EP0248731A1 - Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen - Google Patents

Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen Download PDF

Info

Publication number
EP0248731A1
EP0248731A1 EP87401235A EP87401235A EP0248731A1 EP 0248731 A1 EP0248731 A1 EP 0248731A1 EP 87401235 A EP87401235 A EP 87401235A EP 87401235 A EP87401235 A EP 87401235A EP 0248731 A1 EP0248731 A1 EP 0248731A1
Authority
EP
European Patent Office
Prior art keywords
wall
hot
cold
combustion chamber
orifices
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
EP87401235A
Other languages
English (en)
French (fr)
Other versions
EP0248731B1 (de
Inventor
Gérard Yves Georges Barbier
Gérard Joseph Pascal Bayle-Laboure
Michel André Albert Desaulty
François Duchene
Pascal Maurice Trouillot
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0248731A1 publication Critical patent/EP0248731A1/de
Application granted granted Critical
Publication of EP0248731B1 publication Critical patent/EP0248731B1/de
Expired legal-status Critical Current

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
    • F23R3/04—Air inlet arrangements
    • F23R3/045—Air inlet arrangements using pipes
    • 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
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to combustion chambers and more particularly to double-walled chambers, in particular for turbomachines comprising at least one outer wall, known as a cold wall, formed of several mechanically welded ferrules and intended to ensure the mechanical rigidity of the combustion chamber. , and comprising at least one interior wall, known as the hot wall intended to ensure the thermal resistance of the chamber, formed of several successive ferrules assembled together and on the cold wall so as to leave free between the two walls a cooling space allowing a expansion of the hot wall; the chamber also comprising mixing orifices passing through the two walls to allow the introduction of primary combustion and dilution air inside the chamber.
  • Cooling uses the thermal shield effect provided by secondary air inlets creating along the internal surface of the wall a parietal layer avoiding direct contact between the wall and combustion gases. This layer which dilutes as it travels from upstream to downstream must be renewed by means of air inlets successively distributed in the length of the chamber.
  • US Pat. No. 4,303,941 provides an interior wall, of which stepped hot rings are fixed with radial clearance by screws on the cold wall, while tongues integral with the external face of the hot rings ensure the guiding of the convection air and limit the radial clearance.
  • these tabs useful for channeling the convection air, create significant wakes in the parietal film formed at the outlet of the hot shell, which disturbs the effectiveness of this film.
  • the dilution air inlet orifices placed directly at the outlet of the film also disturb the latter.
  • Patent FR 2 023 415 provides a combustion chamber with double walls, the internal rings of the hot wall being stepped and fixed by their upstream edge, while the downstream comprises pads for limiting the expansion play of the ring.
  • One annoyance presented by this type of chamber which uses the principle of cooling by co-current convection and by parietal film is to present a film thickness which is not completely controlled as a function of the expansion of the hot wall.
  • Another drawback lies in the fact that, as in the previous device, the downstream clearance limitation pads introduce wakes in the parietal film, wakes detrimental to the regularity and efficiency of the latter.
  • Patent FR 2 422 035 for its part, provides for limiting the disturbance of the parietal film, caused by the dilution air inlet holes by leaving a free space between the hot shell and the tubular dilution hole and by having a downstream lip at the inner end of the dilution tube in order to restore downstream the film which had been interrupted by the obstacle constituted by the tube.
  • the object of the present invention is to produce a double-walled combustion chamber which allows better coupling of impact, multi-perforation, convection and film cooling and a significant reduction in the flow rates allocated to cooling.
  • Another important object of the invention is to best control the formation and optimization of the shape of the parietal cooling films by controlling the respective positioning of the upstream part of each hot shell and of the downstream tongue of the previous hot shell. , depending on the expansion of the hot ferrules during the operation of the combustion chamber.
  • the invention aims to simplify the fixing of the ferrules of the hot wall by allowing their floating fixing on the cold wall by means of a particular type of mixing orifices.
  • the invention therefore relates to a double-walled combustion chamber, as defined above and such that the mixing orifices are of the hole-nozzle type comprising a first cylindrical element comprising in combination successively from the outside to the inside from the chamber a flare flared outwards in quarter-round, the flange internally forming an air inlet nozzle and externally comprising a shoulder by which it can rest on the external face of the cold wall without being integral therewith , a first outer cylindrical bearing coming to be housed in a circular recess of the cold wall and a second circular bearing on which is concentrically mounted a second ring-shaped element comprising a collar and a tubular bearing arranged inside one. recess in the hot wall, against which the tubular seat is folded back on the fallen edge and such that the ring is welded to the second cylindrical seat of the prem ier element forming a nozzle.
  • the mixing orifices are of the hole-nozzle type comprising a first cylindrical element comprising in combination successively from the outside to the inside from the
  • the first cylindrical bearing surface of the element of the mixing orifice forming hole-nozzle has a length greater than the thickness of the hot wall so that the mixing orifice, integral with the hot wall, or mounted floating on the cold wall of the combustion chamber.
  • each ferrule constituting the hot wall has at its downstream a curved flange allowing its downstream attachment in an annular groove of the cold wall and each of said ferrules is mounted floating upstream relative to the hot wall by means of the only mixing orifices constituting, in addition to their air inlet function, means for radial and axial positioning of the ferrules of the hot wall on the cold wall and means for controlling the expansion clearance of the hot wall.
  • the wall structure can be organized so that the upstream edge of each ferrule of the hot wall cooperates with a tongue downstream of the ferrule located immediately upstream to form the cooling film and that the slit height of the cooling films is controlled during operation by the positioning of said ferrule by means of its mixing orifices and by the inclination of the downstream tongue of the ferrule located immediately upstream, due to the positioning of said upstream ferrule by its own mixing orifices.
