EP0598662B1 - Aerodynamic injection system for a combustion chamber - Google Patents

Aerodynamic injection system for a combustion chamber Download PDF

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Publication number
EP0598662B1
EP0598662B1 EP93402788A EP93402788A EP0598662B1 EP 0598662 B1 EP0598662 B1 EP 0598662B1 EP 93402788 A EP93402788 A EP 93402788A EP 93402788 A EP93402788 A EP 93402788A EP 0598662 B1 EP0598662 B1 EP 0598662B1
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EP
European Patent Office
Prior art keywords
injection
combustion chamber
fuel
apertures
bowls
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.)
Expired - Lifetime
Application number
EP93402788A
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German (de)
French (fr)
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EP0598662A1 (en
Inventor
Denis Roger Henri Ansart
Denis Jean Maurice 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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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Publication of EP0598662A1 publication Critical patent/EP0598662A1/en
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Publication of EP0598662B1 publication Critical patent/EP0598662B1/en
Anticipated expiration legal-status Critical
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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
    • F23R3/42—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
    • F23R3/02—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

Definitions

  • the present invention relates to an aerodynamic injection system of an annular combustion chamber, comprising at least one injection head having a plurality of air and fuel injection devices regularly distributed circumferentially in the chamber bottom.
  • each of the fuel and air injection devices comprises a fuel injector, a spin external turbulence for the passage of the fuel atomizing air and a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air in the sprayed fuel cone.
  • the object of the present invention is to make a modification to the bowls in order to reduce the number of injectors without impairing the proper functioning of the injection chamber.
  • the web has a cross section of substantially elliptical shape, the axis of smaller dimension being disposed in an axial plane of the combustion chamber, and in that the injector has a plurality of holes fuel injection of different diameters.
  • This arrangement makes it possible to obtain a more flat flame front, by playing on the different diameters of the fuel injection holes.
  • the chamber may have a single injection head or two injection heads spaced radially. Equipping a two-headed chamber with elliptical-shaped bowls according to the invention makes it possible to increase the permeability of the chamber bottom and therefore the average richness near the injectors.
  • FIGS 1 and 2 schematically show the arrangement of bowls 1 of the prior art in the chamber bottom 2 of an annular combustion chamber 3 of a turbomachine having a single injection head.
  • the combustion chamber 3 is delimited by an interior ferrule 4 and an exterior ferrule 5 connected by the chamber bottom 2.
  • the bowls 1 of frustoconical shape and of circular cross section are arranged upstream of the chamber bottom 2 and they each surround a fuel injector 6 with interposition of a turbulence spin 7.
  • the bowls 1 comprise a web 8 flared downstream in the direction of gas flow and having a row of bow holes 9 for the injection of air in the sprayed fuel cone.
  • the fuel is delivered through orifices 10 formed in the injector 6 and is sprayed by the swirling air penetrating through the swirling spin 7.
  • the consecutive bowls 1a and 1b are located at a distance X from each other and the distance Y separating two neighboring injectors 6a and 6b is equal to the distance X increased by the diameter of a bowl 1.
  • the bowls 1 have a veil 8 which has a cross section of elliptical shape, the axis of smaller dimension 11 being disposed in an axial plane of the combustion chamber 3.
  • the orifice 12 allowing the fixing of the bowl 1 of the invention in the bottom of chamber 2 also has a elliptical section.
  • the bowl holes 9 are no longer equidistant from the injector 6.
  • the bowl holes 9 can be equidistant from each other and have the same diameter. However, they can also be placed at variable intervals in order to distribute the air introduced as necessary. Likewise, they can be divided into sectors comprising bowl holes of different diameters as proposed in document FR-A-2 588 919.
  • the injector 6 has a plurality of fuel injection holes 10 distributed over its periphery in order to inject fuel into the swirling air delivered by the spin 7. These injection holes 10 do not all have the same diameter , in order to better homogenize the spray mixture delivered into the combustion chamber 3 downstream of the bowls 1.
  • the injection holes 10 are distributed in first sectors comprising injection holes 10 of small diameter and in second sectors with large diameter injection holes 10.
  • FIGS. 4 and 5 show a combustion chamber 3 which comprises a single injection head equipped with bowls 1 of elliptical shape regularly distributed circumferentially in the bottom of the chamber 2.
  • the bowls 1 described above can advantageously equip a combustion chamber with two heads which has a take-off head 13 and an idle head 14 radially spaced around the axis of the combustion chamber, as can be seen in the Figures 6 and 7.
  • the spacing of the bowls 1 of the idle head 14 is greater than the spacing of the bowls 1 of the take-off head and the total number of bowls 1 of elliptical shape equipping the combustion chamber 3 is less than the number of bowls of circular section necessary to equip a combustion chamber with two heads of the prior art.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Description

