EP1816399A1 - Method of manufacturing a combustion chamber - Google Patents
Method of manufacturing a combustion chamber Download PDFInfo
- 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
- welding
- subassembly
- 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
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 32
- 238000004519 manufacturing process Methods 0.000 title claims description 9
- 238000003466 welding Methods 0.000 claims abstract description 25
- 238000000034 method Methods 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 5
- 239000000945 filler Substances 0.000 claims description 4
- 238000003754 machining Methods 0.000 claims description 2
- 238000003032 molecular docking Methods 0.000 claims description 2
- 238000000429 assembly Methods 0.000 abstract description 2
- 230000007935 neutral effect Effects 0.000 description 6
- 230000000930 thermomechanical effect Effects 0.000 description 2
- 210000002105 tongue Anatomy 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000005493 welding type Methods 0.000 description 1
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
- F23R3/002—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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2213/00—Burner manufacture specifications
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- 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)
Abstract
Assemblage soudé des éléments d'une chambre de combustion.Welded assembly of the elements of a combustion chamber.
On fabrique deux sous-ensembles (20, 30), de la chambre de combustion par soudures bord à bord en soudant à un premier sous-ensemble (20) un anneau intermédiaire de raccordement (14) permettant la soudure finale du second sous-ensemble (30).
Description
L'invention se rapporte à un procédé de fabrication d'une chambre de combustion par assemblages de viroles préformées ; elle concerne plus particulièrement le type d'assemblage retenu, éliminant toute soudure à la molette. L'invention s'applique avantageusement à la fabrication des chambres de combustion dites « à retour ».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.
L'invention concerne également une chambre de combustion directe obtenue par la mise en oeuvre du procédé et un turboréacteur équipé d'une telle chambre de combustion.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.
Une chambre de combustion dite à retour se compose habituellement de tôles embouties pour constituer des viroles. Les viroles sont assemblées entre elles. Pour l'assemblage, les viroles comportent souvent des languettes annulaires assemblées à plat par une soudure à la molette.A so-called return combustion chamber usually consists of pressed sheets to form ferrules. The ferrules are assembled together. For assembly, the ferrules often have annular tongues assembled flat by a seam weld.
Ces languettes soudées font saillie à l'extérieur de la chambre de combustion, ce qui crée des pertes de charge dans le flux d'écoulement d'air de contournement de cette chambre. De plus, il subsiste une faiblesse mécanique au niveau de ces languettes particulièrement pour une chambre à retour lors de sollicitation en flexion du coude externe de celle-ci.These welded tabs protrude outside the combustion chamber, which creates pressure drops in the bypass airflow flow of this chamber. In addition, there is a mechanical weakness in these tabs particularly for a return chamber during bending stress of the outer bend thereof.
En outre, ce type d'assemblage génère des contraintes thermomécaniques et pose des problèmes d'accessibilité si l'on désire réaliser une perforation laser de la chambre.In addition, this type of assembly generates thermomechanical stresses and poses accessibility problems if it is desired to perform a laser perforation of the chamber.
On a récemment cherché à réduire le nombre de languettes annulaires au profit d'assemblages bord à bord. Cependant, les solutions envisagées jusqu'à présent n'ont pas permis de supprimer complètement toute soudure à la molette.Recent attempts have been made to reduce the number of annular tongues in favor of edge-to-edge assemblies. However, the solutions envisaged up to now have not made it possible to completely eliminate any welding at the wheel.
L'invention permet d'atteindre cet objectif.The invention achieves this goal.
Plus particulièrement, l'invention concerne un procédé de fabrication d'une chambre de combustion essentiellement constituée de viroles soudées, caractérisé en ce qu'il consiste à réaliser séparément deux sous-ensembles de telles viroles par soudure bord à bord de celles-ci, en soudant à une extrémité d'un premier sous-ensemble un anneau intermédiaire de raccordement, comportant une portée de montage, à engager une extrémité d'un second sous-ensemble sur cette portée et à la souder audit anneau intermédiaire.More particularly, 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.
Pour la fabrication d'une chambre de combustion dite « à retour » le premier sous-ensemble est principalement constitué des viroles externes et le second sous-ensemble est principalement constitué des viroles internes. Les viroles de chaque sous-ensemble sont assemblées par soudure bord à bord. Une virole à fond plat constitue un fond de chambre, portant les injecteurs et ce fond de chambre fait partie de l'un des sous-ensembles, avant la soudure finale.For the manufacture of a so-called "return" combustion chamber, 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.
Par exemple, l'un des sous-ensembles inclut un tel fond de chambre et l'une des extrémités de ce fond de chambre constitue l'extrémité dudit second sous-ensemble destinée à être soudée audit anneau intermédiaire.For example, 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.
D'une façon connue en soi, toute soudure bord à bord est pratiquée en réglant l'accostage des deux pièces annulaires concernées grâce à des outils d'expansion radiale qui permettent de positionner ces pièces bord à bord en vue de la soudure.In a manner known per se, 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.
L'anneau intermédiaire de raccordement est une pièce au moins en partie usinée, aux cotes ajustées. Il peut donc assurer une fonction de centrage au moment de l'assemblage final des deux sous-ensembles, par soudage orbital. Cet assemblage peut se faire par soudure laser ou soudure « TIG ».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.