  • a low pressure compressor 1 compresses the air drawn at the engine inlet; the flow leaving the low pressure compressor is separated into a primary flow and a secondary flow, the primary flow is compressed again by a high pressure compressor 2 before being mixed with pressurized fuel in an annular combustion chamber 3 such than that of the invention where the mixture is burned to provide combustion energy to the engine.
  • the gases from chamber 3 drive a turbine 4 which, itself drives compressors 1 and 2.
  • the gases are accelerated.
  • the hot flow is then mixed with the cold flow, which at the outlet of the low pressure compressor has flowed into an annular stream formed by the intermediate casing 5 surrounding the hot flow and the external casing 6 of the engine.
  • the gases are then ejected, either dry, or by undergoing a reheating in a post-combustion device 7.
  • FIG. 2 shows in longitudinal section the detail A of FIG. 1.
  • the combustion chamber 3 is an annular double-walled chamber formed by a double internal wall 8, that is to say the one closest to the axis of symmetry of the engine and a double external wall 9 most radially distant from the axis of symmetry of the engine.
  • Each of these double walls 8 and 9 includes an inner wall to the chamber, subjected to combustion gases and called hot wall or hot skin and an outer wall subjected to the flow of primary air cooler than the combustion gases.
  • the cold walls, internal and external, of the chamber are each formed by four ferrules (respectively from upstream to downstream 10, 11, 12, 13; 110, 111, 112, 113) welded together by means of parts massive machined annulars (respectively 14, 15, 16; 114, 115, 116) serving for the attachment of the hot walls and, as regards the piece 114 for the formation of a parietal cooling film.
  • the ferrule 21 has downstream a groove 23 allowing its attachment to a flange 24 of the film 15 of the cold wall while the ferrule 22 has two flanges 25 and 26 which are hung one, 25, on an annular groove of the part machined 16 from the cold wall and the other 26 downstream in a second groove 27 downstream from the internal cold wall.
  • the ferrules 121 and 122 are similarly hung downstream by flanges 123, 125 and 126 in annular grooves of the machined parts 115, 116 and of the downstream 127 of the external wall.
  • the ferrules 21, 22, 121, 122 have their upstream surfaces mounted floating and are positioned on the cold walls only by the mixing orifices 29, 30 intended for supplying combustion air to the primary zone and the zone of dilution.
  • Each mixing orifice 29 or 30 comprises a first cylindrical element 31 having a central bore 32 flared in quarter round 33 towards the outside and forming the mixing air inlet hole-nozzle.
  • the flange formed by the flared part delimits a shoulder 34 which can be supported on the external face of the cold wall 11 or 12, 111 or 112 while the first external cylindrical bearing 35 penetrates inside two aligned circular recesses 36 , 37 cold and hot skin.
  • a second cylindrical bearing surface 38 of smaller diameter extends the first bearing surface 35.
  • a ring 39 comprising a collar 40 and a tubular bearing surface 41 passing through the orifice 37.
  • the collar 40 is disposed between the hot and cold skins resting against the end of the bearing surface 35, while the end 42 of the bearing surface 41 is folded back on the fallen edge onto the hot skin 21, 22 or 121, 122 once the latter has been assembled.
  • the ring 39 is secured to the nozzle hole 31 by a weld bead deposited between the fallen edge 42 and the seat 38.
  • the thickness of the collar 40 determines the minimum interval between the hot and cold skins while the length of the staff 35 added to the thickness of the collar determines the maximum interval.
  • the cold interval hF between walls is fixed by the thickness of the collar and the hot wall by its expansion during operation tends to deviate from the cold wall and it is then the cumulative height of the staff 3 . 5 and the collar 40 which fixes the maximum expansion interval hC when hot.
  • the desired height when cold h F can be fixed between the hot and cold skin of the internal wall and the maximum limit of expansion of the hot skin as well as for the external wall, the minimum distance between walls can be set at the desired hC value when hot.
  • the cooling of the walls of the combustion chamber is achieved by combining a convection flow external to the cold walls, by multi-perforations of the cold walls 10, 11, 12, 13, 110, 111, 112, 113; by convection against the current between cold skins (resp. 11, 12, 13, 111, 112, 113) and hot skins (resp. 21, 22, 121, 122) and by parietal film along the hot ferrules 21 , 22, 121, 122.
  • the machined parts 19, 114 of the primary ferrules have downstream tongues 44, 45 which cooperate with the upstream edge of the ferrules 21 and 121 to form the parietal film for cooling the primary ferrules.
  • the downstream edge of the primary hot shrouds 21, 121 has tongues 46, 47 which cooperate with the upstream edge of the hot dilution shrouds in order to produce the cooling film for said hot dilution shrouds.
  • the radial positioning of the hot ferrules on the cold walls by the mixing orifices 29.30 allows optimum cooling efficiency by the parietal films to be obtained because it allows the shape of the flow-speed cavity to be controlled as well that the slit height of the film, this being able to be better controlled as the thickness of the downstream tabs 44, 45, 46, 47, produced in massive parts, can be calculated so that the low expansion of the tongue does not change substantially the slit height of the film.
  • the fixing of the hot ferrules on the cold walls by the mixing orifices also makes it possible to ensure the circumferential homogeneity of the flow by avoiding the wake phenomena, known in the prior devices and which were due to the bridges for limiting expansion.
  • the method of mounting hot skins on cold skins makes it possible to achieve a better compromise between the various cooling modes used while allowing the production of a double-walled chamber of low weight and technology simple and easy to assemble (or disassemble), which makes its application particularly useful in turbojets for which high performance and high reliability are sought.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Spray-Type Burners (AREA)
EP87401235A 1986-06-04 1987-06-03 Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen Expired EP0248731B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8608015 1986-06-04
FR8608015A FR2599821B1 (fr) 1986-06-04 1986-06-04 Chambre de combustion pour turbomachines a orifices de melange assurant le positionnement de la paroi chaude sur la paroi froide

