EP1619441A1 - Strahltriebwerk mit Schutzvorichtungen für einen Kraftstoffinjektor, Kraftstoffinjector und Schutzblech - Google Patents

Strahltriebwerk mit Schutzvorichtungen für einen Kraftstoffinjektor, Kraftstoffinjector und Schutzblech Download PDF

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Publication number
EP1619441A1
EP1619441A1 EP05105976A EP05105976A EP1619441A1 EP 1619441 A1 EP1619441 A1 EP 1619441A1 EP 05105976 A EP05105976 A EP 05105976A EP 05105976 A EP05105976 A EP 05105976A EP 1619441 A1 EP1619441 A1 EP 1619441A1
Authority
EP
European Patent Office
Prior art keywords
turbojet engine
fuel injection
engine according
arm
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP05105976A
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English (en)
French (fr)
Other versions
EP1619441B1 (de
Inventor
Jacques Marcel Arthur Bunel
Alain Pierre Page
Jacques-A Roche
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 SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1619441A1 publication Critical patent/EP1619441A1/de
Application granted granted Critical
Publication of EP1619441B1 publication Critical patent/EP1619441B1/de
Active legal-status Critical Current
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
    • F23R3/02—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
    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a turbojet comprising a heating channel of the primary gas flow, with a fuel injection device and protection means for the fuel injection device.
  • the invention also concerns, as intermediate products, a fuel injection device and a protective sheet for said turbojet engine.
  • the so-called “afterburner” turbojets generally comprise, upstream to downstream in the direction of gas flow, one or more compressor stages, a combustion chamber, one or more turbine stages, a heating channel or channel afterburner, and an ejection nozzle.
  • the flow of primary gas, downstream of the turbine stages, allows a new combustion, thanks to the oxygen still present within it, in the heating channel before relaxing in the ejection nozzle.
  • flame-holder arms extend radially in the gas flow. They are generally U-shaped section, the branches of the U being oriented downstream, and comprise within them a fuel injector projecting the latter into the gas vein, towards the downstream.
  • the fuel is ignited and the flames are, due to the shape of the section of the arms, causing a depression, hanging on the walls of the arms.
  • a flame ring, concentric with the casing of the heating channel, can also be provided in the gas stream of the primary flow. It works according to the same principle.
  • the primary flow is at a temperature of about 950 ° C.
  • the walls of the flame holder arms although cooled by a jacket supplied with air from the secondary air stream at 200 or 250 ° C, are at a temperature of around 800 to 850 ° C, especially at their trailing edge. , while the flames hung on the arms are at a temperature of 1700 ° C.
  • the fuel is thrown at a temperature of about 100 ° C, more precisely between 50 and 150 ° C, against the walls of the arm at 850 ° C.
  • US 5, 179, 832 proposes, in the case of an annular injection device having two walls forming an enclosure open upstream and downstream, a protective sheet adjacent to the outer wall, against which is projected the fuel .
  • the fuel is thrown by a remote fuel injector tube on the inner side of the upstream opening of the enclosure.
  • Such protection is however not satisfactory in the case of a closed enclosure on the upstream side.
  • the present invention aims to overcome these disadvantages.
  • the invention relates to a turbojet, comprising a gas flow heating channel, the heating channel comprising at least one fuel injection device in the gas stream, which comprises an open chamber, having a section U-shaped, comprising at least one wall and within which extend fuel injection means, which inject the fuel in at least one direction, characterized in that a cooling jacket is provided in the enclosure, on the side of the wall forming the base of its U-shaped section, and the fuel injection device comprises protective means interposed between the fuel injection means and the wall, in a direction of injection of fuel.
  • the protection means comprise at least one sheet.
  • the injection device is in the form of a radial arm.
  • the protection means extend along the entire radial height of the arm.
  • the fuel injection means comprise at least one tube, supplied with fuel and having fuel injection orifices.
  • the fuel injection device further comprising a protective screen, placed in the opening of the enclosure, the protection means are positioned between a wall of the enclosure and the protective screen.
  • the fuel injection means are placed between the walls forming the branches of the U-shaped section of the enclosure.
  • a sheet is placed substantially parallel to each of the walls of the enclosure forming the branches of its U-section.
  • each sheet is fixed to the wall to which it is substantially parallel.
  • each sheet is attached to the cooling jacket.
  • the sheet metal has a U-section, obviously a radial one, in the central part of the wall forming the base of its U-section, which is slid on a slide-forming piece, integral with the cooling jacket. .
