EP2071241A1 - Vorrichtung zum Lenken eines Elements in die Öffnung einer Brennkammerwand eines Turbinentriebwerks - Google Patents

Vorrichtung zum Lenken eines Elements in die Öffnung einer Brennkammerwand eines Turbinentriebwerks Download PDF

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Publication number
EP2071241A1
EP2071241A1 EP08167792A EP08167792A EP2071241A1 EP 2071241 A1 EP2071241 A1 EP 2071241A1 EP 08167792 A EP08167792 A EP 08167792A EP 08167792 A EP08167792 A EP 08167792A EP 2071241 A1 EP2071241 A1 EP 2071241A1
Authority
EP
European Patent Office
Prior art keywords
sleeve
ring
solder
washer
axis
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
EP08167792A
Other languages
English (en)
French (fr)
Other versions
EP2071241B1 (de
Inventor
Patrick Audin
Florian André François Bessagnet
Pierre Pascal Sablayrolles
Guillaume Sevi
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 EP2071241A1 publication Critical patent/EP2071241A1/de
Application granted granted Critical
Publication of EP2071241B1 publication Critical patent/EP2071241B1/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
    • F23R3/28—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
    • F23R3/002—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
    • F23R3/42—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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49348—Burner, torch or metallurgical lance making

Definitions

  • the present invention relates to a device for guiding an element, such as a spark plug or a fuel injector, extending in an orifice or in the vicinity of an orifice of a turbomachine combustion chamber wall. .
  • An annular turbomachine combustion chamber is defined by two coaxial revolution walls which extend one inside the other and which are interconnected at their upstream ends by an annular wall of the chamber bottom.
  • the bottom wall of the chamber has mounting holes for injecting a mixture of air and fuel inside the chamber, the air coming from a compressor of the turbomachine and the fuel being supplied by injectors.
  • injectors extend substantially radially from their outer ends fixed to an outer casing of the chamber, to their heads aligned axially with the orifices of the chamber bottom wall.
  • the external wall of revolution of the chamber comprises at least one orifice for passing one end of a spark plug whose other end is fixed on an outer casing of the chamber, this spark plug being intended to initiate the combustion of the mixture of air and fuel in the room.
  • the walls of the combustion chamber expand thermally, which causes relative displacements between the outer wall of the chamber and the spark plug and between the bottom wall of the chamber and the fuel injectors.
  • guiding devices for the spark plug and the injectors each of which comprises a substantially coaxial ring and a sleeve mounted one inside the other, the ring being intended to be crossed.
  • This sleeve comprises two coaxial annular pieces which are fixed to one another by welding and which define between them the annular groove for guiding the flange of the ring.
  • the patent application EP-A1-1,770,332 of the applicant describes a guiding device of this type.
  • the relative displacements between the outer wall of the chamber and the candle are mainly in a direction parallel to the longitudinal axis of the chamber.
  • the bushing integral with the wall of the chamber is therefore essentially displaced in this longitudinal direction relative to the guide ring of the spark plug carried by the outer casing.
  • the relative displacements of the ring in the groove of the sleeve in the other transverse directions are smaller amplitudes.
  • the axial or longitudinal direction is the preferred direction of movement of the guide ring of the spark plug relative to the socket carried by the chamber.
  • the relative displacements between the bottom wall of the chamber and the injectors are mainly in radial directions relative to the longitudinal axis of the chamber, the preferred direction of relative displacement of the ring mounted around an injector is therefore a direction radial to the longitudinal axis of the chamber.
  • the two annular pieces forming the sleeve of a guiding device are fixed to one another at their outer peripheries by one or more seams which extend over the entire periphery of the socket.
  • the weld seams may overflow into the annular guide groove of the ring and locally clog the outer periphery of this groove, reducing or thus preventing deflections of the ring in transverse direction in the groove of the socket.
  • the welding operation of the parts of the sleeve is therefore difficult to achieve and does not control these weld overflows.
  • a solution to this problem would be to oversize the parts of the sleeve so that the annular groove has a greater transverse dimension than necessary to maintain maximum travel of the ring in the transverse direction, even when the weld beads overflow. inside the throat.
  • the invention aims in particular to provide a simple, effective and economical solution to this problem.
  • a device for guiding an element in an orifice of a turbomachine combustion chamber wall comprising a substantially coaxial ring and a bushing mounted one inside the other, the ring being intended to be traversed axially by the element and having an outer annular flange guided transversely in an internal annular groove of the sleeve intended to be fixed on the edge of the orifice of the wall of the combustion chamber, the sleeve comprising two coaxial annular pieces fixed to one another by brazing or welding and defining between them the annular groove for guiding the rim of the ring, and the device comprising at least one preferred transverse direction of movement of the ring, characterized in that the two pieces of the sleeve are fixed to one another by soldering or soldering zones, these areas being outside the path of the rim of the ring when it is moved relative to the sleeve in the preferred direction,