Publications (2)

Publication Number Publication Date
EP0248731A1 true EP0248731A1 (de) 1987-12-09
EP0248731B1 EP0248731B1 (de) 1989-01-11

Family

ID=9335972

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401235A Expired EP0248731B1 (de) 1986-06-04 1987-06-03 Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen

Country Status (4)

Country Link
US (1) US4805397A (de)
EP (1) EP0248731B1 (de)
DE (1) DE3760036D1 (de)
FR (1) FR2599821B1 (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321320A1 (de) * 1987-12-16 1989-06-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbinenbrennkammer mit einem doppelwandigen Verbindungselement
EP0363624A1 (de) * 1988-10-07 1990-04-18 Westinghouse Electric Corporation Brennkammer einer Gasturbine mit Luftrohren
EP0493304A1 (de) * 1990-12-24 1992-07-01 United Technologies Corporation Integriertes Verbinder- und Luftrohr für eine Brennkammer einer Gasturbine
FR2674317A1 (fr) * 1991-03-20 1992-09-25 Snecma Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
EP0647817A1 (de) * 1993-10-06 1995-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Doppelhäuser einer Brennkammer
EP0694739A1 (de) * 1994-07-27 1996-01-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Doppelwandige Brennkammer
EP0780638A3 (de) * 1995-12-20 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Brennkammer für Gasturbinentriebwerke
FR2970065A1 (fr) * 2011-01-03 2012-07-06 Gen Electric Dispositif de combustion pour moteur a turbine
WO2015031816A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Gas turbine engine wall assembly with support shell contour regions
WO2015117137A1 (en) 2014-02-03 2015-08-06 United Technologies Corporation Film cooling a combustor wall of a turbine engine

