EP2761226B1 - Chambre annulaire de combustion d'une turbomachine - Google Patents

Chambre annulaire de combustion d'une turbomachine Download PDF

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Publication number
EP2761226B1
EP2761226B1 EP12773067.9A EP12773067A EP2761226B1 EP 2761226 B1 EP2761226 B1 EP 2761226B1 EP 12773067 A EP12773067 A EP 12773067A EP 2761226 B1 EP2761226 B1 EP 2761226B1
Authority
EP
European Patent Office
Prior art keywords
orifices
bowl
fuel
air
spark plug
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
EP12773067.9A
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German (de)
English (en)
French (fr)
Other versions
EP2761226A2 (fr
Inventor
Denis Jean Maurice Sandelis
Christophe Pieussergues
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 Services SA
SNECMA SAS
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Publication date
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Publication of EP2761226A2 publication Critical patent/EP2761226A2/fr
Application granted granted Critical
Publication of EP2761226B1 publication Critical patent/EP2761226B1/fr
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/002—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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • 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 an annular combustion chamber of a turbomachine such as a turboprop or an airplane turbojet engine.
  • annular combustion chamber of a turbomachine receives an upstream air flow of a high pressure compressor and delivers downstream a flow of hot gases driving the rotors of high pressure and low pressure turbines.
  • the annular combustion chamber comprises two coaxial walls of revolution which extend one inside the other and which are interconnected at their upstream ends by an annular wall of the chamber bottom, this chamber bottom comprising mounting openings for fuel injection systems between the inner and outer annular walls.
  • Each injection system comprises means for supporting the head of a fuel injector and at least one auger which is arranged downstream of the injector head, coaxially with it, and which delivers a flow of air rotating downstream of the fuel injection to form a mixture of air and fuel to be burned in the combustion chamber.
  • the tendrils of the injection systems are fed with air from an annular diffuser mounted at the outlet of the high-pressure compressor arranged upstream of the combustion chamber.
  • Each auger opens downstream inside a mixing bowl comprising a substantially frustoconical downstream wall flared downstream and having an annular row of air injection orifices regularly distributed around the axis of the bowl.
  • the outer annular wall of the combustion chamber comprises an annular row of primary dilution orifices and at least one spark plug opening inside the combustion chamber and arranged downstream of the primary dilution orifices.
  • the air leaving the high-pressure compressor circulates inside each of the injection systems.
  • the air / fuel mixture is ejected from each injection system forming a sheet of air and substantially frustoconical fuel widening downstream.
  • the angle of opening of the ply is a function of the opening angle of the frustoconical wall of the mixing bowl and the dimensions of the air injection orifices formed in this frustoconical wall.
  • the primary dilution orifices make it possible to stabilize the combustion flame in the chamber bottom and avoid, by dilution of the air / fuel mixture, that the combustion flame does not pick up and enters the high pressure turbine and damages components such as especially the fixed vanes by formation of hot spots.
  • the injection systems are configured so that for each injection system, the air / fuel mixture web crosses or intersects circumferentially, upstream of the dilution orifices, the fuel plies of the two fuel injection systems. adjacent injection. In this way, it ensures a circumferential continuity of the air / fuel mixture between the injection systems before dilution, which ensures that the flame initiated by the spark plug (s) will spread over the entire circumference of the chamber. combustion.
  • the circumferential pitch between the adjacent injection systems is greater. It follows that the fuel plies of the adjacent injection systems are no longer circumferentially intercepted upstream of the primary dilution orifices, which leads to difficulties in circumferentially propagate the flame between the injectors and reduces the performance of the combustion chamber.