  • the invention also relates to a fuel injection device for the turbojet engine above.
  • the invention also relates to a protective sheet for a fuel injection device for the turbojet engine above.
  • the turbojet engine 1 of the invention which extends along an axis 1 ', comprises a plurality of compressor stages 2, a combustion chamber 3, several turbine stages 4, a heat flux channel 5 and an ejection nozzle 6.
  • the heating channel 5 is delimited by an inner liner 5 'enveloped by an outer casing 5 ". These two elements 5', 5" delimit between them a passage for cooling air. cooling.
  • the function of the injectors is to vaporize fuel towards flame holder arms 8, situated downstream in the heating channel 5.
  • the flame holder arms 8 are the same number, here nine, the fuel injector arms 7 and are angularly offset from them, so that in front view, each fuel injector arm 7 is located between two neighboring flame holder arms 8, equidistant from them.
  • the fuel injector arms 7 are radially smaller than the flame holder arms 8.
  • This ring 9 is made up of a plurality of 9 'ring portions, here nine in number, which extend concentrically to the casings 5', 5 "of the heating channel 5, between two flame-holder arms 8 successive.
  • a fuel injector arm 7 comprises a radial cooling sleeve 7a extending over the entire radial height of the arm 7, parallel to which extends, downstream, a fuel injector tube 7b, fueled from the outside of the outer casing 5 "of the heating channel 5 and having fuel vaporization ports, the cooling jacket 7a is supplied with cooling air, taken from the secondary air flow, and has orifices. allowing the arm 7 to be cooled by air impingement
  • the fuel injector arms 7 extend radially perpendicularly to the axis 1 'of the turbojet engine 1.
  • the flame-holder arms 8 extend radially, inclined downstream, from their base integral with the outer casing 5 "of the heating channel 5, with respect to the perpendicular to the axis 1 'of the turbojet engine 1 contained in FIG. the axial plane of the arm 8.
  • a flame-holder arm 8 comprises an open enclosure delimited by walls 8 '- which can be replaced in a similar manner by a continuous wall 8' - in which are contained its various elements. Flame comprises a radial cooling jacket 8a, extending over the entire radial height of the arm 8, parallel to which extends, downstream, a fuel injector tube 8b, supplied with fuel from outside the outer casing 5 "and having fuel jet orifices.
  • the simplified operation of the turbojet engine is as follows. Fuel is vaporized by the fuel injector tubes 7b of the fuel injector arms 7 and by the fuel injector tubes 8b of the flame holder arms 8. This fuel undergoes, thanks to the residual oxygen of the primary gas flow, also thanks to to a supply of air from the secondary flow, a combustion. This combustion occurs at the level of flame-holder arms 8, the shape of which causes the flames to be held by said arms 8. This combustion, called post combustion or heating, provides an additional thrust to the turbojet engine. This post combustion process is well known to those skilled in the art and will therefore not be detailed more precisely. The gas then relaxes in the heating channel 5 and in the ejection nozzle 6 before being ejected from the turbojet engine 1.
  • the outer walls 8 'of a flame holder arm 8, defining its open enclosure, have a U-shaped section, whose branches are facing downstream. More precisely, the branches of the U are not parallel; it would be more of a V with a rounded base; it will be mentioned in the following section U.
  • the cooling jacket 8a occupies the upstream portion of this U-section, that is to say its closed portion.
  • This jacket 8a has a plurality of orifices, typically nine hundred, through which is projected the air of the secondary flow with which it is fed, to cool the walls 8 'of the arm 8. Just downstream, centered by relative to the walls 8 'extends the fuel injector tube 8b.
  • a protective screen 8c also of U-shaped section, whose function is to protect the fuel injector tube 8b and the cooling jacket 8a of the flame attached to the trailing edges of the walls 8 'of the arm 8.
  • This screen 8c occupies almost all the space left between the end of the walls 8' of the arm 8 forming the branches of its U-section.
  • a protective plate 8d extends between the walls of the protective screen 8c and the walls 8 'of the arm 8. Its function is to prevent a direct impact of the fuel on the walls 8' of the arm 8, the disadvantages of which have been presented above.
  • the flame holder arm 8 comprises two protective plates 8d, extending substantially parallel to the two walls 8 'forming the branches of the U-section of the arm 8, since the cooling jacket 8a, without being in contact with it and forming in its vicinity a slight elbow towards the inside of the arm, to the trailing edges of the arm 8.
  • the plates 8d extend over the entire radial height of the arm 8.
  • the fuel shown schematically by dashed lines 10, is projected from the fuel injector tube 8d onto the protective plates 8d, before being ejected, between said plates 8d and the protective screen 8c, out of the arm 8, where he is inflamed.
  • FIG. 5 shows the method of fixing a protective plate 8d within an arm 8.
