EP0911585A1 - Accroche-flamme carburé et refroidi - Google Patents
Accroche-flamme carburé et refroidi Download PDFInfo
- Publication number
- EP0911585A1 EP0911585A1 EP98402599A EP98402599A EP0911585A1 EP 0911585 A1 EP0911585 A1 EP 0911585A1 EP 98402599 A EP98402599 A EP 98402599A EP 98402599 A EP98402599 A EP 98402599A EP 0911585 A1 EP0911585 A1 EP 0911585A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- passage
- flame
- downstream
- radial
- 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
Links
Images
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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
- F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
- F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
Definitions
- the ventilation tube described in this document has a section circular, is located in the vicinity of the dihedral edge and has holes to cool the dihedral wings.
- An anti-radiation screen, of semicircular section is arranged downstream of the fuel line, between the downstream edges of the dihedral, with provision for lateral axial slits for the flow of the air-fuel mixture in the afterburner.
- the fuel line injection ports are consisting of holes arranged in substantially radial planes and directed towards the internal walls of the dihedral. This flame catcher is said carbide.
- French patent application published under No. 2,696,502 shows radial flame catchers also made up of dihedrons and comprising a ventilation tube for cooling the dihedral.
- the flame holder does not include either a fuel line, or a radiation shield.
- the fuel is here injected upstream of the flame catchers via fuel lines arranged laterally on the link arms arranged alternately between the flame catchers.
- the injected fuel trickles down the walls external flame catchers.
- the cross-section of the ventilation tube is larger than that of the cylindrical tube of FR 2709342, which provides better cooling of the dihedral walls, but the fuel lines are exposed to the heat of the flue gases, which can lead to dysfunctions due to the risk of coking and "vapor-lock".
- the purpose of the present invention is to provide a device for post-combustion in which the flame catchers are of the fuel type and combine the qualities of the two previous definitions.
- the invention achieves its object by optimizing the aerodynamic cooling of each flame catcher.
- the ventilation tube is of section generally triangular and has two substantially lateral sides parallel to the outer plates and a downstream face which has a radial gutter in which the fuel line is housed, a plurality of additional orifices directed towards the fuel line being formed in the wall of said gutter in order to ensure the ventilation of the fuel line, the latter injecting the fuel downstream.
- the flow section of the ventilation is greater than the circular section of the ventilation tube described in FR 2 709 342.
- the cooling air flow is increased and the outer dihedral plates are impact cooled by air passing through the openings opening on the lateral faces of the tubes ventilation.
- the holes in the gutter blow air onto the fuel line in all operating ranges of the turbojet engine, which prevents the risks of coking and "vapor-lock", and promotes the thermal behavior of the fuel line in regime dry, i.e. in the event of the chamber not operating afterburner.
- the position of the holes, but also the shape of the tube ventilation of the flame catcher are best suited to ensure good ventilation of the dihedral walls and the fuel line.
- the fuel line is equipped with injectors aeromechanical.
- injectors aeromechanical This arrangement provides good quality spraying and controlling the size of the diffusion cone fuel droplets and this in order to avoid any risk of impact on the external dihedral plates of the heating system.
- Figure 1 shows in section a flame catch type fuel, similar to that described in the published patent application under the number FR 2 709 342, arranged radially in the gas stream hot flowing from upstream to downstream in the direction of arrow G, which includes a sheet bent in the form of a V-shaped dihedral to present two side plates 2, 3 connected by a rounded edge 4 arranged in upstream with respect to the general direction of flow of the hot gases G, and which further comprises a multi-perforated cross-section ventilation tube 5 circular disposed between the side plates 2, 3 in the vicinity of the edge 4, a fuel line 6 downstream of the ventilation tube 5 and a screen anti-radiation 7 which has a concave surface downstream and which connects the edges 8, 9 downstream of the side plates 2 and 3 while providing side slots 10, 11 for the evacuation of the air-fuel mixture.
- FR 2 709 342 arranged radially in the gas stream hot flowing from upstream to downstream in the direction of arrow G, which includes a sheet bent in the form of a V-shaped dihedral
- the ventilation tube 5 has holes 12 for blowing fresh air from the blower to plates 2, 3 and edge 4.
- the orifices 13 of the fuel line 6 inject a flow of fuel 14 to the side slots 10, 11.
- FIG. 2 shows a section of a flame catcher 1 ′, of the type non-fueled, as described in the published French patent application under number 2 696 502.