La présente invention concerne un système d'injection aérodynamique d'une chambre de combustion annulaire, comportant au moins une tête d'injection présentant une pluralité de dispositifs d'injection d'air et de carburant régulièrement répartis circonférentiellement dans le fond de chambre.The present invention relates to an aerodynamic injection system of an annular combustion chamber, comprising at least one injection head having a plurality of air and fuel injection devices regularly distributed circumferentially in the chamber bottom.

US 3 834 159, GB 2 028 488 et US 4 045 956 decrivent des chambres de combustion dans lesquelles on alterne des injecteurs de carburant avec des arrivées d'air. Cette alternance d'injecteurs et d'ouvertures d'admission d'air conduisent à des richesses locales hétérogènes circonférentiellement dans la zone primaire de la chambre de combustion.US 3,834,159, GB 2,028,488 and US 4,045,956 describe combustion chambers in which fuel injectors are alternated with air inlets. This alternation of injectors and air intake openings lead to heterogeneous local wealth circumferentially in the primary zone of the combustion chamber.

FR-A-2 357 738 qui représente l'état de la technique le plus proche de la présente invention concerne un système d'injection dans lequel chacun des dispositifs d'injection de carburant et d'air comprend un injecteur de carburant, une vrille de turbulence externe pour le passage de l'air de pulvérisation du carburant et un corps en forme de bol comportant un voile aval évasé dans le sens de l'écoulement et pourvu d'une rangée de trous de bols pour l'injection d'air dans le cône de carburant pulvérisé.FR-A-2 357 738 which represents the closest state of the art to the present invention relates to an injection system in which each of the fuel and air injection devices comprises a fuel injector, a spin external turbulence for the passage of the fuel atomizing air and a bowl-shaped body comprising a downstream web flared in the direction of flow and provided with a row of bowl holes for the injection of air in the sprayed fuel cone.

Ces bols sont disposés à une certaine distance les uns des autres, et comme ils sont de section circulaire, le nombre de dispositifs d'injection équipant la chambre de combustion est élevé.These bowls are arranged at a certain distance from each other, and as they are of circular section, the number of injection devices equipping the combustion chamber is high.

Le but de la présente invention est d'apporter une modification aux bols afin de diminuer le nombre d'injecteurs sans nuire au bon fonctionnement de la chambre d'injection.The object of the present invention is to make a modification to the bowls in order to reduce the number of injectors without impairing the proper functioning of the injection chamber.

Ce but est atteint par le fait que le voile présente une section transversale de forme sensiblement elliptique, l'axe de plus petite dimension étant disposé dans un plan axial de la chambre de combustion, et en ce que l'injecteur comporte une pluralité de trous d'injection de carburant de diamètres différents.This object is achieved by the fact that the web has a cross section of substantially elliptical shape, the axis of smaller dimension being disposed in an axial plane of the combustion chamber, and in that the injector has a plurality of holes fuel injection of different diameters.

Cette disposition permet d'obtenir un front de flamme plus aplati, en jouant sur les différents diamètres des trous d'injection de carburant.This arrangement makes it possible to obtain a more flat flame front, by playing on the different diameters of the fuel injection holes.

