10.
  • the deflectors are all identical and are mounted on the periphery of the chamber bottom, being fixed by the flanges of the openings for the injection systems.
  • the joint cover formed by the tongue 10d1 of each of the deflectors covers the edge 10'c of the adjacent deflector 10 'over a width sufficient to accommodate variations in expansion of the combustion chamber.
  • Each housing 10d10, 10'd10 is arranged to retain the edge 10c, 10'c of the adjacent deflector so that the leaks between two adjacent deflectors are reduced if not totally eliminated whatever the engine speed.
  • the deflectors are identical but the solution also includes the case where a first deflector comprises a joint cover along the two longitudinal edges cooperating with the simple edges of a second deflector without joint cover.
  • the efficiency is the same.
  • the assembly is however different and requires the manufacture of two part references.
  • FIGS 7, 8 and 9 represent an embodiment according to the invention with a grooved joint cover which improves the tightness compared to the previous solution.
  • the longitudinal edge 20d comprises a tongue 20d1 parallel to the wall of the deflector and providing a housing 20d10g in the form of a groove.
  • This groove is arranged so as to cooperate with the edge 20 ′ c of the adjacent deflector.
  • the edge 20'c forms a rear step to engage the groove 20d10g.
  • the clearance is sufficient to allow the expansion of the combustion chamber during the different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.
  • the deflectors can be all identical or alternating: one with joint covers on the two edges and the other with simple edges cooperating with the grooves of the edges with joint covers.
  • the figures 10 and 11 show an improvement between the deflectors and the chamber bottom.
  • the chamber bottom 2 comprises a radial groove 2r in the area where the joint cover of the deflector junction is placed. This groove 2r makes it possible to provide a sufficient air gap, when the joint covers are of a greater thickness than the clearance between the flat part 20a of the deflector and the wall of the chamber bottom.
  • the deflectors 30, 30 ' with a flat wall 30a, 30'a, a central opening 30b, 30'b, two longitudinal edges 30c, 30'c and 30d, 30'd and two rounded and curved transverse edges 30e, 30'e and 30f, 30'f.
  • the two longitudinal edges 30c, 30d; 30'c, 30'd each include a tongue 30c1, 30d1; 30'c1, 30'd1 parallel to the wall of the deflector and providing a housing 30c10g and 30d10g, 30'c10g, 304d10g in the shape of a groove.
  • These grooves are arranged so as to cooperate with an attached metal tongue 31.
  • the tongue is housed in the adjacent grooves 30d10g and 30'c10g.
  • the clearance is sufficient to allow the expansion of the combustion chamber during the different engine speeds while maintaining a sealing contact between the edge 20'c and the sides of the groove 20d10g.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)

Claims (9)