- the flame holder 1 ' is also present in the form of a dihedral having two side plates 2 ', 3' connected by a rounded edge 4 'oriented upstream relative to the axial direction general G of the hot gas flow.
- a 5 'ventilation tube axial is disposed between the side plates 2 ', 3'.
- This 5 'tube has a generally triangular section whose side faces 15, 16 are parallel and adjacent to the side plates 2 ', 3' and have 12 'orifices which breathe in fresh air taken from the air passage secondary from the blower at the head of the 5 'ventilation tube against the internal faces of the dihedral.
- the downstream face of the ventilation tube 5 ' is concave and has orifices 18 for injecting fresh air downstream in the afterburner 19.
- the turbofan and post-combustion turbojet shown partially in FIG. 3 comprises an annular external casing 20, of axis of revolution 21, an exhaust casing 22 of the combustion having passed through the blades of the turbo-reactor and circulating from upstream to downstream in the direction of arrow G, and a afterburner 23 downstream of the exhaust casing 22.
- the exhaust casing 22 is contained inside the casing external 20 and delimits, with the latter, a first passage 24 in which flows from the secondary air S from the blower.
- the exhaust casing 22 is constituted by an annular wall external 25 with axis 21 and an internal annular wall 26 also with axis 21.
- the exhaust casing 22, the outer wall 25 and the inner wall 26 are interconnected by connecting rods or by link arms radials not shown in the drawing.
- the outer wall 25 and the inner wall 26 define between them a second passage 27 for the flow of gases from the combustion.
- Flame catching arms 30, which extend radially obliquely towards the combustion chamber 20 are arranged at the limit the exhaust casing 22 and the afterburner 23. Each flame catching arm 30 extends substantially in a plane radial containing axis 21.
- Each flame catching arm 30 has a head portion 31 which crosses the first passage 24 and which supports downstream a ring burner 32 of annular shape with axis 21 connected by a pipe fuel 33 to a fuel supply 33a, and a main body 34 which extends inside the second passage 27 and which is the subject of the present invention.
- the main body 34 is shaped according to a dihedral having a V-shaped section whose apex of the angle is oriented upstream, the branches of the V being oriented towards downstream with respect to the general direction G of the flow of hot gases. he comprises two external plates 35, 36 having a common edge 37 of round shape.
- a ventilation tube 38 extends over the entire height of the body main 34. This tube 38 is open at its end remote from the axis 21 in order to allow a withdrawal of a cooling air flow R in the first passage 24, and is closed at its lower end. he has a plurality of orifices for evacuation over its entire length air taken from the tube 38.
- This ventilation tube 38 has a generally triangular section, and it has two side walls 39, 40 substantially parallel to the external plates 35, 36, placed a short distance from the latter in order to vigorously cool the external plates 39, 40 by the orifices 41.
- the downstream face 42 of the ventilation tube which is directed towards the interior of the afterburner 23 has a convex shape and it has a gutter 43, of open U section in which are arranged two fuel lines 44, 45 radial, supplied with fuel.
- In the wall delimiting the gutter 42 are provided orifices 46 which supply cooling air to the ducts of fuel 44, 45.
- the fuel lines 44, 45 include injectors aeromechanics 47 which inject fuel downstream to the chamber afterburner 23.
- the aeromechanical injectors 47 allow to obtain a good quality of spraying and to control the extent of the diffusion cone of fuel droplets and this in order to avoid any risk of impact on the V-shaped dihedral of the flame catcher 30.
- the ventilation tube 38 of the flame catcher 30 acts as a structural core and air supply duct R from the blower.
- the air flow R is supplied throughout the operating range of the turbojet engine to prevent the risks of coking and vapor-lock both in diet only heats in dry operation.
- the shape of the ventilation tube 38 as well as the position of the ports 41 and 46 are best suited to ensure integrity thermal of injectors.
- the arrangement proposed by the invention thus makes it possible to ensure the thermal integrity of the dihedral walls and the fuel system both in dry operation and in heating. It also allows to remove the injection organs placed in the primary flow in the case of the use of non-carbureted flame catchers, where a greater operational reliability by preventing risks of flashback.