  • the two soldering or soldering zones of the two parts of the sleeve are not located on the preferred direction of movement of the ring, and the overflows of the weld or solder cords which penetrate into the groove of the sleeve. socket and close locally do not limit the movement of the rim of the ring in this direction. It is therefore not necessary to take into account the overflows of the weld seams in the sizing of the sleeve of the guiding device. In a particular embodiment of the invention, this makes it possible to obtain a reduction of about 2 mm over the diameter of the socket compared to the prior art.
  • the areas of solder or solder are distributed around the axis of the bushing.
  • These zones can be two in number and are then diametrically opposite to the axis of the socket.
  • One of the two parts of the sleeve is for example a washer with a substantially oval or oblong outer contour, this washer having end portions with a smaller radius of curvature which are brazed or welded to the other part of the sleeve.
  • This particular form of the washer of the socket reduces the mass of the device.
  • the areas of solder or solder are aligned on an axis substantially perpendicular to the preferred direction of movement of the ring.
  • the zones of soldering or brazing are four in number and are diametrically opposed two by two with respect to the axis of the socket.
  • One of the two parts of the sleeve is for example a washer with an outer contour of substantially square shape to reduce the mass of this part, this washer having end portions corresponding to the vertices of the square which are brazed or welded to the other part of the socket.
  • the diametrically opposite welding zones are aligned on axes inclined at an angle of approximately 45 ° relative to the preferred direction of movement of the ring.
  • the present invention also relates to a turbomachine combustion chamber, characterized in that it comprises at least one device as described above, and a turbomachine, such as an airplane turbojet or turboprop, characterized in that it comprises at least one turbine of this type.
  • FIG. 1 represents an annular combustion chamber 10, for a turbomachine such as an aircraft turbojet, arranged at the outlet of an annular diffuser 12, itself located at the outlet of a compressor (not shown).
  • the chamber 10 comprises a wall 14 of internal revolution and a wall of external revolution 16 connected upstream to an annular wall 18 of chamber bottom and attached downstream by annular inner and outer 20 and outer ring 22 respectively on an internal frustoconical web 24 of diffuser, and on a downstream end of an outer casing 26 of the chamber, the upstream end of this housing 26 being fixed on an outer frustoconical web 28 of the diffuser.
  • the wall 18 of the chamber bottom has holes 30 for mounting systems 37 for injecting a mixture of air and fuel into the chamber 10, the air coming from the diffuser 12 and the fuel being supplied by injectors 32
  • the injectors 32 are fixed at their radially external ends to the outer casing 26 and regularly distributed over a circumference around the axis of revolution 34 of the chamber.
  • Each injector 32 comprises at its radially inner end a fuel injection head 36 which is guided in an injection system 37 and which is aligned with the axis 38 of a corresponding orifice 30 of the wall 18 of the chamber, this axis 38 being merged in the drawing with the longitudinal axis of the section of the chamber.
  • An upstream curved annular hood 40 is fixed on the upstream ends of the walls 14, 16 and 18 of the chamber and comprises orifices 42 for air passage aligned with the orifices 30 of the wall 18 of the chamber bottom.
  • the mixture of air and fuel injected into the chamber 10 is ignited by means of at least one spark plug 44 which extends radially outside the chamber.
  • This plug 44 is guided at its radially inner end in an orifice 46 of the outer wall 16 of the chamber, and its radially outer end is fixed by appropriate means on the outer casing 26 and connected to electrical supply means (not shown) located outside the housing 26.
  • a device 48 for guiding the radially inner end of the spark plug 44 is fixed outside the chamber 10 on the outer wall 16, around the orifice 46 to compensate for the relative displacements between the outer wall 16. of the chamber and the spark plug 44 carried by the casing 26 during the operation of the turbomachine. These relative displacements mainly take place in the longitudinal direction, that is to say substantially parallel to the axis 38 of the chamber 10.
  • a device 48 'for guiding the head 36 of the injector is also carried by each injection system 37 mounted in an orifice 30 of the wall 18 of the chamber, to compensate for the relative displacements between the chamber and the injector which mainly take place radially with respect to the axis 38.
  • the guiding device 48 (48 '), better visible in figure 2 , comprises a ring 50 traversed axially by the spark plug 44 (or the head 36 of the injector) and mounted inside one end of a coaxial sleeve 52, the other end of which is fixed by brazing, welding or analogous on the outer wall 16 of the chamber, around the orifice 46 for passage of the spark plug (or fixed on the injection system 37 carried by the wall 18 of the chamber).