  1. Brennkammer eines Gasturbinenmotors, die ringförmig ist, umfassend eine Außenwand, eine Innenwand, eine Wand, welche die zwei Wände verbindet und einen Kammerboden bildet, Deflektoren (20) eines Brennkammerbodens eines Gasturbinenmotors, die in den Boden eingebracht sind, wobei die Deflektoren (20) einen Wandabschnitt (20a) parallel zum Kammerboden mit einer Öffnung für den Durchgang eines Injektors der Brennkammer, zwei Längsränder (20c, 20d) und zwei Querränder (20e, 20f) umfassen und wovon mindestens der eine der Längsränder eine Fugenabdeckung (20d1) umfasst, dadurch gekennzeichnet, dass die Fugenabdeckung eine Nut (20d10g) einrichtet, die eine Aufnahme entlang des Randes für den Rand (20'c) eines benachbarten Deflektors (20') bildet, um die Verbindungsstelle zwischen den zwei Rändern dicht zu machen und gleichzeitig ihr Zueinandergleiten zu ermöglichen, wenn sich die Wand des Kammerbodens dehnt.
  2. Brennkammer nach dem vorstehenden Anspruch, wobei die Querränder (20e, 20f) der Deflektoren (20) einen gekrümmten Wandabschnitt umfassen, wobei die Nut ebenfalls entlang der Längsränder des gekrümmten Abschnitts eingerichtet ist.
  3. Brennkammer nach einem der vorstehenden Ansprüche, wobei die Deflektoren (20) eine Fugenabdeckung (20d1) entlang eines Längsrands und einen Rand (20c) ohne Fugenabdeckung entlang des anderen Längsrands umfassen, wobei die zwei Ränder komplementär sind, um sich an einen Rand eines anderen gleichen Deflektors anzupassen, der Rand an Rand angeordnet ist.
  4. Brennkammer nach Anspruch 1 oder 2, wobei die Deflektoren (20) eine Fugenabdeckung entlang der zwei Längsränder umfassen.
  5. Brennkammer nach Anspruch 1, mit Deflektoren, umfassend eine Fugenabdeckung (20d1) entlang eines Längsrands und einen Rand (20c) ohne Fugenabdeckung entlang des anderen Längsrands, wobei die zwei Ränder komplementär sind, um sich an einen Rand eines anderen gleichen Deflektors anzupassen, der Rand an Rand angeordnet ist, wobei alle identisch sind.
  6. Brennkammer nach Anspruch 1, mit Deflektoren, umfassend eine Fugenabdeckung entlang der zwei Längsränder, und Deflektoren mit einfachen Rändern, umfassend zwei Längsränder, die komplementär sind zu den Fugenabdeckungen der Deflektoren, die eine Fugenabdeckung entlang der zwei Längsränder umfassen, wobei sich die Deflektoren, die eine Fugenabdeckung entlang der zwei Längsränder umfassen, mit den Deflektoren mit einfachen Rändern abwechseln.
  7. Brennkammer nach einem der Ansprüche 1, 5 oder 6, deren Kammerboden eine Rille umfasst, die einen Spalt zwischen dem Kammerboden und den Fugenabdeckungen einrichtet.
  8. Kammer konvergenter Art nach einem der Ansprüche 1, 5 bis 7.
  9. Gasturbinenmotor, umfassend eine Brennkammer (10) nach einem der Ansprüche 1, 5 bis 8.
EP08159737.9A 2007-07-05 2008-07-04 Brennkammer eines Gasturbinentriebwerks Active EP2012061B2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0704869A FR2918444B1 (fr) 2007-07-05 2007-07-05 Deflecteur de fond de chambre, chambre de combustion le comportant et moteur a turbine a gaz en etant equipe

Publications (3)

Publication Number Publication Date
EP2012061A1 EP2012061A1 (de) 2009-01-07
EP2012061B1 EP2012061B1 (de) 2016-12-07
EP2012061B2 true EP2012061B2 (de) 2020-06-17

Family

ID=39267949

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08159737.9A Active EP2012061B2 (de) 2007-07-05 2008-07-04 Brennkammer eines Gasturbinentriebwerks

Country Status (5)

Country Link
US (2) US20090019856A1 (de)
EP (1) EP2012061B2 (de)
CA (1) CA2636659C (de)
FR (1) FR2918444B1 (de)
RU (1) RU2498162C2 (de)

