EP1816399A1 - Verfahren zur Herstellung einer Brennkammer - Google Patents

Verfahren zur Herstellung einer Brennkammer Download PDF

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Publication number
EP1816399A1
EP1816399A1 EP07101484A EP07101484A EP1816399A1 EP 1816399 A1 EP1816399 A1 EP 1816399A1 EP 07101484 A EP07101484 A EP 07101484A EP 07101484 A EP07101484 A EP 07101484A EP 1816399 A1 EP1816399 A1 EP 1816399A1
Authority
EP
European Patent Office
Prior art keywords
edge
combustion chamber
ferrules
welded
welding
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
EP07101484A
Other languages
English (en)
French (fr)
Other versions
EP1816399B1 (de
Inventor
David Locatelli
Didier Hernandez
Patrick Audin
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 EP1816399A1 publication Critical patent/EP1816399A1/de
Application granted granted Critical
Publication of EP1816399B1 publication Critical patent/EP1816399B1/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
    • F23R3/002—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
    • F23R3/54—Reverse-flow combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2213/00—Burner manufacture specifications
    • 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
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • 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
    • Y10T29/49346—Rocket or jet device making

Definitions

  • the invention relates to a method of manufacturing a combustion chamber by assembling preformed ferrules; it relates more particularly to the type of assembly retained, eliminating any welding by the wheel.
  • the invention is advantageously applied to the manufacture of so-called "return" combustion chambers.
  • the invention also relates to a direct combustion chamber obtained by the implementation of the method and a turbojet engine equipped with such a combustion chamber.
  • a so-called return combustion chamber usually consists of pressed sheets to form ferrules.
  • the ferrules are assembled together.
  • the ferrules often have annular tongues assembled flat by a seam weld.
  • this type of assembly generates thermomechanical stresses and poses accessibility problems if it is desired to perform a laser perforation of the chamber.
  • the invention achieves this goal.
  • the invention relates to a method of manufacturing a combustion chamber consisting essentially of welded ferrules, characterized in that it consists in separately making two subsets of such ferrules by welding edge to edge thereof, by welding at one end of a first subassembly an intermediate connecting ring, having a mounting surface, engaging one end of a second subassembly on that span and welding it to said intermediate ring.
  • the first subassembly mainly consists of external ferrules and the second sub-assembly mainly consists of internal ferrules.
  • the ferrules of each subassembly are assembled by welding edge to edge.
  • a flat-bottomed ferrule constitutes a chamber bottom, carrying the injectors and this chamber bottom is part of one of the subassemblies, before the final weld.
  • one of the subassemblies includes such a chamber bottom and one of the ends of this chamber bottom constitutes the end of said second subassembly intended to be welded to said intermediate ring.
  • any edge-to-edge welding is practiced by adjusting the docking of the two annular parts concerned by means of radial expansion tools which allow to position these parts edge to edge for the purpose of welding.
  • the intermediate connecting ring is a part at least partially machined, adjusted dimensions. It can therefore ensure a centering function at the time of final assembly of the two subassemblies, by orbital welding. This assembly can be done by laser welding or "TIG" welding.
  • intermediate connecting ring comprises or itself constitutes the filler metal required for welding with said second subset.
  • a combustion chamber according to the invention is therefore characterized in that it consists of a plurality of preformed ferrules including a chamber bottom, assembled by edge-to-edge welds with the exception of a junction between two subassemblies. such ferrules, said junction being made with the interposition of an aforementioned intermediate connecting ring.
  • FIG. 3 is a specific orbital weld of the invention making it possible to join two subassemblies of ferrules already welded together
  • FIGS. 1A-1C and FIGS. 2A-2C can be performed in a different order.
  • edge-to-edge welds mentioned with reference to FIGS. 1A-1C and 2A-2C are indicated by arrows.
  • the other end of the external bend is then welded edge to edge under neutral gas at one end of a cylindrical shell 13 forming the outer wall of the combustion chamber.
  • the intermediate connecting ring 14 comprises a cylindrical mounting surface 15, of reduced diameter. Its dimensions are mastered by machining. It may, for example, include a chamfer in the vicinity of the shoulder defining the range of reduced diameter. This chamfer will provide the filler metal during the final weld.
  • a first subassembly 20 was formed forming the entire external part of a so-called "return" combustion chamber.
  • FIG. 2A is welded edge to edge a shell 21 of stamped sheet metal, intended to form the inner elbow of the combustion chamber, with a connecting ring 22 of the same functionality as that of Figure 1a and also for the subsequent connection with the turbine.
  • the other end of the internal elbow of the combustion chamber is then welded edge-to-edge and under a neutral gas with a cylindrical shell 23 intended to form the internal wall of this combustion chamber.
  • a second subassembly 30 has been made constituting the entire internal wall of the future combustion chamber, supplemented by the chamber bottom itself.
  • the two subassemblies 20, 30 are approached to each other, the intermediate connecting ring 14 being fitted on the chamber bottom 24 and welded by orbital welding, for example by laser, under neutral gas.
  • the required filler metal is provided by said intermediate connecting ring.
  • the combustion chamber thus obtained, with a "smooth" outer wall, facilitates the positioning of the laser equipment used to make the multperforation orifices in the wall of the combustion chamber.
  • the type of welding used ensures a better thermomechanical behavior of the chamber.
  • the cost of manufacture is reduced.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Laser Beam Processing (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Butt Welding And Welding Of Specific Article (AREA)
EP07101484A 2006-02-01 2007-01-31 Verfahren zur Herstellung einer Brennkammer Active EP1816399B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0650352A FR2896854B1 (fr) 2006-02-01 2006-02-01 Procede de fabrication d'une chambre de combustion