La chambre peut comporter une seule tête d'injection ou deux têtes d'injection espacées radialement. L'équipement d'une chambre à deux têtes avec des bols de forme elliptique selon l'invention permet d'augmenter la perméabilité du fond de chambre et donc la richesse moyenne près des injecteurs.The chamber may have a single injection head or two injection heads spaced radially. Equipping a two-headed chamber with elliptical-shaped bowls according to the invention makes it possible to increase the permeability of the chamber bottom and therefore the average richness near the injectors.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante, faite à titre d'exemple et en référence aux dessins annexés dans lesquels:

  • la figure 1 est une vue en perspective d'une partie de chambre de combustion comportant une tête d'injection équipée de bols de l'art antérieur,
  • la figure 2 représente le fond de chambre équipé de bols de l'art antérieur, selon une vue prise de l'intérieur de la chambre de combustion et dans la direction opposée à l'écoulement des gaz,
  • la figure 3 est une coupe axiale d'un bol,
  • la figure 4 est une vue en perspective d'une partie de chambre de combustion comportant une tête d'injection équipée de bols selon l'invention,
  • la figure 5 est une vue du fond de chambre prise depuis l'intérieur de la chambre de combustion représentée sur la figure 4,
  • la figure 6 est une coupe axiale d'une chambre de combustion à deux têtes équipée de bols selon l'invention, et
  • la figure 7 est une vue du fond de chambre prise depuis l'intérieur de la chambre de combustion de la figure 6.
Other advantages and characteristics of the invention will emerge on reading the following description, given by way of example and with reference to the appended drawings in which:
  • FIG. 1 is a perspective view of a part of the combustion chamber comprising an injection head equipped with bowls of the prior art,
  • FIG. 2 represents the bottom of the chamber equipped with bowls of the prior art, according to a view taken from inside the combustion chamber and in the direction opposite to the flow of gases,
  • FIG. 3 is an axial section of a bowl,
  • FIG. 4 is a perspective view of a part of the combustion chamber comprising an injection head equipped with bowls according to the invention,
  • FIG. 5 is a view of the chamber bottom taken from inside the combustion chamber shown in FIG. 4,
  • FIG. 6 is an axial section of a combustion chamber with two heads fitted with bowls according to the invention, and
  • FIG. 7 is a view of the bottom of the chamber taken from the interior of the combustion chamber of FIG. 6.

Les figures 1 et 2 montrent schématiquement la disposition des bols 1 de l'art antérieur dans le fond de chambre 2 d'une chambre de combustion 3 annulaire d'une turbomachine comportant une seule tête d'injection. La chambre de combustion 3 est délimitée par une virole intérieure 4 et une virole extérieure 5 reliée par le fond de chambre 2. Les bols 1 de forme tronconique et de section transversale circulaire sont disposés en amont du fond de chambre 2 et ils entourent chacun un injecteur de carburant 6 avec interposition d'une vrille de turbulence 7. Les bols 1 comportent un voile 8 évasé vers l'aval dans le sens de l'écoulement des gaz et présentant une rangée de trous de bols 9 pour l'injection d'air dans le cône de carburant pulvérisé. Le carburant est délivré par des orifices 10 ménagés dans l'injecteur 6 et est pulvérisé par l'air tourbillonnant pénétrant par la vrille de turbulence 7.Figures 1 and 2 schematically show the arrangement of bowls 1 of the prior art in the chamber bottom 2 of an annular combustion chamber 3 of a turbomachine having a single injection head. The combustion chamber 3 is delimited by an interior ferrule 4 and an exterior ferrule 5 connected by the chamber bottom 2. The bowls 1 of frustoconical shape and of circular cross section are arranged upstream of the chamber bottom 2 and they each surround a fuel injector 6 with interposition of a turbulence spin 7. The bowls 1 comprise a web 8 flared downstream in the direction of gas flow and having a row of bow holes 9 for the injection of air in the sprayed fuel cone. The fuel is delivered through orifices 10 formed in the injector 6 and is sprayed by the swirling air penetrating through the swirling spin 7.