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5431517A (en) * 1994-01-12 1995-07-11 General Electric Company Apparatus and method for securing a bracket to a fixed member
JPH09195799A (ja) * 1996-01-17 1997-07-29 Mitsubishi Heavy Ind Ltd 燃焼器のスプリングシール装置
US6499993B2 (en) * 2000-05-25 2002-12-31 General Electric Company External dilution air tuning for dry low NOX combustors and methods therefor
US6334310B1 (en) * 2000-06-02 2002-01-01 General Electric Company Fracture resistant support structure for a hula seal in a turbine combustor and related method
EP1381811A1 (de) * 2001-04-27 2004-01-21 Siemens Aktiengesellschaft Brennkammer, insbesondere einer gasturbine
EP1312865A1 (de) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Ringbrennkammer für eine Gasturbine
US8281600B2 (en) * 2007-01-09 2012-10-09 General Electric Company Thimble, sleeve, and method for cooling a combustor assembly
US8387396B2 (en) 2007-01-09 2013-03-05 General Electric Company Airfoil, sleeve, and method for assembling a combustor assembly
US8616004B2 (en) * 2007-11-29 2013-12-31 Honeywell International Inc. Quench jet arrangement for annular rich-quench-lean gas turbine combustors
US8171740B2 (en) * 2009-02-27 2012-05-08 Honeywell International Inc. Annular rich-quench-lean gas turbine combustors with plunged holes
US8141365B2 (en) * 2009-02-27 2012-03-27 Honeywell International Inc. Plunged hole arrangement for annular rich-quench-lean gas turbine combustors
US9010123B2 (en) * 2010-07-26 2015-04-21 Honeywell International Inc. Combustors with quench inserts
US9249679B2 (en) * 2011-03-15 2016-02-02 General Electric Company Impingement sleeve and methods for designing and forming impingement sleeve
JP5821550B2 (ja) 2011-11-10 2015-11-24 株式会社Ihi 燃焼器ライナ
US20130298564A1 (en) * 2012-05-14 2013-11-14 General Electric Company Cooling system and method for turbine system
US8695352B2 (en) * 2012-07-12 2014-04-15 Solar Turbines Inc. Baffle assembly for bleed air system of gas turbine engine
DE102012022259A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
US20140190171A1 (en) * 2013-01-10 2014-07-10 Honeywell International Inc. Combustors with hybrid walled liners
US20150354819A1 (en) 2013-01-16 2015-12-10 United Technologies Corporation Combustor Cooled Quench Zone Array
EP3039346B1 (de) * 2013-08-30 2022-09-14 Raytheon Technologies Corporation Konturierte verdünnungsdurchgänge für eine gasturbinenbrennkammer
US10816201B2 (en) * 2013-09-13 2020-10-27 Raytheon Technologies Corporation Sealed combustor liner panel for a gas turbine engine
WO2015147938A2 (en) * 2014-01-03 2015-10-01 United Technologies Corporation A cooled grommet for a combustor wall assembly
US10112557B2 (en) * 2014-04-03 2018-10-30 United Technologies Corporation Thermally compliant grommet assembly
GB201514390D0 (en) 2015-08-13 2015-09-30 Rolls Royce Plc A combustion chamber and a combustion chamber segment
EP3315864B1 (de) * 2016-10-26 2021-07-28 Raytheon Technologies Corporation Gegossene brennkammerauskleidungsplatte mit abgerundeter verdünnungsdurchgangshülse für eine gasturbinenmotorbrennkammer
US10697372B2 (en) * 2017-04-05 2020-06-30 General Electric Company Turbine engine conduit interface
GB201720254D0 (en) * 2017-12-05 2018-01-17 Rolls Royce Plc A combustion chamber arrangement
US10816203B2 (en) * 2017-12-11 2020-10-27 General Electric Company Thimble assemblies for introducing a cross-flow into a secondary combustion zone
US11022308B2 (en) 2018-05-31 2021-06-01 Honeywell International Inc. Double wall combustors with strain isolated inserts
US10808930B2 (en) * 2018-06-28 2020-10-20 Raytheon Technologies Corporation Combustor shell attachment