  • the document FR2901349 relates to a combustion chamber comprising a frustoconical bowl having orifices for producing two annular sheets of mixed air and fuel.
  • the invention aims in particular to provide a simple, economical and effective solution to the problems mentioned above, to avoid the disadvantages of the known technique.
  • annular combustion chamber comprising two coaxial revolution walls, respectively internal and external, connected to each other at their upstream ends by an annular chamber bottom wall having system mounting openings.
  • injection unit each comprising at least one swirler for producing a flow of air rotating downstream of a fuel injector and a substantially frustoconical walled bowl downstream of the swirler and formed with an annular row of injection orifices of air for producing a substantially frustoconical and rotating web of air and fuel mixture
  • the outer wall of revolution comprising an annular row of primary dilution orifices, characterized in that the orifices of the bowls are distributed and dimensioned by in such a way that at least some air / fuel mixture plies have at least one local expansion circumferentially intercepting a web Fuel adjacent to the primary dilution ports.
  • the invention makes it possible to maintain the same angular opening of the fuel plies by modifying certain bowls so as to form a local expansion of their fuel ply, this widening circumferentially intercepting the mixing ply. air / fuel from an injection system adjacent upstream of the primary dilution ports.
  • the orifices of the bowls being regularly distributed around the axes of the bowls, orifices of certain bowls have a smaller diameter than the other orifices of said bowls, the orifices with reduced diameter being formed on a angular sector of predetermined size and angular position so as to form a local expansion of the fuel ply.
  • the orifices of the abovementioned angular sector of each aforementioned bowl have a diameter at least 40% smaller than the diameter of the other orifices of the bowl.
  • At least some of the bowls are devoid of orifices on an angular sector of predetermined size and angular position so as to form the local expansion of the fuel ply.
  • some of the bowls comprise two angular sectors that are diametrically opposed, one to the other and including orifices with reduced diameter and / or without orifices.
  • the fuel ply formed at the outlet of each of these bowls comprises two diametrically opposite enlargements with respect to the axis of the bowl, which intercept the fuel plies generated by the two injection systems located on each side of the bowl. other of the bowl.
  • the combustion chamber comprises at least one spark plug mounted in an orifice of the outer wall of revolution and the orifices of the injection system bowl located closest to the spark plug are distributed and dimensioned so that the sheet air / fuel mixture of said injection system has another local expansion intercepting the axis of the spark plug between the radially inner end of the spark plug and a point of the outer periphery of said bowl.
  • This additional widening of the fuel ply makes it possible to locally project the fuel ply closer to the inner end of the spark plug, which further facilitates the ignition of the air / fuel mixture and the propagation of the flame.
  • the bowl located closer to the candle may comprise smaller diameter orifices than the other orifices of said bowl, these reduced diameter orifices being formed on an angular sector of predetermined size and angular position so as to form the intercepting widening the axis of the candle.
  • the bowl located closest to the candle may also be devoid of orifices on an angular sector of predetermined size and position so as to form the widening intercepting the axis of the candle.
  • the aforementioned angular sector or sectors extend over approximately 20 ° to 50 °.
  • the invention also relates to a turbomachine, such as a turboprop or an airplane turbojet, comprising a combustion chamber as described above.
  • FIG 1 represents an annular combustion chamber 10 of a turbomachine such as a turbojet engine or an airplane turboprop, arranged at the outlet of a centrifugal diffuser 12 mounted at the outlet of a high-pressure compressor (not shown).
