EP1717516B1 - Chambre de combustion aisément démontable à performance aérodynamique améliorée - Google Patents

Chambre de combustion aisément démontable à performance aérodynamique améliorée Download PDF

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Publication number
EP1717516B1
EP1717516B1 EP06112766.8A EP06112766A EP1717516B1 EP 1717516 B1 EP1717516 B1 EP 1717516B1 EP 06112766 A EP06112766 A EP 06112766A EP 1717516 B1 EP1717516 B1 EP 1717516B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
tongues
wall
annular
end 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.)
Active
Application number
EP06112766.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1717516A1 (fr
Inventor
Christophe Pieussergues
Pierre Sablayrolles
Laurent Marnas
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
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Safran Aircraft Engines SAS
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Publication date
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Publication of EP1717516A1 publication Critical patent/EP1717516A1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F23R2900/00017—Assembling combustion chamber liners or subparts

Definitions

  • the invention relates to a combustion chamber for a reactor. It relates more particularly to an improvement in the assembly of the different parts of the combustion chamber, with the dual aim of reducing the disturbances of the air flow around it, which may penalize its performance, and to facilitate the maintenance.
  • a known combustion chamber is a divisible assembly of several parts. There is a generally annular outer wall, a generally annular inner wall and a bottom wall extending between said outer and inner walls.
  • the fuel injection means are mounted on said bottom wall of the chamber. They consist of a plurality of injection systems spaced circularly.
  • a fairing defines with said bottom wall of chamber an annular cavity housing these injection means.
  • the combustion chamber thus defined is an axisymmetric assembly which must be as aerodynamic as possible since placed in the air stream.
  • the shroud generally comprises an annular piece called outer cap and an annular piece called inner cap. The various components of the combustion chamber are assembled together removably.
  • the bolting assembly is replaced by a set of welds between said inner and outer walls, the bottom wall of the chamber and the fairing.
  • this type of combustion chamber there are no more screw heads to disturb the flow at the external bypass or at the internal bypass of the combustion chamber.
  • the welds make this combustion chamber difficult to repair because it is necessary at least to cut said chamber according to two circular welds. As these welds are on cones, it is very difficult and expensive to reassemble the chamber after repairing an element thereof.
  • the document EP1265033 A1 discloses all the features of the preamble of claim 1.
  • the invention overcomes this double difficulty.
  • the invention relates to a combustion chamber of a reactor comprising a generally annular outer wall, a generally annular inner wall, a chamber bottom wall extending between said outer and inner walls and on which are mounted means injection molding and a shroud defining with said bottom wall of an annular chamber chamber housing said injection means, said fairing comprising an annular piece said outer cap and an annular piece called inner cap, characterized in that said caps comprise parts internal fasteners projecting into said annular cavity, in that said bottom wall of the chamber comprises corresponding internal fasteners protruding inside said annular cavity and in that the fasteners of said caps. are assembled to the fasteners of said bottom wall of room.
  • the aforementioned internal fasteners are tabs distributed circumferentially or, more generally, ferrules.
  • those of said caps and those of said bottom wall of the chamber are welded.
  • they are welded two by two together at their ends only.
  • a possible disassembly of the components of the combustion chamber can be easily done by grinding the ends of the tongues so as to eliminate the welded areas.
  • fasteners are ferrules
  • said outer cap and said outer wall are assembled circumferentially by welding.
  • the welding can be done singing against singing.
  • the inner wall and the bottom wall of the chamber are secured circumferentially.
  • the assembly can be achieved by riveting or even capping.
  • the weld joining the tongues together is preferably a TIG weld, known per se.
  • a high intensity current passes through a tungsten electrode forming an arc with the parts to be assembled.