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1195188A (fr) * 1958-07-21 1959-11-16 Gen Electric Manchon intérieur de chambre de combustion pour les moteurs à turbine à gaz
US3496722A (en) * 1968-08-02 1970-02-24 Garrett Corp Combustion chamber flame tube construction
FR2422035A1 (fr) * 1978-04-04 1979-11-02 Gen Electric Dispositif de combustion refroidi par film d'air
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
FR2567250A1 (fr) * 1984-07-06 1986-01-10 Gen Electric Chambre de combustion pour moteur a turbine a gaz

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1059199A (en) * 1965-10-20 1967-02-15 Rolls Royce Flame tube
US3899876A (en) * 1968-11-15 1975-08-19 Secr Defence Brit Flame tube for a gas turbine combustion equipment
US3545202A (en) * 1969-04-02 1970-12-08 United Aircraft Corp Wall structure and combustion holes for a gas turbine engine
US4614082A (en) * 1972-12-19 1986-09-30 General Electric Company Combustion chamber construction
US4555901A (en) * 1972-12-19 1985-12-03 General Electric Company Combustion chamber construction
US4302941A (en) * 1980-04-02 1981-12-01 United Technologies Corporation Combuster liner construction for gas turbine engine
US4512159A (en) * 1984-04-02 1985-04-23 United Technologies Corporation Clip attachment
US4748806A (en) * 1985-07-03 1988-06-07 United Technologies Corporation Attachment means
DE3535443C1 (de) * 1985-10-04 1986-11-20 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Brennkammer fuer ein Gasturbinentriebwerk,insbesondere Ringbrennkammer,mit mindestes einer Luftzufuhrbuchse

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1195188A (fr) * 1958-07-21 1959-11-16 Gen Electric Manchon intérieur de chambre de combustion pour les moteurs à turbine à gaz
US3496722A (en) * 1968-08-02 1970-02-24 Garrett Corp Combustion chamber flame tube construction
US4480436A (en) * 1972-12-19 1984-11-06 General Electric Company Combustion chamber construction
US4184326A (en) * 1975-12-05 1980-01-22 United Technologies Corporation Louver construction for liner of gas turbine engine combustor
FR2422035A1 (fr) * 1978-04-04 1979-11-02 Gen Electric Dispositif de combustion refroidi par film d'air
FR2567250A1 (fr) * 1984-07-06 1986-01-10 Gen Electric Chambre de combustion pour moteur a turbine a gaz

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0321320A1 (de) * 1987-12-16 1989-06-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbinenbrennkammer mit einem doppelwandigen Verbindungselement
FR2624953A1 (fr) * 1987-12-16 1989-06-23 Snecma Chambre de combustion, pour turbomachines, possedant un convergent a doubles parois
US4901522A (en) * 1987-12-16 1990-02-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Turbojet engine combustion chamber with a double wall converging zone
EP0363624A1 (de) * 1988-10-07 1990-04-18 Westinghouse Electric Corporation Brennkammer einer Gasturbine mit Luftrohren
EP0493304A1 (de) * 1990-12-24 1992-07-01 United Technologies Corporation Integriertes Verbinder- und Luftrohr für eine Brennkammer einer Gasturbine
FR2674317A1 (fr) * 1991-03-20 1992-09-25 Snecma Chambre de combustion de turbomachine comportant un reglage du debit de comburant.
EP0506516A1 (de) * 1991-03-20 1992-09-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verbrennungsluftzufuhreinrichtung für eine Brennkammer einer Turbomaschine
FR2710968A1 (fr) * 1993-10-06 1995-04-14 Snecma Chambre de combustion à double paroi.
EP0647817A1 (de) * 1993-10-06 1995-04-12 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Doppelhäuser einer Brennkammer
US5499499A (en) * 1993-10-06 1996-03-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Cladded combustion chamber construction
EP0694739A1 (de) * 1994-07-27 1996-01-31 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Doppelwandige Brennkammer
FR2723177A1 (fr) * 1994-07-27 1996-02-02 Snecma Sa Chambre de combustion comportant une double paroi
EP0780638A3 (de) * 1995-12-20 1998-06-10 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Brennkammer für Gasturbinentriebwerke
FR2970065A1 (fr) * 2011-01-03 2012-07-06 Gen Electric Dispositif de combustion pour moteur a turbine
WO2015031816A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Gas turbine engine wall assembly with support shell contour regions
EP3039347A1 (de) * 2013-08-30 2016-07-06 United Technologies Corporation Wandanordnung für gasturbinenmotor mit stützschalenkonturregionen
EP3039347A4 (de) * 2013-08-30 2016-09-21 United Technologies Corp Wandanordnung für gasturbinenmotor mit stützschalenkonturregionen
WO2015117137A1 (en) 2014-02-03 2015-08-06 United Technologies Corporation Film cooling a combustor wall of a turbine engine
EP3102883A4 (de) * 2014-02-03 2017-03-01 United Technologies Corporation Filmkühlung einer brennkammerwand eines turbinenmotors