Les bols consécutifs 1a et 1b sont situés à une distance X les uns des autres et la distance Y séparant deux injecteurs voisins 6a et 6b est égale à la distance X augmentée du diamètre d'un bol 1.The consecutive bowls 1a and 1b are located at a distance X from each other and the distance Y separating two neighboring injectors 6a and 6b is equal to the distance X increased by the diameter of a bowl 1.

Selon la présente invention, les bols 1 ont un voile 8 qui présente une section transversale de forme elliptique, l'axe de plus petite dimension 11 étant disposé dans un plan axial de la chambre de combustion 3. L'orifice 12 permettant la fixation du bol 1 de l'invention dans le fond de chambre 2 a également une section elliptique. Les trous de bols 9 ne sont plus équidistants de l'injecteur 6. Grâce à cette disposition, la distance Y' séparant deux injecteurs consécutifs 6a et 6b d'une tête d'injection est augmentée par rapport à la distance Y de l'art antérieur, si l'on conserve la distance X séparant deux bols consécutifs 1a et 1b et les dimensions radiales de la chambre de combustion. Il faut donc un nombre moindre d'injecteurs pour équiper la chambre de combustion 3.According to the present invention, the bowls 1 have a veil 8 which has a cross section of elliptical shape, the axis of smaller dimension 11 being disposed in an axial plane of the combustion chamber 3. The orifice 12 allowing the fixing of the bowl 1 of the invention in the bottom of chamber 2 also has a elliptical section. The bowl holes 9 are no longer equidistant from the injector 6. With this arrangement, the distance Y 'separating two consecutive injectors 6a and 6b from an injection head is increased relative to the distance Y of the art previous, if we keep the distance X separating two consecutive bowls 1a and 1b and the radial dimensions of the combustion chamber. A smaller number of injectors is therefore required to equip the combustion chamber 3.

Les trous de bols 9 peuvent être équidistants les uns des autres et avoir le même diamètre. Mais on peut également les disposer à des intervalles variables afin de répartir l'air introduit selon les nécessités. De même, on peut les répartir en secteurs comportant des trous de bols de diamètres différents comme cela est proposé dans le document FR-A-2 588 919.The bowl holes 9 can be equidistant from each other and have the same diameter. However, they can also be placed at variable intervals in order to distribute the air introduced as necessary. Likewise, they can be divided into sectors comprising bowl holes of different diameters as proposed in document FR-A-2 588 919.

L'injecteur 6 comporte une pluralité de trous 10 d'injection de carburant répartis sur sa périphérie afin d'injecter du carburant dans l'air tourbillonnant délivré par la vrille 7. Ces trous d'injection 10 n'ont pas tous le même diamètre, afin de mieux homogénéiser le mélange pulvérisé délivré dans la chambre de combustion 3 en aval des bols 1. De préférence, les trous d'injection 10 sont répartis en des premiers secteurs comportant des trous d'injection 10 de faible diamètre et en des deuxièmes secteurs comportant des trous d'injection 10 de gros diamètre.The injector 6 has a plurality of fuel injection holes 10 distributed over its periphery in order to inject fuel into the swirling air delivered by the spin 7. These injection holes 10 do not all have the same diameter , in order to better homogenize the spray mixture delivered into the combustion chamber 3 downstream of the bowls 1. Preferably, the injection holes 10 are distributed in first sectors comprising injection holes 10 of small diameter and in second sectors with large diameter injection holes 10.

Les figures 4 et 5 montrent une chambre de combustion 3 qui comporte une seule tête d'injection équipée de bols 1 de forme elliptique régulièrement répartis circonférentiellement dans le fond de chambre 2.FIGS. 4 and 5 show a combustion chamber 3 which comprises a single injection head equipped with bowls 1 of elliptical shape regularly distributed circumferentially in the bottom of the chamber 2.