- the proposed solution also allows the use of composite materials to make the dihedral, hence a gain in mass.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
- Exhaust Gas After Treatment (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
- Processes For Solid Components From Exhaust (AREA)
Abstract
Description
Claims (3)
- Dispositif de postcombustion pour turboréacteur à double flux comportant un carter annulaire externe (20) possédant un axe (21) de sensible révolution, un carter d'échappement (22) contenu à l'intérieur dudit carter externe (20), comprenant une paroi annulaire externe (25) et une paroi annulaire interne (26), ayant chacune le même axe de révolution que le carter externe (20) et délimitant avec lui un premier passage (24) pour l'écoulement d'un air secondaire, la paroi annulaire externe (25) et la paroi annulaire interne (26) délimitant entre elles un deuxième passage (27) pour l'écoulement des gaz de combustion, ce dispositif de postcombustion comprenant également une paroi de postcombustion annulaire (28) ayant le même axe de révolution que le carter externe (20), disposée à l'intérieur du carter externe en étant écartée d'une distance déterminée de manière à ménager un passage d'air de refroidissement et délimitant une chambre de postcombustion (23) en aval des premier (24) et deuxième (27) passages, des bras accroche-flamme (30) s'étendant dans des plans radiaux par rapport audit axe (21), au moins à l'intérieur du deuxième passage (27), et étant conformés chacun en un dièdre, délimité par deux plaques externes (35, 36) ayant une arête commune (37), et ayant une section externe en V dont la pointe est orientée vers l'amont par rapport au sens axial général d'écoulement (G) desdits gaz de combustion, chaque accroche-flamme (30) comportant en outre un tube de ventilation (38) multiperforé pour le refroidissement des plaques externes (35, 36) par un air de refroidissement prélevé dans le premier passage (24) et au moins un conduit radial de carburant(44, 45) muni d'orifices d'injection de carburant, caractérisé par le fait que le tube de ventilation (38) a une section globalement triangulaire et comporte deux faces latérales (39, 40) sensiblement parallèles aux plaques externes (35, 36) et une face aval (42) qui présente une gouttière radiale (43), dans laquelle loge le conduit de carburant (44, 45), une pluralité d'orifices supplémentaires (46) dirigés vers le conduit du carburant étant ménagés dans la paroi (42) de ladite gouttière (43) afin d'assurer la ventilation du conduit de carburant, ce dernier injectant le carburant vers l'aval.
- Dispositif selon la revendication 1, caractérisé par le fait que le conduit de carburant (44, 45) est équipé d'injecteurs aéromécaniques (46).
- Dispositif selon l'une quelconque des revendications 1 ou 2, caractérisé par le fait que chaque accroche-flamme (30) comporte deux conduits de carburant (44, 45)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9713274 | 1997-10-23 | ||
FR9713274A FR2770284B1 (fr) | 1997-10-23 | 1997-10-23 | Accroche-flamme carbure et a refroidissement optimise |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0911585A1 true EP0911585A1 (fr) | 1999-04-28 |
EP0911585B1 EP0911585B1 (fr) | 2003-09-10 |
Family
ID=9512546
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP98402599A Expired - Lifetime EP0911585B1 (fr) | 1997-10-23 | 1998-10-20 | Accroche-flamme carburé et refroidi |
Country Status (7)
Country | Link |
---|---|
US (1) | US6112516A (fr) |
EP (1) | EP0911585B1 (fr) |
JP (1) | JPH11218055A (fr) |
DE (1) | DE69817970T2 (fr) |
ES (1) | ES2202772T3 (fr) |
FR (1) | FR2770284B1 (fr) |
RU (1) | RU2150597C1 (fr) |
Cited By (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN100368731C (zh) * | 2003-08-05 | 2008-02-13 | 斯内克马发动机公司 | 加力燃烧装置 |
FR2909437A1 (fr) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Dispositif accroche-flammes, systemes de post-combustion et turboreacteur |
FR2909438A1 (fr) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Dispositif accroche-flammes, systeme de post-combustion et turboreacteur |
WO2011054760A1 (fr) * | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz |
CN102538010A (zh) * | 2012-02-12 | 2012-07-04 | 北京航空航天大学 | 一种稳定器与涡轮后整流支板一体化设计的加力燃烧室 |
US8402768B2 (en) | 2009-11-07 | 2013-03-26 | Alstom Technology Ltd. | Reheat burner injection system |
US8490398B2 (en) | 2009-11-07 | 2013-07-23 | Alstom Technology Ltd. | Premixed burner for a gas turbine combustor |
US8677756B2 (en) | 2009-11-07 | 2014-03-25 | Alstom Technology Ltd. | Reheat burner injection system |
US8713943B2 (en) | 2009-11-07 | 2014-05-06 | Alstom Technology Ltd | Reheat burner injection system with fuel lances |
CN104048324A (zh) * | 2014-07-24 | 2014-09-17 | 南京航空航天大学 | 一种蒸发式火焰稳定器 |
CN104776448A (zh) * | 2015-03-11 | 2015-07-15 | 北京航空航天大学 | 多功能模态可调稳焰支板 |
CN105992913A (zh) * | 2014-02-12 | 2016-10-05 | 法孚皮拉德公司 | 流内燃烧器模块 |
CN109915856A (zh) * | 2019-03-01 | 2019-06-21 | 西北工业大学 | 一种加力燃烧室整流支板结构 |
Families Citing this family (21)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2869953B1 (fr) * | 2004-05-05 | 2008-07-04 | Snecma Moteurs Sa | Dispositif d'alimentation en air et en carburant d'un anneau-bruleur dans une chambre de postcombustion |
FR2873168B1 (fr) * | 2004-07-16 | 2008-10-31 | Snecma Moteurs Sa | Turboreacteur comprenant une chambre de post-combustion a allumage securise |
FR2873411B1 (fr) | 2004-07-21 | 2009-08-21 | Snecma Moteurs Sa | Turboreacteur avec des moyens de protection pour un dispositif d'injection de carburant, dispositif d'injection et tole de protection pour le turboreacteur |
FR2873408B1 (fr) * | 2004-07-23 | 2008-10-17 | Snecma Moteurs Sa | Turboreacteur avec un ecran de protection de la rampe de carburant d'un anneau bruleur, l'anneau bruleur et l'ecran de protection |
US7481059B2 (en) * | 2004-08-12 | 2009-01-27 | Volvo Aero Corporation | Method and apparatus for providing an afterburner fuel-feed arrangement |
US7565804B1 (en) * | 2006-06-29 | 2009-07-28 | General Electric Company | Flameholder fuel shield |
US7581398B2 (en) * | 2006-06-29 | 2009-09-01 | General Electric Company | Purged flameholder fuel shield |
FR2950416B1 (fr) * | 2009-09-23 | 2012-04-20 | Snecma | Dispositif accroche-flammes comprenant un support de bras et un ecran de protection thermique monoblocs |
DE102009045950A1 (de) * | 2009-10-23 | 2011-04-28 | Man Diesel & Turbo Se | Drallerzeuger |
RU2480604C1 (ru) * | 2011-11-10 | 2013-04-27 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Турбореактивный двигатель |
JP2013181473A (ja) * | 2012-03-02 | 2013-09-12 | Ihi Corp | アフタバーナ及び航空機エンジン |
RU2614268C1 (ru) * | 2015-11-11 | 2017-03-24 | Акционерное общество "Научно-производственный центр газотурбостроения "Салют" (АО "НПЦ газотурбостроения "Салют") | Узел подачи топлива в форсажную камеру турбореактивного двухконтурного двигателя |
CN106610029B (zh) * | 2016-11-18 | 2019-03-26 | 西北工业大学 | 一种支板射流的一体化加力燃烧室 |
CN108426267B (zh) * | 2018-05-11 | 2023-07-25 | 北京航空航天大学 | 一种折叠v型钝体驻涡火焰稳定器 |
CN109631085B (zh) * | 2018-12-13 | 2020-06-30 | 西安航天动力研究所 | 后掠圆弧型气动雾化蒸发式稳定器 |
US11408610B1 (en) * | 2021-02-03 | 2022-08-09 | General Electric Company | Systems and methods for spraying fuel in an augmented gas turbine engine |
FR3121959B1 (fr) * | 2021-04-19 | 2024-02-09 | Safran Aircraft Engines | Dispositif d'injection de carburant amélioré pour postcombustion de turboréacteur |
CN113701191B (zh) * | 2021-09-01 | 2022-06-24 | 南昌航空大学 | 一种交错导流中缝式v型火焰稳定器 |
GB2615335B (en) * | 2022-02-04 | 2024-05-08 | Rolls Royce Plc | A reheat assembly |
GB2615337A (en) * | 2022-02-04 | 2023-08-09 | Rolls Royce Plc | Reheat assembly for gas turbine engine |
GB2615336A (en) * | 2022-02-04 | 2023-08-09 | Rolls Royce Plc | Reheat assembly for gas turbine engine |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4887425A (en) * | 1988-03-18 | 1989-12-19 | General Electric Company | Fuel spraybar |
US5396761A (en) * | 1994-04-25 | 1995-03-14 | General Electric Company | Gas turbine engine ignition flameholder with internal impingement cooling |
US5400589A (en) * | 1982-10-07 | 1995-03-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Afterburner for a turbofan engine |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4490973A (en) * | 1983-04-12 | 1985-01-01 | The United States Of America As Represented By The Secretary Of The Air Force | Flameholder with integrated air mixer |