Also Published As

Publication number Publication date
FR2599821A1 (fr) 1987-12-11
US4805397A (en) 1989-02-21
EP0248731B1 (de) 1989-01-11
FR2599821B1 (fr) 1988-09-02
DE3760036D1 (en) 1989-02-16

Similar Documents

Publication Publication Date Title
EP0248731B1 (de) Gasturbinenbrennkammer mit Mischöffnungen, die eine heisse Wand gegenüber einer kühlen Wand Festlegen
EP1818613B1 (de) Brennkammer eines Turbotriebwerks
EP2771618B1 (de) Ringförmige brennkammerwand mit verbesserter kühlung an den primär- und/oder verdünnungsluftlöchern
CA2782661C (fr) Chambre de combustion pour turbomachine
CA2987526C (fr) Paroi annulaire de chambre de combustion a refroidissement optimise
CA2641989A1 (fr) Chambre de combustion a dilution optimisee et turbomachine en etant munie
FR2639678A1 (fr) Compartiment, notamment a chicanes, du type resonateur de helmholtz attenuateur de bruits, chemisage acoustique notamment annulaire, pour un canal notamment annulaire d'un moteur a turbines a gaz, et moteur equipe de ces dispositifs
CA2642059C (fr) Paroi de chambre de combustion a dilution et refroidissement optimises, chambre de combustion et turbomachine en etant munies
CA2925565C (fr) Chambre de combustion de turbomachine pourvue de moyens de deflection d'air pour reduire le sillage cree par une bougie d'allumage
FR3021351B1 (fr) Paroi de turbomachine comportant une partie au moins d'orifices de refroidissement obtures
FR2873408A1 (fr) Turboreacteur avec un ecran de protection de la rampe de carburant d'un anneau bruleur, l'anneau bruleur et l'ecran de protection
FR3094034A1 (fr) Chemise tubulaire de ventilation pour un distributeur de turbomachine
EP4136327B1 (de) Kühlvorrichtung für turbinengehäuse
EP4179256B1 (de) Ringbrennkammer für eine flugzeugturbomaschine
EP3771862A1 (de) Kraftstoffeinspritzernase für turbomaschine, die eine innen durch einen zapfen begrenzte kammer zur inbetriebsetzung der drehbewegung umfasst
FR3109430A1 (fr) Bougie pour chambre de combustion monobloc
FR3065024A1 (fr) Anneau de turbine de turbomachine et procede de fabrication d'un tel anneau
FR3071908A1 (fr) Chambre de combustion de turbomachine a geometrie de cheminee fixe
FR3068732A1 (fr) Dispositif de refroidissement
WO2022223914A1 (fr) Cone de diffusion pour partie arriere de turboreacteur integrant un anneau accroche-flamme en bord de fuite
EP4327021A1 (de) Flammenhalter für eine nachbrenner-turbodüsenvorrichtung mit drei verzweigten armen
FR3108966A1 (fr) Chambre de combustion comportant une paroi comprenant un conduit de refroidissement entre une première cloison et une deuxième cloison
FR3122719A1 (fr) Accroche-flammes pour postcombustion de turboréacteur comprenant des bras à bords de fuite dentelés
FR3098569A1 (fr) Paroi annulaire pour chambre de combustion de turbomachine comprenant des trous primaires, des trous de dilution et des orifices de refroidissement inclines
FR3122720A1 (fr) Cône de diffusion pour partie arrière de turboréacteur intégrant un système d'injection d'air et de carburant

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: 19870619

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

17Q First examination report despatched

Effective date: 19880316

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)
REF Corresponds to:

Ref document number: 3760036

Country of ref document: DE

Date of ref document: 19890216

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
REG Reference to a national code

Ref country code: FR

Ref legal event code: CL

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 19940830

Year of fee payment: 8

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Effective date: 19960301

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Ref country code: FR

Ref legal event code: CD

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20050524

Year of fee payment: 19

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20050527

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

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: 20060603

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20060603

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20070228

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: 20060630