  • the metal receiving the arc undergoes a local fusion.
  • the welding is done in a neutral gas environment (argon for example).
  • the tongues carried by the caps are preferably assembled to them by brazing.
  • Each tab is assembled to the cap by means of a filler metal whose melting point is less than the melting point of the materials to be assembled. The assembly is performed without melting the metal of the elements to be assembled. Once brought to the melting temperature, the filler metal enters by capillary attraction between the parts to be assembled.
  • the filler metal is preferably based on nickel for a brazing temperature of the order of 1160 ° C.
  • the inner cap has an annular band in contact enveloping with the end portion of the inner wall.
  • a combustion chamber 11 which consists of the assembly of several annular parts.
  • a combustion chamber 11 which consists of the assembly of several annular parts.
  • the shroud defines with said bottom wall of a chamber annular cavity 20 housing the means injection.
  • injectors 22 circumferentially spaced regularly and mounted on the bottom wall of chamber 14.
  • the invention relates more particularly to the method of assembly between said inner and outer walls, the bottom wall of the chamber and the two caps.
  • the caps 16, 17 comprise tongues 24, 25, respectively, projecting inside the annular cavity 20. These tongues are regularly distributed circumferentially.
  • Each cap has as many tabs 24 or 25 as there are injectors but they are offset circumferentially relative to the injectors for better accessibility in case of disassembly.
  • a tongue 24 or 25 has a curved portion 28 conforming to the shape of the inner face of the cap and a portion 29 curved radially inward, which protrudes into the annular cavity.
  • the bottom wall of the chamber also has tabs 34, 35 projecting into the annular cavity.
  • the chamber bottom wall 14 and the tongues 34, 35 carried by it, inside and outside, are drawn from the same cut and stamped sheet as can be seen on FIG. figure 2 .
  • outer tongues 34 and a series of inner tongues 35 There are a series of outer tongues 34 and a series of inner tongues 35.
  • the outer tongues 34 of the chamber bottom wall and the tongues 24 of the outer cap are equal in number and correspond, each tongue of the cap being applied. by its projecting portion against a corresponding tongue of the chamber bottom wall.
  • the tongues 25 of the inner cap and the inner tongues 35 of the bottom wall of the chamber are equal in number and correspond, each tongue of the inner cap being applied by its projecting portion against the corresponding tongue of the wall of the bedroom background.
  • the tongues of said caps are assembled to the tongues of said bottom wall of the chamber. More particularly, the tongues of said caps and those of said chamber bottom wall are welded in pairs and preferably only at their ends.
  • the solder 40 is preferably of the TIG type.
  • the parts of the tongues 24, 25 secured to the caps 16, 17 are joined thereto by brazing. Because the tongues are bent so as to be placed side by side in pairs and welded only at their ends, it is relatively easy to separate them, for example by grinding said welded ends. . These grinding operations will disassemble the various parts of the combustion chamber for repairs. After these repairs reassembly is possible by re-welding the ends of the slightly shortened tabs 24, 34 and 25, 35.
  • outer cap 16 and said outer wall 12 are joined circumferentially by welding. As shown, the weld 42 is edge-to-edge so that the flow of air outside the combustion chamber is not disturbed.
  • the chamber bottom wall 14 is not attached to said outer part.
  • the inner wall 13 and said bottom wall chamber 14 are secured circumferentially.
  • the two walls are shaped with annular bands 43, 44 in contact. These strips can be secured by riveting or capping.
  • Said inner cap 17 also comprises an annular band 47 in contact enveloping with the annular band of said inner wall. It is not attached to this inner wall. This arrangement does not substantially disturb the flow of air within the vein defined by the inner wall and the inner cap of the combustion chamber. Said inner wall 13 and the inner cap 17 are not secured in their contact zone.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Portable Nailing Machines And Staplers (AREA)
EP06112766.8A 2005-04-28 2006-04-19 Chambre de combustion aisément démontable à performance aérodynamique améliorée Active EP1717516B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0504283A FR2885201B1 (fr) 2005-04-28 2005-04-28 Chambre de combustion aisement demontable a performance aerodynamique amelioree

Publications (2)