  • the combustion chamber 10 is followed by a high pressure turbine 14 of which only the inlet distributor 16 is shown.
  • the combustion chamber 10 comprises two coaxial inner and outer frustoconical walls 18, 18, arranged one inside the other and with a reduced section downstream. Such a combustion chamber is said to be convergent.
  • the inner annular walls 18 and outer 20 are connected at their upstream ends to an annular bottom wall of chamber 22 and attached downstream by inner annular flanges 24 and outer 26.
  • the outer annular flange 26 bears radially externally on a housing external 28 and in axial support on a radial flange 30 for fixing the distributor 16 of the high-pressure turbine to the outer casing 28.
  • the inner annular flange 24 of the combustion chamber bears radially and axially on an inner annular piece 32 for fixing from the distributor 16 to an inner annular wall 34.
  • the chamber bottom 22 has openings for mounting systems for injecting an air-fuel mixture into the chamber, the air coming from the centrifugal diffuser 12 and the fuel being supplied by injectors 36.
  • the injectors 36 are fixed at their radially outer ends to the outer casing 28 and are regularly distributed over a circumference around the axis of revolution 38 of the chamber.
  • Each injector 36 comprises at its radially inner end a fuel injection head 40 which is aligned with the axis of a corresponding opening of the chamber bottom 22.
  • the mixture of air and fuel injected into the chamber 10 is ignited by means of at least one spark plug 42 which extends radially outside the chamber 10.
  • the inner end of the spark plug 42 extends into an orifice of the outer wall 20 of the chamber, and its radially outer end is fixed by means appropriate to the outer housing 28 and connected to power supply means (not shown) located outside the housing 28.
  • the outer annular wall 20 of the combustion chamber comprises an annular row of primary orifices 44 for dilution of the air / fuel mixture arranged upstream of the spark plug 42.
  • Each injection system as we see best in figure 2 comprises two upstream turbulence swirlers 46 and coaxial downstream swirlers 48 connected upstream to means for centering and guiding the head of the injector, and downstream to a mixing bowl 50 which is mounted axially in the opening of the wall of chamber background 22.
  • the tendrils 46, 48 each comprise a plurality of vanes extending radially around the axis of the auger and regularly distributed around this axis to deliver a flow of air rotating downstream of the injection head.
  • the tendrils 46, 48 are separated from one another by a radial wall 52 connected at its radially inner end to a venturi 54 which extends axially downstream inside the downstream tendrill and which separates the air flows from the upstream tendrils 46 and downstream 48.
  • a first annular airflow vein is formed inside the venturi 54 and a second annular airflow vein is formed outside the venturi 54 venturi 54.
  • the mixing bowl 50 comprises a substantially frustoconical wall 56 flared downstream and connected at its downstream end to a cylindrical flange 58 extending upstream and axially mounted in the opening of the chamber bottom wall 22 with a Annular deflector 60.
  • the upstream end of the frustoconical wall of the bowl is fixed by an intermediate annular piece 62 to the downstream auger.
  • the frustoconical wall 56 of the bowl comprises an annular row of air injection orifices 64 regularly distributed around the axis 70 of the bowl.
  • the air passing through these orifices and the air flowing in the veins inside and outside the venturi 54 mix with the pulverized fuel by the injector to form a rotating web of air and fuel mixture having a substantially frustoconical shape 66 widening downstream.
  • the axes 68 of each of the air injection orifices 64 of the bowl are inclined with respect to the axis 70 of the bowl and converge towards it in the downstream direction.
  • a second annular row of orifices 72 is formed at the junction between the upstream end of the cylindrical rim 58 and the frustoconical wall 56. These second orifices 72 provide ventilation of the downstream face of the deflector 60 and limit the heating of the bottom of the room 22.
  • the upstream swirlers 46 and downstream 48 of the injection system induce a rotation of the flow of air and sprayed fuel and the air injection orifices 64 of the frustoconical wall 56 of the bowl 50 perform a shear of the mixture. air / fuel.