US4901527A (en) * | 1988-02-18 | 1990-02-20 | General Electric Company | Low turbulence flame holder mount |
FR2706588B1 (fr) * | 1993-06-16 | 1995-07-21 | Snecma | Système d'injection de carburant pour chambre de combustion. |
FR2709342B1 (fr) | 1993-08-25 | 1995-09-22 | Snecma | Dispositif de post combustion d'un turboréacteur. |
US5813221A (en) * | 1997-01-14 | 1998-09-29 | General Electric Company | Augmenter with integrated fueling and cooling |
-
1997
- 1997-10-23 FR FR9713274A patent/FR2770284B1/fr not_active Expired - Fee Related
-
1998
- 1998-10-20 DE DE69817970T patent/DE69817970T2/de not_active Expired - Fee Related
- 1998-10-20 EP EP98402599A patent/EP0911585B1/fr not_active Expired - Lifetime
- 1998-10-20 ES ES98402599T patent/ES2202772T3/es not_active Expired - Lifetime
- 1998-10-22 RU RU98119148/06A patent/RU2150597C1/ru not_active IP Right Cessation
- 1998-10-22 JP JP10300584A patent/JPH11218055A/ja not_active Withdrawn
- 1998-10-23 US US09/177,492 patent/US6112516A/en not_active Expired - Fee Related
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5400589A (en) * | 1982-10-07 | 1995-03-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Afterburner for a turbofan engine |
US4887425A (en) * | 1988-03-18 | 1989-12-19 | General Electric Company | Fuel spraybar |
US5396761A (en) * | 1994-04-25 | 1995-03-14 | General Electric Company | Gas turbine engine ignition flameholder with internal impingement cooling |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN100368731C (zh) * | 2003-08-05 | 2008-02-13 | 斯内克马发动机公司 | 加力燃烧装置 |
FR2909437A1 (fr) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Dispositif accroche-flammes, systemes de post-combustion et turboreacteur |
FR2909438A1 (fr) * | 2006-12-04 | 2008-06-06 | Snecma Sa | Dispositif accroche-flammes, systeme de post-combustion et turboreacteur |
US8677756B2 (en) | 2009-11-07 | 2014-03-25 | Alstom Technology Ltd. | Reheat burner injection system |
WO2011054760A1 (fr) * | 2009-11-07 | 2011-05-12 | Alstom Technology Ltd | Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz |
US8713943B2 (en) | 2009-11-07 | 2014-05-06 | Alstom Technology Ltd | Reheat burner injection system with fuel lances |
US8402768B2 (en) | 2009-11-07 | 2013-03-26 | Alstom Technology Ltd. | Reheat burner injection system |
US8490398B2 (en) | 2009-11-07 | 2013-07-23 | Alstom Technology Ltd. | Premixed burner for a gas turbine combustor |
US8572980B2 (en) | 2009-11-07 | 2013-11-05 | Alstom Technology Ltd | Cooling scheme for an increased gas turbine efficiency |
CN102538010B (zh) * | 2012-02-12 | 2014-03-05 | 北京航空航天大学 | 一种稳定器与涡轮后整流支板一体化设计的加力燃烧室 |
CN102538010A (zh) * | 2012-02-12 | 2012-07-04 | 北京航空航天大学 | 一种稳定器与涡轮后整流支板一体化设计的加力燃烧室 |
CN105992913A (zh) * | 2014-02-12 | 2016-10-05 | 法孚皮拉德公司 | 流内燃烧器模块 |
CN105992913B (zh) * | 2014-02-12 | 2018-12-18 | 法孚皮拉德公司 | 流内燃烧器模块 |
CN104048324A (zh) * | 2014-07-24 | 2014-09-17 | 南京航空航天大学 | 一种蒸发式火焰稳定器 |
CN104776448A (zh) * | 2015-03-11 | 2015-07-15 | 北京航空航天大学 | 多功能模态可调稳焰支板 |
CN109915856A (zh) * | 2019-03-01 | 2019-06-21 | 西北工业大学 | 一种加力燃烧室整流支板结构 |
CN109915856B (zh) * | 2019-03-01 | 2020-06-16 | 西北工业大学 | 一种加力燃烧室整流支板结构 |
Also Published As
Publication number | Publication date |
---|---|
JPH11218055A (ja) | 1999-08-10 |
DE69817970T2 (de) | 2004-07-22 |
US6112516A (en) | 2000-09-05 |
RU2150597C1 (ru) | 2000-06-10 |
EP0911585B1 (fr) | 2003-09-10 |
DE69817970D1 (de) | 2003-10-16 |
ES2202772T3 (es) | 2004-04-01 |
FR2770284A1 (fr) | 1999-04-30 |
FR2770284B1 (fr) | 1999-11-19 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP0911585B1 (fr) | Accroche-flamme carburé et refroidi | |
CA2588952C (fr) | Chambre de combustion d'une turbomachine | |
CA2646959C (fr) | Systeme d'injection d'un melange d'air et de carburant dans une chambre de combustion de turbomachine | |
EP1593911B1 (fr) | Dispositif d'alimentation en air et en carburant d'un anneau-brûleur dans une chambre de postcombustion | |
EP2042806B1 (fr) | Chambre de combustion d'une turbomachine | |
EP0214003B1 (fr) | Dispositif d'injection à bol elargi pour chambre de combustion de turbomachine | |