Publication Number Publication Date
EP1717516A1 EP1717516A1 (fr) 2006-11-02
EP1717516B1 true EP1717516B1 (fr) 2019-04-03

Family

ID=35500968

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06112766.8A Active EP1717516B1 (fr) 2005-04-28 2006-04-19 Chambre de combustion aisément démontable à performance aérodynamique améliorée

Country Status (7)

Country Link
US (1) US7637111B2 (zh)
EP (1) EP1717516B1 (zh)
JP (1) JP2006307854A (zh)
CN (1) CN1854610A (zh)
CA (1) CA2544957C (zh)
FR (1) FR2885201B1 (zh)
RU (1) RU2411412C2 (zh)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8109098B2 (en) * 2006-05-04 2012-02-07 Siemens Energy, Inc. Combustor liner for gas turbine engine
FR2911668B1 (fr) * 2007-01-18 2009-03-20 Snecma Sa Chambre de combustion d'une turbomachine
FR2911669B1 (fr) 2007-01-23 2011-09-16 Snecma Carenage pour chambre de combustion, chambre de combustion en etant equipee et turboreacteur les comportant.
FR2920525B1 (fr) * 2007-08-31 2014-06-13 Snecma Separateur pour alimentation de l'air de refroidissement d'une turbine
FR2964725B1 (fr) * 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
US8938978B2 (en) * 2011-05-03 2015-01-27 General Electric Company Gas turbine engine combustor with lobed, three dimensional contouring
US8938976B2 (en) * 2011-05-20 2015-01-27 Siemens Energy, Inc. Structural frame for gas turbine combustion cap assembly
FR2976346B1 (fr) * 2011-06-08 2013-07-05 Turbomeca Chambre de combustion annulaire de turbomachine
FR2998038B1 (fr) * 2012-11-09 2017-12-08 Snecma Chambre de combustion pour une turbomachine
DE102015213629A1 (de) * 2015-07-20 2017-01-26 Rolls-Royce Deutschland Ltd & Co Kg Abdeckteil und Brennkammerbaugruppe für eine Gasturbine
US9995175B2 (en) * 2016-06-29 2018-06-12 General Electric Company System and method for gas bearing support of turbine

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265033A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Chambre de combustion munie d'un système de fixation de fond de chambre

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3422620A (en) * 1967-05-04 1969-01-21 Westinghouse Electric Corp Combustion apparatus
US3854285A (en) * 1973-02-26 1974-12-17 Gen Electric Combustor dome assembly
US4411134A (en) * 1981-10-26 1983-10-25 Moir David L Apparatus for the repair and replacement of transition ducts on jet engines and bracket therefor
FR2662784B1 (fr) * 1990-06-05 1992-08-14 Snecma Ensemble d'injection pour turbomachine, comprenant un bol de prevaporisation.
JP2597800B2 (ja) * 1992-06-12 1997-04-09 ゼネラル・エレクトリック・カンパニイ ガスタービンエンジン用燃焼器
DE69930455T2 (de) * 1998-11-12 2006-11-23 Mitsubishi Heavy Industries, Ltd. Gasturbinenbrennkammer
FR2855249B1 (fr) * 2003-05-20 2005-07-08 Snecma Moteurs Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre
US7415826B2 (en) * 2005-07-25 2008-08-26 General Electric Company Free floating mixer assembly for combustor of a gas turbine engine

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265033A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Chambre de combustion munie d'un système de fixation de fond de chambre

Also Published As

Publication number Publication date
CN1854610A (zh) 2006-11-01
JP2006307854A (ja) 2006-11-09
US7637111B2 (en) 2009-12-29
EP1717516A1 (fr) 2006-11-02
CA2544957C (fr) 2014-12-23
CA2544957A1 (fr) 2006-10-28
FR2885201B1 (fr) 2010-09-17
US20060242939A1 (en) 2006-11-02
FR2885201A1 (fr) 2006-11-03
RU2411412C2 (ru) 2011-02-10
RU2006114416A (ru) 2007-11-10

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