  • the larger the diameter of the air injection orifices 64 of the bowl 50 the greater the flow of air passing through these orifices is important, which decreases the opening angle 74 of the frustoconical air mixture sheet. /fuel.
  • the configuration and the number of the injection systems are determined so that the fuel plies of the adjacent injection systems are intercepted. or intersect circumferentially upstream of the primary dilution ports 44 to form a circumferentially continuous air / fuel mixture cloud.
  • the figure 3 represents two adjacent injection systems S1 and S2 and the dashed lines represent the frustoconical fuel plies pulverized by the injection systems S1 and S2, respectively.
  • the figure 4 represents a section of the fuel plies N1 and N2 of the injection systems S1 and S2, respectively, in a transverse plane 76 passing through the primary dilution orifices.
  • increasing the opening angle of the fuel plies is not desirable because it would lead to spraying a larger amount of fuel towards the inner annular walls 18 and outer 20, which would cause the forming hot spots on the inner annular walls 18 and outer 20 of the combustion chamber.
  • the increase in the number of injection systems is also not desirable because it would lead to an increase in the turbomachine and an increase in fuel consumption.
  • the invention provides a solution to this problem as well as to those mentioned above by realizing a distribution and dimensioning of the bowls of injection systems so as to locally expand in the circumferential direction the fuel plies so that they intercept in upstream of the primary dilution ports the fuel layers produced by the adjacent injection systems.
  • the mixing bowl 78 seen from downstream comprises a plurality of orifices 80 regularly distributed around the axis 82 of the bowl.
  • the bowl 78 comprises an angular sector 84 whose orifices 86 have a diameter smaller than the diameter of the other orifices 80 of the bowl 78.
  • each particle of air and fuel of the air / fuel layer follows a substantially helical frustoconical trajectory.
  • the local enlargement takes a form corresponding to these frustoconical helical trajectories.
  • the sector 84 of the bowl 78 must be offset angularly from an angle ⁇ in the opposite direction of rotation of the air / fuel mixture, that is to say in the direction of clockwise, relative to a plane 87 containing the axis 82 of the bowl 78 and perpendicular to a radial plane 89 containing the axis 82 of the bowl 78 and the axis of the combustion chamber.
  • planes 87 and 89 are represented by lines and are perpendicular to the plane of the sheet.
  • the angle ⁇ is measured from the middle of the sector of the bowl 78 having orifices 86 of reduced diameter. This angle ⁇ determines the position (arrow A) of the widening of the fuel ply which will circumferentially circumferentially intercept the fuel ply of an adjacent injection system.
  • the figure 6 represents two adjacent injection systems of which one S1 is identical to that of the prior art described with reference to FIG. figure 3 and the other S3 corresponds to the injection system described with reference to the figure 5 .
  • the dotted lines represent the frustoconical shapes of the fuel plies N1, N3 produced by each of the injection systems S1 and S3.
  • the widening 88 of the fuel layer N3 of the injection system S3 circumferentially intersects the fuel ply N1 of the injection system S1 upstream of the primary air injection orifices.
  • the figure 7 represents a section of the fuel plies N1 and N3 of the injection systems S1 and S3, respectively, in a transverse plane 76 passing through the primary dilution orifices. In this figure, it is observed that the local expansion 88 of the air / fuel mixture web N3 of the injection system S3 circumferentially intersects the web N1 of the injection system S1.
  • the angular extent of the sector 84 of the bowl 78 determines the angular extent of the widening around the axis 82 of the bowl 78.
  • the sector of the bowl comprising reduced diameter orifices is replaced by a sector 90 devoid of air injection orifices as shown in FIG. figure 8 .
  • This sector 90 without orifices is also offset by an angle ⁇ with respect to the plane 87.