De plus, l'anneau intermédiaire de raccordement comporte ou constitue lui-même le métal d'apport nécessaire à la soudure avec ledit second sous-ensemble.In addition, the intermediate connecting ring comprises or itself constitutes the filler metal required for welding with said second subset.
Une chambre de combustion selon l'invention est donc caractérisée en ce qu'elle est constituée d'une pluralité de viroles préformées dont un fond de chambre, assemblées par soudures bord à bord à l'exception d'une jonction entre deux sous-ensembles de telles viroles, ladite jonction étant faite avec interposition d'un anneau intermédiaire de raccordement précité.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.
L'invention sera mieux comprise et d'autres avantages de celle-ci apparaîtront plus clairement à la lumière de la description qui va suivre d'un procédé de fabrication d'une chambre de combustion « à retour » conforme à son principe, donnée uniquement à titre d'exemple et faite en référence aux dessins annexés dans lesquels :
- les figures 1A à 1C illustrent différentes opérations de soudage pour constituer un premier sous-ensemble ;
- les figures 2A à 2C illustrent différentes opérations de soudage pour constituer un second sous-ensemble ; et
- la figure 3 illustre une opération de soudage orbital réunissant les deux sous-ensembles pour constituer une chambre de combustion à retour.
- FIGS. 1A to 1C illustrate various welding operations to constitute a first subset;
- FIGS. 2A to 2C illustrate various welding operations to form a second subassembly; and
- Figure 3 illustrates an orbital welding operation bringing together the two subassemblies to form a return combustion chamber.
Les dessins décrits brièvement ci-dessus sont des demi-coupes schématiques représentant des viroles annulaires ou d'autres pièces annulaires réunies entre elles successivement pour constituer une chambre de combustion à retour. A l'exception de la soudure illustrée sur la figure 3 qui est une soudure orbitale spécifique de l'invention permettant de réunir deux sous-ensembles de viroles déjà soudées entre elles, les autres opérations décrites en référence aux figures 1A-1C et aux figures 2A-2C, peuvent être effectuées dans un ordre différent. L'opération schématisée à la figure 3, en revanche, est la dernière soudure.The drawings described briefly above are schematic half-sections showing annular rings or other annular pieces joined together successively to form a return combustion chamber. With the exception of the weld illustrated in FIG. 3 which is a specific orbital weld of the invention making it possible to join two subassemblies of ferrules already welded together, the other operations described with reference to FIGS. 1A-1C and FIGS. 2A-2C, can be performed in a different order. The operation shown schematically in Figure 3, however, is the last weld.
Les soudures bord à bord mentionnées en référence aux figures 1A-1C et 2A-2C sont indiquées par des flèches.The edge-to-edge welds mentioned with reference to FIGS. 1A-1C and 2A-2C are indicated by arrows.
Conformément à la figure 1A, on soude bord à bord, sous gaz neutre ; une tôle emboutie en forme de virole 11, formant le coude externe de la chambre de combustion, avec un anneau de raccordement éventuellement usiné 12. Cet anneau servira ultérieurement au raccordement entre la sortie de chambre et une turbine haute pression.According to Figure 1A, weld edge to edge, under neutral gas; a ferrule-shaped pressed
Conformément à la figure 1B on soude ensuite, bord à bord, sous gaz neutre, l'autre extrémité du coude externe à une extrémité d'une virole cylindrique 13 formant la paroi externe de la chambre de combustion.In accordance with FIG. 1B, the other end of the external bend is then welded edge to edge under neutral gas at one end of a
Conformément à la figure 1C, on soude bord à bord l'autre extrémité circulaire de la virole cylindrique 13 audit anneau intermédiaire de raccordement 14 qui sera utilisé lors de la soudure finale. La soudure, annulaire, se fait sous gaz neutre. Comme mentionné précédemment, l'anneau intermédiaire de raccordement 14 comporte une portée de montage 15, cylindrique, de diamètre réduit. Ses cotes sont maîtrisées par usinage. Il peut, par exemple, comporter un chanfrein au voisinage de l'épaulement définissant la portée de diamètre réduit. Ce chanfrein permettra de fournir le métal d'apport lors de la soudure finale.According to Figure 1C, is welded edge to edge the other circular end of the
A l'issu de l'opération illustrée sur la figure 1C, on a réalisé un premier sous-ensemble 20 formant toute la partie externe d'une chambre de combustion dite « à retour ».At the end of the operation illustrated in FIG. 1C, a
Conformément à l'opération illustrée sur la figure 2A, on soude bord à bord une virole 21 en tôle emboutie, destinée à former le coude interne de la chambre de combustion, avec un anneau de raccordement 22 de même fonctionnalité que celui de la figure 1a et destiné lui aussi au raccordement ultérieur avec la turbine.According to the operation illustrated in Figure 2A, is welded edge to edge a
Conformément à la figure 2B, on soude ensuite, bord à bord et sous gaz neutre, l'autre extrémité du coude interne de la chambre de combustion avec une virole cylindrique 23 destinée à former la paroi interne de cette chambre de combustion.According to FIG. 2B, the other end of the internal elbow of the combustion chamber is then welded edge-to-edge and under a neutral gas with a
Conformément à la figure 2C, on soude ensuite, bord à bord et sous gaz neutre, l'autre extrémité de la virole cylindrique 23 au bord interne d'une virole 24 destinée à constituer le fond de chambre sur lequel seront montés les injecteurs.According to Figure 2C, is then welded, edge to edge and under neutral gas, the other end of the
A l'issu de l'opération illustrée sur la figure 2C, on a réalisé un second sous-ensemble 30 constituant toute la paroi interne de la future chambre de combustion, complétée par le fond de chambre lui-même.At the end of the operation illustrated in FIG. 2C, a
Conformément à la figure 3, les deux sous-ensembles 20, 30 sont accostés l'un à l'autre, l'anneau intermédiaire de raccordement 14 étant ajusté sur le fond de chambre 24 et soudé par soudure orbitale, par exemple par laser, sous gaz neutre. Comme mentionné précédemment, le métal d'apport nécessaire est fourni par ledit anneau intermédiaire de raccordement.According to FIG. 3, the two
Il est à noter que, étant donné la structure de l'anneau intermédiaire de raccordement, la dernière soudure ne perturbera pas l'écoulement de l'air autour de la chambre de combustion.It should be noted that, given the structure of the intermediate connecting ring, the last weld will not disturb the flow of air around the combustion chamber.