  • the ring 50 comprises a cylindrical portion 54 whose inner surface 56 surrounds with a slight clearance the spark plug 44 (or the head 36 of the injector).
  • This cylindrical portion 54 is connected at one end to an outwardly flared frustoconical portion 58 which serves to guide the spark plug (or head) when mounted in the device, and has at its other end an annular flange 60 which extends radially outwards with respect to the axis of the ring 50 and which is guided in an internal annular groove 62 of the sleeve 52.
  • the bushing 52 comprises two coaxial annular pieces 64, 66 which are fixed by soldering or welding one on the other and which define between them the annular groove 62 for guiding the outer flange 60 of the ring 50.
  • the sleeve 52 comprises a first annular piece 64 with a substantially S or Z-shaped section and a second flat annular piece 66 formed by a washer.
  • the first piece 64 comprises a cylindrical wall 68 which is welded or brazed at one end to the wall 16 (or to the injection system 37) and which is connected at its other end to a radial wall 70 defining an inner annular surface 72 the groove 62.
  • the radial wall 70 of the part 64 is connected at its outer periphery to a cylindrical rim 74 extending on the opposite side to the cylindrical wall 68 and on which is applied and welded or brazed the periphery of the washer 66 of the socket.
  • This washer 66 extends substantially radially with respect to the axis of the bushing and defines another internal annular surface 76 of the groove, this surface 76 being parallel to the surface 72 defined by the first part 64 of the bushing.
  • the annular surfaces 72, 76 guide the outer flange 60 of the ring in a radial plane or transverse to the axis of the sleeve.
  • the outer diameter of the annular rim 60 of the ring 50 is smaller than the internal diameter of the cylindrical rim 74 of the sleeve 52 and the outer diameter of the cylindrical portion 54 of the ring is smaller than the inner diameter of the washer 66 to allow displacements of the flange 60 of the ring in the groove 62 in a transverse plane.
  • the axial dimension or thickness of the outer flange 60 of the ring is also smaller than the axial dimension of the groove 62 of the sleeve to allow angular offsets between the axes of the ring 50 and the sleeve 52.
  • material 78 melts into the groove 62 of the sleeve and locally clog the throat on at least a portion of its periphery, which results in a decrease in the travel of the ring 50 in the transverse direction in the groove.
  • the invention overcomes this problem by welding or brazing the washer 66 and the sleeve piece 64 into circumferential zones which are spaced from each other and which are remote from the preferred direction of displacement of the rim of the ring during operation.
  • the washer 66 is fixed on the piece 64 by four zones 80 of solder or solder regularly distributed around the axis of the sleeve. These weld zones 80 may each be formed by one or more weld points or by a weld bead extending over a small angular extent around the axis of the bushing (for example of the order of about 20 °).
  • the welding zones 80 are diametrically opposite two by two with respect to the axis of the bushing. Two diametrically opposite welding zones 80 are aligned on an axis P1 (or P2) perpendicular to the axis of the bushing. According to the invention, the axes P1 and P2 are shifted, by 45 ° in the example represented in the clockwise and counterclockwise direction, with respect to the preferred direction X1, X2 relative displacement of the ring.
  • the preferred direction of relative displacement of the ring is the longitudinal direction along the axis 38, the displacements of the ring taking place in this direction upstream (X1) or downstream (X2).
  • the preferred guide direction of the ring is the radial direction relative to the axis 38, the displacements of the ring taking place in this direction towards the outside (X1) or inward (X2).
  • the shape of the washer 66 has been optimized to reduce its mass.
  • the washer 66 has an outer contour of substantially square shape whose vertices are applied and welded at the zones 80 on the cylindrical rim 74 of the part 64 of the sleeve.
  • the edges of the square outer contour of the washer 66 are not resting on this cylindrical rim 74 and are spaced from this rim radially inwardly so as to define ventilation air passage spaces between the washer 66 and the cylindrical flange 74 of the piece 64.
  • the washer 166 is fixed on the outer rim 174 by two diametrically opposed zones 180 of solder or solder which each extend over an angular extent of about 40 °. According to the invention, these welding zones 180 are offset with respect to the direction X1, X2 privileged displacement of the ring.
  • This direction X1, X2 can be the direction longitudinal in the case of guiding a spark plug 44, or the radial direction in the case of guiding the head 36 of an injector.
  • the welding zones 180 are aligned on an axis P3 which is substantially perpendicular to this preferred direction X1, X2.
  • the washer 166 here has an oval or oblong shape whose vertices corresponding to the ends of smaller radius of curvature are brazed or welded to the cylindrical flange 174 of the part 164.
  • the side parts of the washer 166 corresponding to the ends of larger radius bending are spaced apart and located radially recessed inwardly of the cylindrical rim 174 of the sleeve, so as to create air passage spaces between the washer 166 and the flange 174.
  • the ring 50, 150, the piece 64, 164 and the washer 66, 166 of the device are for example made of cobalt-based alloy.