Families Citing this family (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2943403B1 (fr) 2009-03-17 2014-11-14 Snecma Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
CH704185A1 (de) * 2010-12-06 2012-06-15 Alstom Technology Ltd Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.
EP2954261B1 (de) * 2013-02-08 2020-03-04 United Technologies Corporation Gasturbinenbrennkammer
US9534784B2 (en) * 2013-08-23 2017-01-03 Pratt & Whitney Canada Corp. Asymmetric combustor heat shield panels
US8984896B2 (en) * 2013-08-23 2015-03-24 Pratt & Whitney Canada Corp. Interlocking combustor heat shield panels
GB201501817D0 (en) * 2015-02-04 2015-03-18 Rolls Royce Plc A combustion chamber and a combustion chamber segment
US10041679B2 (en) * 2015-06-24 2018-08-07 Delavan Inc Combustion systems
US10739001B2 (en) 2017-02-14 2020-08-11 Raytheon Technologies Corporation Combustor liner panel shell interface for a gas turbine engine combustor
US10718521B2 (en) 2017-02-23 2020-07-21 Raytheon Technologies Corporation Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor
US10677462B2 (en) 2017-02-23 2020-06-09 Raytheon Technologies Corporation Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor
US10830434B2 (en) 2017-02-23 2020-11-10 Raytheon Technologies Corporation Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor
US10823411B2 (en) 2017-02-23 2020-11-03 Raytheon Technologies Corporation Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor
FR3064050B1 (fr) * 2017-03-14 2021-02-19 Safran Aircraft Engines Chambre de combustion d'une turbomachine
US10941937B2 (en) 2017-03-20 2021-03-09 Raytheon Technologies Corporation Combustor liner with gasket for gas turbine engine
FR3078384B1 (fr) * 2018-02-28 2021-05-28 Safran Aircraft Engines Chambre de combustion a fond de chambre double
FR3081974B1 (fr) 2018-06-04 2020-06-19 Safran Aircraft Engines Chambre de combustion d'une turbomachine
US11408609B2 (en) * 2018-10-26 2022-08-09 Collins Engine Nozzles, Inc. Combustor dome tiles
US11143108B2 (en) 2019-03-07 2021-10-12 Pratt & Whitney Canada Corp. Annular heat shield assembly for combustor
US11226099B2 (en) * 2019-10-11 2022-01-18 Rolls-Royce Corporation Combustor liner for a gas turbine engine with ceramic matrix composite components
US20240271791A1 (en) * 2023-02-14 2024-08-15 Collins Engine Nozzles, Inc. Line replaceable fuel injector panels with single hatch installation

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU352573A1 (ru) * 1970-10-05 1983-06-23 Pinchuk V V Кольцева камера сгорани газотурбинного двигател
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4180974A (en) * 1977-10-31 1980-01-01 General Electric Company Combustor dome sleeve
JPS5915728A (ja) * 1982-07-19 1984-01-26 Central Res Inst Of Electric Power Ind 高熱曝露壁面の熱遮断構造
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
SU1753783A1 (ru) * 1990-02-27 1996-06-10 Моторостроительное конструкторское бюро Камера сгорания газотурбинного двигателя
GB2247522B (en) * 1990-09-01 1993-11-10 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (en) * 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
EP0591565B1 (de) * 1992-10-05 1996-01-24 Asea Brown Boveri Ag Leitschaufeleinhängung für axialdurchströmte Turbomaschine
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
GB2298267B (en) * 1995-02-23 1999-01-13 Rolls Royce Plc An arrangement of heat resistant tiles for a gas turbine engine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
EP1118806A1 (de) * 2000-01-20 2001-07-25 Siemens Aktiengesellschaft Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
EP1528343A1 (de) * 2003-10-27 2005-05-04 Siemens Aktiengesellschaft Keramischer Hitzeschildstein mit eingebetteten Verstärkungselementen zur Auskleidung einer Gasturbinenbrennkammerwand
JP4476152B2 (ja) * 2005-04-01 2010-06-09 三菱重工業株式会社 ガスタービン燃焼器
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.
FR2918443B1 (fr) * 2007-07-04 2009-10-30 Snecma Sa Chambre de combustion comportant des deflecteurs de protection thermique de fond de chambre et moteur a turbine a gaz en etant equipe

Also Published As

Publication number Publication date
RU2008127426A (ru) 2010-01-10
US20090019856A1 (en) 2009-01-22
FR2918444B1 (fr) 2013-06-28
FR2918444A1 (fr) 2009-01-09
US20130312420A1 (en) 2013-11-28
EP2012061A1 (de) 2009-01-07
RU2498162C2 (ru) 2013-11-10
EP2012061B1 (de) 2016-12-07
US8683806B2 (en) 2014-04-01
CA2636659A1 (fr) 2009-01-05
CA2636659C (fr) 2015-10-27

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