Les bols 1 décrits ci-dessus peuvent avantageusement équiper une chambre de combustion à deux têtes qui présente une tête de décollage 13 et une tête de ralenti 14 radialement espacées autour de l'axe de la chambre de combustion, comme on peut le voir sur les figures 6 et 7. L'espacement des bols 1 de la tête de ralenti 14 est supérieur à l'espacement des bols 1 de la tête de décollage et le nombre total de bols 1 de forme elliptique équipant la chambre de combustion 3 est inférieur au nombre de bols de section circulaire nécessaires pour équiper une chambre de combustion à deux têtes de l'art antérieur.The bowls 1 described above can advantageously equip a combustion chamber with two heads which has a take-off head 13 and an idle head 14 radially spaced around the axis of the combustion chamber, as can be seen in the Figures 6 and 7. The spacing of the bowls 1 of the idle head 14 is greater than the spacing of the bowls 1 of the take-off head and the total number of bowls 1 of elliptical shape equipping the combustion chamber 3 is less than the number of bowls of circular section necessary to equip a combustion chamber with two heads of the prior art.

Claims (3)

  1. An aerodynamic injection system of an annular combustion chamber (3) comprising at least one injection head having a plurality of air and fuel injection devices evenly distributed around the periphery of the chamber end (2), each such injection device comprising a fuel injector (6), an external swirler (7) for the passage of the fuel-atomizing air and a bowl-shaped body (1) having a downstream skirt (8) flared in the direction of the flow and formed with a row of apertures (9) for injecting air into the cone of atomised fuel, characterised in that the skirt (8) is of substantially elliptical cross-section, the minor axis being disposed in an axial plane of the combustion chamber (3), and the injector (6) is formed with a plurality of fuel injection apertures (10) of various diameters.
  2. A system according to claim 1, characterised in that the plurality of injection apertures are arranged in first sectors comprising small-diameter injection apertures and second sectors comprising large-diameter injection apertures.
  3. A system according to claim 1 or claim 2, characterised in that the combustion chamber (3) comprises two radially spaced-apart injection heads (13, 14).
EP93402788A 1992-11-18 1993-11-17 Aerodynamic injection system for a combustion chamber Expired - Lifetime EP0598662B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9213832 1992-11-18
FR9213832A FR2698157B1 (en) 1992-11-18 1992-11-18 Aerodynamic combustion chamber injection system.

Publications (2)

Publication Number Publication Date
EP0598662A1 EP0598662A1 (en) 1994-05-25
EP0598662B1 true EP0598662B1 (en) 1996-04-03

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EP93402788A Expired - Lifetime EP0598662B1 (en) 1992-11-18 1993-11-17 Aerodynamic injection system for a combustion chamber