Publications (2)

Publication Number Publication Date
EP1816399A1 true EP1816399A1 (de) 2007-08-08
EP1816399B1 EP1816399B1 (de) 2010-09-22

Family

ID=37037957

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07101484A Active EP1816399B1 (de) 2006-02-01 2007-01-31 Verfahren zur Herstellung einer Brennkammer

Country Status (9)

Country Link
US (1) US8015707B2 (de)
EP (1) EP1816399B1 (de)
JP (1) JP2007237294A (de)
CN (1) CN101012937A (de)
CA (1) CA2576704C (de)
DE (1) DE602007009332D1 (de)
FR (1) FR2896854B1 (de)
RU (1) RU2426032C2 (de)
ZA (1) ZA200700924B (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3084445A1 (fr) 2018-07-25 2020-01-31 Safran Aircraft Engines Fabrication d'une chambre de combustion en materiau composite

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7595958B2 (en) 2006-01-06 2009-09-29 Charles Partee System including a hard disk drive and stray magnetic field sensor and associated method
US8864492B2 (en) * 2011-06-23 2014-10-21 United Technologies Corporation Reverse flow combustor duct attachment
DE102013220653B4 (de) * 2013-10-14 2019-12-05 Eberspächer Climate Control Systems GmbH & Co. KG Brennkammerbaugruppe, insbesondere für einen Verdampferbrenner
CN107120689B (zh) * 2017-04-28 2019-04-26 中国航发湖南动力机械研究所 回流燃烧室内弯管结构及回流燃烧室、燃气涡轮发动机
US11112119B2 (en) 2018-10-25 2021-09-07 General Electric Company Combustor assembly for a turbo machine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB791752A (en) * 1954-03-02 1958-03-12 Bristol Aero Engines Ltd Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines
US4458481A (en) * 1982-03-15 1984-07-10 Brown Boveri Turbomachinery, Inc. Combustor for regenerative open cycle gas turbine system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4195475A (en) * 1977-12-21 1980-04-01 General Motors Corporation Ring connection for porous combustor wall panels
US6986452B2 (en) * 1999-09-03 2006-01-17 Lockheed Martin Corporation Friction stir welding as a rivet replacement technology
US7168606B2 (en) * 2003-02-06 2007-01-30 Weatherford/Lamb, Inc. Method of mitigating inner diameter reduction of welded joints
FR2870470B1 (fr) * 2004-05-18 2007-09-28 Snecma Moteurs Sa Procede de soudage tig

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB791752A (en) * 1954-03-02 1958-03-12 Bristol Aero Engines Ltd Improvements in or relating to flame tubes for use in combustion systems of gas turbine engines
US4458481A (en) * 1982-03-15 1984-07-10 Brown Boveri Turbomachinery, Inc. Combustor for regenerative open cycle gas turbine system

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3084445A1 (fr) 2018-07-25 2020-01-31 Safran Aircraft Engines Fabrication d'une chambre de combustion en materiau composite
US11085640B2 (en) 2018-07-25 2021-08-10 Sanfran Aircraft Engines Production of a combustion chamber made of composite material

Also Published As

Publication number Publication date
CN101012937A (zh) 2007-08-08
CA2576704C (fr) 2015-04-21
EP1816399B1 (de) 2010-09-22
JP2007237294A (ja) 2007-09-20
FR2896854A1 (fr) 2007-08-03
DE602007009332D1 (de) 2010-11-04
CA2576704A1 (fr) 2007-08-01
RU2426032C2 (ru) 2011-08-10
ZA200700924B (en) 2008-07-30
US8015707B2 (en) 2011-09-13
RU2007103789A (ru) 2008-08-10
US20070175029A1 (en) 2007-08-02
FR2896854B1 (fr) 2008-04-25

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