EP1907754B1 (fr) | Procédé et installation de combustion de gaz combustible pauvre, sans soutien, à l'aide d'un brûleur et brûleur associé | |
EP0592305A1 (fr) | Dispositif de post-combustion pour turbo-réacteur double flux | |
FR2942640A1 (fr) | Chambre de post-combustion pour turbomachine | |
FR2709342A1 (fr) | Dispositif de post combustion d'un turboréacteur. | |
EP3430316B1 (fr) | Chambre de combustion d'une turbine, notamment d'une turbine a cycle thermodynamique avec recuperateur, pour la production d'energie, en particulier d'energie electrique | |
FR2975467A1 (fr) | Systeme d'injection de carburant pour une chambre de combustion de turbomachine | |
EP1621817B1 (fr) | Chambre de post-combustion à allumage sécurisé | |
WO2009144408A2 (fr) | Chambre de combustion annulaire de moteur a turbine a gaz | |
EP0879995B1 (fr) | Système de réchauffe dichotomique réduisant les pertes en sec. | |
EP0727615A1 (fr) | Ensemble d'injection de carburant pour chambre de combustion de turbines à gaz | |
FR2804748A1 (fr) | Perfectionnement aux bruleurs a gaz pour le chauffage d'un gaz circulant dans un conduit | |
FR2504983A1 (fr) | Dispositif de post-combustion pour turbo-reacteur | |
EP4327023A1 (fr) | Cone de diffusion pour partie arriere de turboreacteur integrant un anneau accroche-flamme en bord de fuite | |
FR2673705A1 (fr) | Chambre de combustion de turbomachine munie d'un dispositif anti-cokefaction du fond de ladite chambre. | |
EP3969813A1 (fr) | Chambre de combustion comprenant des moyens de refroidissement d'une zone d'enveloppe annulaire en aval d'une cheminee | |
WO2022223916A1 (fr) | Dispositif d'injection de carburant pour postcombustion de turboreacteur | |
FR3094777A1 (fr) | Chambre de combustion principale de turboréacteur équipée d’une grille en aval de ses bruleurs | |
FR3136016A1 (fr) | Anneau accroche-flammes pour postcombustion de turboreacteur comprenant un conduit pour chauffer un segment angulaire de l'anneau | |
FR3136017A1 (fr) | Anneau accroche-flammes pour postcombustion de turboreacteur comprenant des ecopes de prelevement de flux primaire |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 19981030 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): DE ES FR GB IT SE |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
AKX | Designation fees paid |
Free format text: DE ES FR GB IT SE |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
GRAH | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOS IGRA |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SNECMA MOTEURS |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE ES FR GB IT SE |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20030922 Year of fee payment: 6 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20030924 Year of fee payment: 6 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20031016 Year of fee payment: 6 |
|
REF | Corresponds to: |
Ref document number: 69817970 Country of ref document: DE Date of ref document: 20031016 Kind code of ref document: P |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: ES Payment date: 20031022 Year of fee payment: 6 |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20031029 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20031219 Year of fee payment: 6 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FG2A Ref document number: 2202772 Country of ref document: ES Kind code of ref document: T3 |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20040614 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20041020 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: SE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20041021 Ref country code: ES Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20041021 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20050503 |
|
EUG | Se: european patent has lapsed | ||
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20041020 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20050630 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20051020 |
|
REG | Reference to a national code |
Ref country code: ES Ref legal event code: FD2A Effective date: 20041021 |