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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)
EP08167792.4A 2007-12-14 2008-10-29 Vorrichtung zum Lenken eines Elements in die Öffnung einer Brennkammerwand eines Turbinentriebwerks Active EP2071241B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708701A FR2925147B1 (fr) 2007-12-14 2007-12-14 Dispositif de guidage d'un element dans un orifice d'une paroi de chambre de combustion de turbomachine

Publications (2)

Publication Number Publication Date
EP2071241A1 true EP2071241A1 (de) 2009-06-17
EP2071241B1 EP2071241B1 (de) 2018-12-05

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Family Applications (1)

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EP08167792.4A Active EP2071241B1 (de) 2007-12-14 2008-10-29 Vorrichtung zum Lenken eines Elements in die Öffnung einer Brennkammerwand eines Turbinentriebwerks

Country Status (6)

Country Link
US (1) US8261556B2 (de)
EP (1) EP2071241B1 (de)
JP (1) JP2009186168A (de)
CA (1) CA2647145C (de)
FR (1) FR2925147B1 (de)
RU (1) RU2490547C2 (de)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2952703A1 (fr) * 2009-11-19 2011-05-20 Snecma Guide d'une bougie d'allumage dans une chambre de combustion d'une turbomachine
FR2952700A1 (fr) * 2009-11-18 2011-05-20 Snecma Guidage d'une bougie dans une chambre de combustion de turbomachine
FR2957975A1 (fr) * 2010-03-24 2011-09-30 Snecma Dispositif de positionnement d’une bougie d’allumage
FR2958372A1 (fr) * 2010-03-30 2011-10-07 Snecma Chambre de combustion de turbomachine.
FR3042588A1 (fr) * 2015-10-16 2017-04-21 Snecma Dispositif d'injection pour une chambre de combustion d'une turbomachine

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6610839B1 (en) 1997-08-14 2003-08-26 Geron Corporation Promoter for telomerase reverse transcriptase
EP2249003B1 (de) * 2008-02-27 2016-11-02 Mitsubishi Hitachi Power Systems, Ltd. Gasturbine
FR2953908A1 (fr) * 2009-12-16 2011-06-17 Snecma Guidage d'une bougie dans une chambre de combustion de turbomachine
FR2986856B1 (fr) * 2012-02-15 2018-05-04 Safran Aircraft Engines Dispositif d'injection d'air et de carburant pour une chambre de combustion d'une turbomachine
WO2014104901A1 (en) * 2012-12-28 2014-07-03 General Electric Company Methods of reinforcing combustor aperture and related combustor
WO2014168654A1 (en) 2013-03-14 2014-10-16 Rolls-Royce Corporation Inverted cap igniter tube
US9989254B2 (en) * 2013-06-03 2018-06-05 General Electric Company Combustor leakage control system
US9651261B2 (en) * 2014-06-25 2017-05-16 Siemens Energy, Inc. Combustion turbine engine combustor basket igniter port alignment verification tool and method for validating igniter alignment
US20170176004A1 (en) * 2015-12-18 2017-06-22 Pratt & Whitney Canada Corp. Combustor floating collar assembly
GB2548585B (en) * 2016-03-22 2020-05-27 Rolls Royce Plc A combustion chamber assembly
GB201804656D0 (en) 2018-03-23 2018-05-09 Rolls Royce Plc An igniter seal arrangement for a combustion chamber
FR3083264B1 (fr) * 2018-06-29 2021-06-18 Safran Aircraft Engines Dispositif de guidage dans une chambre de combustion
FR3109430B1 (fr) * 2020-04-17 2022-12-02 Safran Aircraft Engines Bougie pour chambre de combustion monobloc