  • the protective plate 8d is fixed to the wall 8 'of the arm 8, to which it is substantially parallel, by means of fixing pins 11 passing through holes provided for this purpose in the sheet 8d and the wall 8 '.
  • spacers 12 are positioned between their surfaces facing one another, around the fixing pins 11.
  • the protective screen 8c is fixed to the protective plate 8d at its wall portions corresponding to the branches of its U-section, by the same fixing pins 11.
  • Such wall portion is generally in the form of a plate, having recesses 13 in which are drilled through holes fixing pins 12.
  • the screen 8c is plated on the sheet 8d at the recesses 13, while the bulk of its surface is discarded of the sheet 8d, so as to leave a passage space for the fuel 10.
  • the fixing pins 11 are arbitrary and will be chosen by those skilled in the art.
  • the fuel 10 projected by the tube 8b does not come into contact with the walls 8 'of the arm 8, whose temperature is very important, avoiding them to undergo a too great thermal gradient. It is projected on the protective sheets 8d, which are within the space defined by the walls 8 'of the arm 8 and are at a lower temperature, thanks in particular to the cooling provided by the jacket 8a. Their temperature is typically 600 to 650 ° C, instead of 850 ° C for the walls 8 'of the arm 8. The thermal gradient to which they are subjected is less important.
  • the sheets 8d may be made of any suitable material, for example metal, ceramic or ceramic matrix components (CMC).
  • the sheets 8d thus protect the walls 8 'of the arm 8, since they are placed between the tube 8b and the walls 8' of the arm, in the fuel injection direction; they undergo deformations, but once deformed they are easily replaceable, at least more easily than the walls 8 'of the arm 8, which ensures lower maintenance costs than for the structures of the prior art.
  • a sheet 8d can be directly attached to the cooling jacket 8a.
  • the arm 8 comprises two protective plates 8d, extending substantially parallel to the two walls forming the branches of the U-section of the arm 8, these two plates 8d being fixed to the cooling jacket 8a of the arm 8, in its downstream portion.
  • the attachment can be obtained by any means of attachment.
  • the sheets 8d preferably extend to the trailing edges of the arm 8, over its entire radial height.
  • the sheets 8d can be, on the one hand, fixed to the cooling jacket 8a, on the other hand, fixed to the walls 8 'of the arm 8, for example in the same way as previously.
  • the operation of the arm 8 and the protection of the walls 8 'by the protective plates 8d are similar to those described above.
  • the advantage of this solution is the continuity between the protective plates 8d and the cooling jacket 8a, excluding any possible contact between the fuel and the walls 8 'of the arm 8.
  • a U-shaped sheet metal 8d having a radial recess 15 in the central part of the wall forming the base of its U-section, extending from a radial end of the plate 8d. almost to its other radial end.
  • the sheet 8d is slid into a T-section part 14, integral with the cooling jacket 8a by the base of the T.
  • This part 14 thus forms a slide for the protective plate 8d, at its recess 15, which is slid until its non-recessed radial end comes into abutment on the piece 14. It can be locked to the piece 14.
  • the protective plate 8d protects not only the walls 8 'of the arm 8 by the walls forming the branches of its U-section, extending to the trailing edge of the arm 8, but also the cooling jacket 8a by the wall forming the base of its U-section, completed by the wall of the slide 14 forming the bar of its section T.
  • the operation of the arm 8 and its protection by the protective plate 8d are also quite comparable to what has been seen previously.
  • the advantage of this embodiment of the protective plate 8d is its ease of replacement, by simple translational movement in the slide 14.
  • the sheet 8d is furthermore as a single piece, to protect all the walls 8 'of the arm 8.
  • the protective plate 8d in its downstream region close to a trailing edge of the arm 8 may be, whatever its overall shape, shaped differently than a simple plate.
  • the downstream end wall of the protective plate 8d may include slots 16, which can absorb the deformations to which the sheet 8d is subjected. These slots 16 may optionally be completed by circular recesses 17 at their upstream end, which allow greater deformation of the sheet portions 8d located between two slots 16.
  • the walls of the sheet 8d may have, in their downstream end portion, or even over their entire wall substantially parallel to a wall 8 'of the arm 8, a section, sectional view transverse to the overall plane of the wall, of corrugated shape, which absorbs the deformations related to thermal gradients. Indeed, this type of undulations is generally the result of deformations; the fact of providing them in advance allows somehow to pre-constrain the sheet 8d.
  • the invention has been presented in connection with a fuel injection device in the primary gas flow which is a radial arm, but it goes without saying that the invention applies to any type of fuel injection device in the primary gas stream, including a ring.