  • Such a bowl 92 makes it possible to obtain a sheet of fuel of substantially the same shape as that obtained with a bowl 78 comprising a sector 84 with orifices 86. with reduced diameter. Only the width of the widening of the fuel ply is greater because no air flow circulates through the sector 90 of the bowl 92.
  • the sector 84 of the bowl 78 comprising orifices of reduced diameter and the sector 90 of the bowl 92 without openings extend angularly about 50 ° and the angle ⁇ is of the order of 120 °.
  • the mixer bowl 94 comprises two angular sectors 96, 98 diametrically opposite one another and devoid of air injection orifices.
  • Arrows B and C illustrate the path traveled by the air and fuel particles passing near the first 96 and second 98 sectors of the bowl 94.
  • the figure 10 represents an injection system S4 comprising a bowl 94 having two diametrically opposite sectors mentioned above.
  • the first 96 and second 98 sectors of the bowl 94 allow the formation of a first enlargement 100 and a second enlargement 102 of the fuel layer N4 ( Figures 10 and 11 ).
  • These first and second enlargements 100, 102 are diametrically opposite each other and are intended to circumferentially intercept the fuel plies. produced by the injection systems located on either side of the bowl 94.
  • each sector 98, 96 extends angularly about 20 to 30 ° and is angularly offset by an angle of about 100 ° in the opposite direction of rotation of the air / fuel mixture, that is to say in the clockwise, with respect to a plane 95 containing the axis 97 of the bowl 94 and perpendicular to a radial plane 99 containing the axis 97 of the bowl 94 and the axis of the combustion chamber.
  • planes 95 and 99 are represented by lines and are perpendicular to the plane of the sheet.
  • the two diametrically opposed angular sectors may comprise reduced diameter orifices. It is also possible that one of the sectors has no openings and the other sector has small diameter orifices.
  • the mixing bowl 104 located closest to the spark plug 42 comprises two angular sectors 106, 108 without orifices, one of which allows the formation of a first enlargement for circumferentially intercepting an adjacent fuel layer and the other 108 allows the formation of a second enlargement for intercepting the axis 110 of the spark plug 42 between the inner end of the spark plug and a point of the outer periphery of the bowl 104.
  • the first and second enlargements are substantially localized on the fuel ply at 90 ° from each other.
  • Arrows D and E illustrate the paths traveled by the particles of air and fuel passing in the vicinity of the first and second sectors of the bowl 104.
  • the first angular sector 106 of the bowl 104 extends angularly about 50 ° and the second angular sector 108 for effecting a fuel projection closer to the inner end of the spark plug 42 extends angularly about 40 °.
  • the injection system located closer to the candle could still understand two diametrically opposed sectors as described with reference to the figure 10 and intended to achieve circumferential propagation of the combustion flame and a third sector devoid of orifices or reduced diameter orifices for the projection of fuel to the candle.
  • the positioning and the angular extent of the sector comprising orifices with reduced diameter or without orifices is determined by three-dimensional simulation.
  • Such a simulation takes into account many parameters such as the shape and inclination of the auger blades, the direction of rotation of the tendrils, the air flow of the high-pressure compressor and the fuel flow of the injectors, etc.
  • the mixing bowl according to the invention makes it possible to have a circumferential continuity of the air / fuel mixture between two injectors before the introduction of air through the primary dilution orifices, which ensures a good circumferential propagation of the combustion flame when the number of injection systems is reduced and / or when the circumferential pitch between these systems is greater.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Nozzles (AREA)
EP12773067.9A 2011-09-27 2012-09-20 Chambre annulaire de combustion d'une turbomachine Active EP2761226B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1158655A FR2980554B1 (fr) 2011-09-27 2011-09-27 Chambre annulaire de combustion d'une turbomachine
PCT/FR2012/052098 WO2013045792A2 (fr) 2011-09-27 2012-09-20 Chambre annulaire de combustion d'une turbomachine