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US (1) US5351475A (en)
EP (1) EP0598662B1 (en)
DE (1) DE69302078T2 (en)
FR (1) FR2698157B1 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2727193B1 (en) * 1994-11-23 1996-12-20 Snecma TWO-HEAD COMBUSTION CHAMBER OPERATING AT FULL GAS SLOW MOTION
US5619855A (en) * 1995-06-07 1997-04-15 General Electric Company High inlet mach combustor for gas turbine engine
FR2751054B1 (en) * 1996-07-11 1998-09-18 Snecma ANNULAR TYPE FUEL INJECTION ANTI-NOX COMBUSTION CHAMBER
GB2319078B (en) * 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
DE19720402A1 (en) * 1997-05-15 1998-11-19 Bmw Rolls Royce Gmbh Axially stepped annular combustion chamber for gas turbine
US6038861A (en) * 1998-06-10 2000-03-21 Siemens Westinghouse Power Corporation Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
US6119459A (en) * 1998-08-18 2000-09-19 Alliedsignal Inc. Elliptical axial combustor swirler
DE19914666B4 (en) * 1999-03-31 2009-08-20 Alstom Burner for a heat generator
DE10340826A1 (en) * 2003-09-04 2005-03-31 Rolls-Royce Deutschland Ltd & Co Kg Homogeneous mixture formation by twisted injection of the fuel
DE10348604A1 (en) * 2003-10-20 2005-07-28 Rolls-Royce Deutschland Ltd & Co Kg Fuel injector with filmy fuel placement
US7509809B2 (en) * 2005-06-10 2009-03-31 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
US7836699B2 (en) * 2005-12-20 2010-11-23 United Technologies Corporation Combustor nozzle
JP2008159524A (en) * 2006-12-26 2008-07-10 Shinko Electric Ind Co Ltd Solid oxide fuel cell power generator
US8146365B2 (en) * 2007-06-14 2012-04-03 Pratt & Whitney Canada Corp. Fuel nozzle providing shaped fuel spray
DE102007043626A1 (en) * 2007-09-13 2009-03-19 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity
US8402763B2 (en) * 2009-10-26 2013-03-26 General Electric Company Combustor headend guide vanes to reduce flow maldistribution into multi-nozzle arrangement
DE102012002465A1 (en) * 2012-02-08 2013-08-08 Rolls-Royce Deutschland Ltd & Co Kg Gas turbine combustor with unsymmetrical fuel nozzles
US9145778B2 (en) 2012-04-03 2015-09-29 General Electric Company Combustor with non-circular head end
GB201222304D0 (en) * 2012-12-12 2013-01-23 Rolls Royce Plc A fuel injector and a gas turbine engine combustion chamber
US9376985B2 (en) * 2012-12-17 2016-06-28 United Technologies Corporation Ovate swirler assembly for combustors
US9404656B2 (en) * 2012-12-17 2016-08-02 United Technologies Corporation Oblong swirler assembly for combustors
GB2548585B (en) * 2016-03-22 2020-05-27 Rolls Royce Plc A combustion chamber assembly
US20180058696A1 (en) * 2016-08-23 2018-03-01 General Electric Company Fuel-air mixer assembly for use in a combustor of a turbine engine
US11149952B2 (en) * 2016-12-07 2021-10-19 Raytheon Technologies Corporation Main mixer in an axial staged combustor for a gas turbine engine
JP7446077B2 (en) * 2019-10-04 2024-03-08 三菱重工業株式会社 Gas turbine combustor, gas turbine and oil fuel combustion method
FR3142533A1 (en) * 2022-11-28 2024-05-31 Safran Aircraft Engines Combustion chamber for turbomachine

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3521824A (en) * 1968-10-11 1970-07-28 Delavan Manufacturing Co Air-liquid flat spray nozzle
US3834159A (en) * 1973-08-03 1974-09-10 Gen Electric Combustion apparatus
US4045956A (en) * 1974-12-18 1977-09-06 United Technologies Corporation Low emission combustion chamber
FR2357738A1 (en) * 1976-07-07 1978-02-03 Snecma Combustion chamber for gas turbine engine - uses air streams ensuring stoichiometric mixture for all turbine speeds
US4162611A (en) * 1976-07-07 1979-07-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Combustion chamber for turbo engines
GB2028488B (en) * 1978-08-19 1983-02-02 Rolls Royce Gas turbine
US4218020A (en) * 1979-02-23 1980-08-19 General Motors Corporation Elliptical airblast nozzle
FR2588919B1 (en) * 1985-10-18 1987-12-04 Snecma SECTORIZED BOWL INJECTION DEVICE
CH672541A5 (en) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
DE3837635A1 (en) * 1988-11-05 1990-05-10 Proizv Ob Nevskij Z Im V I Method for burning fuel in a combustion chamber

Also Published As

Publication number Publication date
FR2698157A1 (en) 1994-05-20
DE69302078T2 (en) 1996-09-12
EP0598662A1 (en) 1994-05-25
DE69302078D1 (en) 1996-05-09
FR2698157B1 (en) 1994-12-16
US5351475A (en) 1994-10-04

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