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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)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05105976.4A 2004-07-21 2005-06-30 Kraftstoffinjector mit Schutzvorichtungen und Strahltriebwerk mit einem derartigen Kraftstoffinjector Active EP1619441B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0408059A FR2873411B1 (fr) 2004-07-21 2004-07-21 Turboreacteur avec des moyens de protection pour un dispositif d'injection de carburant, dispositif d'injection et tole de protection pour le turboreacteur

Publications (2)

Publication Number Publication Date
EP1619441A1 true EP1619441A1 (de) 2006-01-25
EP1619441B1 EP1619441B1 (de) 2016-09-14

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP05105976.4A Active EP1619441B1 (de) 2004-07-21 2005-06-30 Kraftstoffinjector mit Schutzvorichtungen und Strahltriebwerk mit einem derartigen Kraftstoffinjector

Country Status (5)

Country Link
US (1) US7600383B2 (de)
EP (1) EP1619441B1 (de)
CA (1) CA2512375C (de)
FR (1) FR2873411B1 (de)
RU (1) RU2373416C2 (de)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1840469A1 (de) * 2006-03-30 2007-10-03 Snecma Nachbrennerarm einer Nachbrennkammer
FR2909438A1 (fr) * 2006-12-04 2008-06-06 Snecma Sa Dispositif accroche-flammes, systeme de post-combustion et turboreacteur
FR2909437A1 (fr) * 2006-12-04 2008-06-06 Snecma Sa Dispositif accroche-flammes, systemes de post-combustion et turboreacteur
EP1835230A3 (de) * 2006-03-14 2010-12-29 United Technologies Corporation Stützkonstruktion für Sprührohre
WO2011054760A1 (en) * 2009-11-07 2011-05-12 Alstom Technology Ltd A cooling scheme for an increased gas turbine efficiency
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

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FR2928202A1 (fr) * 2008-02-29 2009-09-04 Snecma Sa Accroche flamme pour canal de rechauffe d'un turboreacteur avec une semelle d'ecartement, canal de rechauffe et turboreacteur comprenant un canal de rechauffe.
US9759424B2 (en) * 2008-10-29 2017-09-12 United Technologies Corporation Systems and methods involving reduced thermo-acoustic coupling of gas turbine engine augmentors
FR2950416B1 (fr) * 2009-09-23 2012-04-20 Snecma Dispositif accroche-flammes comprenant un support de bras et un ecran de protection thermique monoblocs
US9879862B2 (en) 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
EP2837888A1 (de) * 2013-08-15 2015-02-18 Alstom Technology Ltd Sequentielle Verbrennung mit Verdünnungsgasmischer
EP2955442A1 (de) 2014-06-11 2015-12-16 Alstom Technology Ltd Prallgekühlte Wandanordnung
FR3032519B1 (fr) * 2015-02-10 2017-02-24 Herakles Dispositif accroche-flamme
CA2988555C (en) 2015-06-16 2019-03-26 Ihi Corporation Engine aft section structure
CN106642200B (zh) * 2016-12-23 2019-02-12 中航空天发动机研究院有限公司 一种驻涡式的凹腔支板火焰稳定器
CN106642201B (zh) * 2016-12-23 2019-07-09 中航空天发动机研究院有限公司 用于飞行器发动机燃烧室的火焰稳定装置
CN106642202B (zh) * 2016-12-23 2019-02-12 中航空天发动机研究院有限公司 一种用于tbcc亚燃冲压发动机燃烧室的火焰稳定装置
CN113028449B (zh) * 2021-02-26 2023-03-17 中国空气动力研究与发展中心设备设计与测试技术研究所 一种燃气发生器流线型燃料分流盘
RU205518U1 (ru) * 2021-03-10 2021-07-19 Акционерное общество "ОДК-Климов" Форсажная камера двухконтурного турбореактивного двигателя
FR3122719A1 (fr) * 2021-05-04 2022-11-11 Safran Aircraft Engines Accroche-flammes pour postcombustion de turboréacteur comprenant des bras à bords de fuite dentelés
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
CN113898973B (zh) * 2021-09-15 2022-10-21 南京航空航天大学 一种油气复合冷却式火焰稳定器及燃烧室
CN114646078A (zh) * 2022-03-15 2022-06-21 西北工业大学 一种新型加力燃烧室整流支板结构