Publications (2)

Publication Number Publication Date
EP2761226A2 EP2761226A2 (fr) 2014-08-06
EP2761226B1 true EP2761226B1 (fr) 2015-11-18

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP12773067.9A Active EP2761226B1 (fr) 2011-09-27 2012-09-20 Chambre annulaire de combustion d'une turbomachine

Country Status (8)

Country Link
US (1) US9651260B2 (pt)
EP (1) EP2761226B1 (pt)
CN (1) CN103842728B (pt)
BR (1) BR112014002927B1 (pt)
CA (1) CA2848629C (pt)
FR (1) FR2980554B1 (pt)
RU (1) RU2606460C2 (pt)
WO (1) WO2013045792A2 (pt)

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EP2940389A1 (en) * 2014-05-02 2015-11-04 Siemens Aktiengesellschaft Combustor burner arrangement
CN104308320B (zh) * 2014-08-27 2016-08-24 北京动力机械研究所 喷油环的钎焊定位装置
CN105841193B (zh) * 2016-05-18 2018-07-20 葛明龙 两种航空航天涡扇发动机
CN106392504B (zh) * 2016-12-21 2019-01-18 中国南方航空工业(集团)有限公司 一种航空发动机涡流器加工方法
FR3061761B1 (fr) * 2017-01-10 2021-01-01 Safran Aircraft Engines Chambre de combustion pour turbomachine
FR3080437B1 (fr) * 2018-04-24 2020-04-17 Safran Aircraft Engines Systeme d'injection pour une chambre annulaire de combustion de turbomachine
CN111396927B (zh) * 2020-03-27 2021-06-08 中国科学院工程热物理研究所 二维阵列无传统旋流器的低污染燃烧装置
US20220325891A1 (en) * 2021-04-12 2022-10-13 General Electric Company Dilution horn pair for a gas turbine engine combustor
FR3142533A1 (fr) 2022-11-28 2024-05-31 Safran Aircraft Engines Chambre de combustion pour turbomachine

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FR2588919B1 (fr) * 1985-10-18 1987-12-04 Snecma Dispositif d'injection a bol sectorise
GB9023004D0 (en) * 1990-10-23 1990-12-05 Rolls Royce Plc A gas turbine engine combustion chamber and a method of operating a gas turbine engine combustion chamber
FR2753779B1 (fr) * 1996-09-26 1998-10-16 Systeme d'injection aerodynamique d'un melange air carburant
US6141967A (en) * 1998-01-09 2000-11-07 General Electric Company Air fuel mixer for gas turbine combustor
RU2215241C2 (ru) * 2002-01-23 2003-10-27 Открытое акционерное общество "Авиадвигатель" Камера сгорания газотурбинного двигателя
US6877491B2 (en) * 2002-07-31 2005-04-12 Honda Giken Kogyo Kabushiki Kaisha Air fuel injection engine
FR2856467B1 (fr) * 2003-06-18 2005-09-02 Snecma Moteurs Chambre de combustion annulaire de turbomachine
US7316117B2 (en) * 2005-02-04 2008-01-08 Siemens Power Generation, Inc. Can-annular turbine combustors comprising swirler assembly and base plate arrangements, and combinations
FR2881813B1 (fr) * 2005-02-09 2011-04-08 Snecma Moteurs Carenage de chambre de combustion de turbomachine
US8511097B2 (en) * 2005-03-18 2013-08-20 Kawasaki Jukogyo Kabushiki Kaisha Gas turbine combustor and ignition method of igniting fuel mixture in the same
FR2901349B1 (fr) * 2006-05-19 2008-09-05 Snecma Sa Chambre de combustion d'une turbomachine
FR2925146B1 (fr) * 2007-12-14 2009-12-25 Snecma Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine
US8091367B2 (en) * 2008-09-26 2012-01-10 Pratt & Whitney Canada Corp. Combustor with improved cooling holes arrangement
US8966877B2 (en) * 2010-01-29 2015-03-03 United Technologies Corporation Gas turbine combustor with variable airflow

Also Published As

Publication number Publication date
CN103842728A (zh) 2014-06-04
WO2013045792A3 (fr) 2013-12-19
CN103842728B (zh) 2016-01-20
BR112014002927A2 (pt) 2017-03-01
FR2980554A1 (fr) 2013-03-29
FR2980554B1 (fr) 2013-09-27
RU2014116962A (ru) 2015-11-10
EP2761226A2 (fr) 2014-08-06
CA2848629A1 (fr) 2013-04-04
WO2013045792A2 (fr) 2013-04-04
RU2606460C2 (ru) 2017-01-10
CA2848629C (fr) 2019-07-23
US9651260B2 (en) 2017-05-16
BR112014002927B1 (pt) 2020-12-29
US20150040569A1 (en) 2015-02-12

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