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4216651A (en) * 1977-05-11 1980-08-12 Lucas Industries Limited Sealing arrangement for use in a combustion assembly
EP1342954A1 (de) 2002-03-04 2003-09-10 General Electric Company Vorrichtung zur Positionierung eines Zünders an einer Gasturbinenbrennkammerwand
US20060042268A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
US20060042269A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Gas turbine floating collar
EP1770332A1 (de) 2005-09-29 2007-04-04 Snecma Vorrichtung zur Führung einer Einrichtung in eine Öffnung einer Gasturbinenbrennkammerwand
US20080016874A1 (en) * 2004-08-24 2008-01-24 Lorin Markarian Gas turbine floating collar arrangement

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5117624A (en) * 1990-09-17 1992-06-02 General Electric Company Fuel injector nozzle support
RU2160416C2 (ru) * 1999-12-01 2000-12-10 ООО "Самаратрансгаз" АО "ГАЗПРОМ" Камера сгорания газотурбинного двигателя
US6557350B2 (en) * 2001-05-17 2003-05-06 General Electric Company Method and apparatus for cooling gas turbine engine igniter tubes
FR2856466B1 (fr) * 2003-06-20 2005-08-26 Snecma Moteurs Dispositif d'etancheite de bougie non soude sur la paroi de chambre
US7104066B2 (en) * 2003-08-19 2006-09-12 General Electric Company Combuster swirler assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4216651A (en) * 1977-05-11 1980-08-12 Lucas Industries Limited Sealing arrangement for use in a combustion assembly
EP1342954A1 (de) 2002-03-04 2003-09-10 General Electric Company Vorrichtung zur Positionierung eines Zünders an einer Gasturbinenbrennkammerwand
US20060042268A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
US20060042269A1 (en) * 2004-08-24 2006-03-02 Pratt & Whitney Canada Corp. Gas turbine floating collar
US20080016874A1 (en) * 2004-08-24 2008-01-24 Lorin Markarian Gas turbine floating collar arrangement
EP1770332A1 (de) 2005-09-29 2007-04-04 Snecma Vorrichtung zur Führung einer Einrichtung in eine Öffnung einer Gasturbinenbrennkammerwand

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2952700A1 (fr) * 2009-11-18 2011-05-20 Snecma Guidage d'une bougie dans une chambre de combustion de turbomachine
FR2952703A1 (fr) * 2009-11-19 2011-05-20 Snecma Guide d'une bougie d'allumage dans une chambre de combustion d'une turbomachine
US8875484B2 (en) 2009-11-19 2014-11-04 Snecma Guide for an ignition plug in a turbomachine combustion chamber
FR2957975A1 (fr) * 2010-03-24 2011-09-30 Snecma Dispositif de positionnement d’une bougie d’allumage
FR2958372A1 (fr) * 2010-03-30 2011-10-07 Snecma Chambre de combustion de turbomachine.
FR3042588A1 (fr) * 2015-10-16 2017-04-21 Snecma Dispositif d'injection pour une chambre de combustion d'une turbomachine

Also Published As

Publication number Publication date
CA2647145C (fr) 2016-08-16
RU2490547C2 (ru) 2013-08-20
US20090151361A1 (en) 2009-06-18
JP2009186168A (ja) 2009-08-20
EP2071241B1 (de) 2018-12-05
FR2925147A1 (fr) 2009-06-19
RU2008149166A (ru) 2010-06-20
CA2647145A1 (fr) 2009-06-14
FR2925147B1 (fr) 2012-07-13
US8261556B2 (en) 2012-09-11

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