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EP0744543A1 (de) * 1995-05-25 1996-11-27 United Technologies Corporation Nachbrennerkühlung
FR2770284A1 (fr) * 1997-10-23 1999-04-30 Snecma Accroche-flamme carbure et a refroidissement optimise
EP1132687A1 (de) * 2000-02-29 2001-09-12 General Electric Company Verfahren und Vorrichtung zur Reduzierung der thermischen Belastungen eines Nachbrenners
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US5396763A (en) * 1994-04-25 1995-03-14 General Electric Company Cooled spraybar and flameholder assembly including a perforated hollow inner air baffle for impingement cooling an outer heat shield
US6463739B1 (en) * 2001-02-05 2002-10-15 General Electric Company Afterburner heat shield
US7467518B1 (en) * 2006-01-12 2008-12-23 General Electric Company Externally fueled trapped vortex cavity augmentor

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1364192A (fr) * 1963-05-22 1964-06-19 Bristol Siddeley Engines Ltd Perfectionnements apportés aux moteurs de propulsion par réaction
US5179832A (en) * 1991-07-26 1993-01-19 United Technologies Corporation Augmenter flame holder construction
FR2689211A1 (fr) * 1992-03-30 1993-10-01 Stein Industrie Busette orientable en matériau réfractaire pour injection d'air et de combustible dans les brûleurs de chaudières de centrales thermiques.
FR2709342A1 (fr) * 1993-08-25 1995-03-03 Snecma Dispositif de post combustion d'un turboréacteur.
US5396761A (en) * 1994-04-25 1995-03-14 General Electric Company Gas turbine engine ignition flameholder with internal impingement cooling
EP0744543A1 (de) * 1995-05-25 1996-11-27 United Technologies Corporation Nachbrennerkühlung
FR2770284A1 (fr) * 1997-10-23 1999-04-30 Snecma Accroche-flamme carbure et a refroidissement optimise
US20020189259A1 (en) * 1999-04-01 2002-12-19 Peter Laing Fuel manifold block and ring with macrolaminate layers
EP1132687A1 (de) * 2000-02-29 2001-09-12 General Electric Company Verfahren und Vorrichtung zur Reduzierung der thermischen Belastungen eines Nachbrenners

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1835230A3 (de) * 2006-03-14 2010-12-29 United Technologies Corporation Stützkonstruktion für Sprührohre
EP1840469A1 (de) * 2006-03-30 2007-10-03 Snecma Nachbrennerarm einer Nachbrennkammer
FR2899316A1 (fr) * 2006-03-30 2007-10-05 Snecma Sa Bras accroche-flammes d'une chambre de post-combustion
US7856828B2 (en) 2006-03-30 2010-12-28 Snecma Flameholder arm for an afterburner
FR2909438A1 (fr) * 2006-12-04 2008-06-06 Snecma Sa Dispositif accroche-flammes, systeme de post-combustion et turboreacteur
FR2909437A1 (fr) * 2006-12-04 2008-06-06 Snecma Sa Dispositif accroche-flammes, systemes de post-combustion et turboreacteur
WO2011054760A1 (en) * 2009-11-07 2011-05-12 Alstom Technology Ltd A cooling scheme for an increased gas turbine efficiency
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
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

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RU2373416C2 (ru) 2009-11-20
US7600383B2 (en) 2009-10-13
US20060016192A1 (en) 2006-01-26
CA2512375A1 (fr) 2006-01-21
FR2873411B1 (fr) 2009-08-21
CA2512375C (fr) 2012-11-27
RU2005123131A (ru) 2007-01-27
EP1619441B1 (de) 2016-09-14
FR2873411A1 (fr) 2006-01-27

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