De plus, la chambre de combustion ainsi obtenue, à paroi externe « lisse » facilite le positionnement des équipements laser utilisés pour réaliser les orifices de multperforation dans la paroi de la chambre de combustion.In addition, 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.
Le type de soudure utilisé assure un meilleur comportement thermomécanique de la chambre. Le coût de fabrication est réduit.The type of welding used ensures a better thermomechanical behavior of the chamber. The cost of manufacture is reduced.
Claims (10)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0650352A FR2896854B1 (en) | 2006-02-01 | 2006-02-01 | METHOD FOR MANUFACTURING A COMBUSTION CHAMBER |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1816399A1 true EP1816399A1 (en) | 2007-08-08 |
| EP1816399B1 EP1816399B1 (en) | 2010-09-22 |
Family
ID=37037957
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP07101484A Active EP1816399B1 (en) | 2006-02-01 | 2007-01-31 | Method of manufacturing a combustion chamber |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US8015707B2 (en) |
| EP (1) | EP1816399B1 (en) |
| JP (1) | JP2007237294A (en) |
| CN (1) | CN101012937A (en) |
| CA (1) | CA2576704C (en) |
| DE (1) | DE602007009332D1 (en) |
| FR (1) | FR2896854B1 (en) |
| RU (1) | RU2426032C2 (en) |
| ZA (1) | ZA200700924B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3084445A1 (en) | 2018-07-25 | 2020-01-31 | Safran Aircraft Engines | MANUFACTURE OF A COMBUSTION CHAMBER OF COMPOSITE MATERIAL |
Families Citing this family (5)
| 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 (en) | 2013-10-14 | 2019-12-05 | Eberspächer Climate Control Systems GmbH & Co. KG | Combustion chamber assembly, in particular for an evaporator burner |
| CN107120689B (en) * | 2017-04-28 | 2019-04-26 | 中国航发湖南动力机械研究所 | Bend pipe structure and reverse flow type combustor, gas-turbine unit in reflowed combustion room |
| US11112119B2 (en) * | 2018-10-25 | 2021-09-07 | General Electric Company | Combustor assembly for a turbo machine |
Citations (2)
| 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)
| 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 (en) * | 2004-05-18 | 2007-09-28 | Snecma Moteurs Sa | TIG WELDING PROCESS |
-
2006
- 2006-02-01 FR FR0650352A patent/FR2896854B1/en not_active Expired - Fee Related
-
2007
- 2007-01-26 US US11/627,715 patent/US8015707B2/en active Active
- 2007-01-30 CA CA2576704A patent/CA2576704C/en active Active
- 2007-01-30 JP JP2007019114A patent/JP2007237294A/en not_active Withdrawn
- 2007-01-31 DE DE602007009332T patent/DE602007009332D1/en active Active
- 2007-01-31 ZA ZA200700924A patent/ZA200700924B/en unknown
- 2007-01-31 RU RU2007103789/06A patent/RU2426032C2/en active
- 2007-01-31 EP EP07101484A patent/EP1816399B1/en active Active
- 2007-02-01 CN CN200710004592.4A patent/CN101012937A/en active Pending
Patent Citations (2)
| 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)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR3084445A1 (en) | 2018-07-25 | 2020-01-31 | Safran Aircraft Engines | MANUFACTURE OF A COMBUSTION CHAMBER OF COMPOSITE MATERIAL |
| 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 |
|---|---|
| EP1816399B1 (en) | 2010-09-22 |
| DE602007009332D1 (en) | 2010-11-04 |
| RU2426032C2 (en) | 2011-08-10 |
| ZA200700924B (en) | 2008-07-30 |
| FR2896854B1 (en) | 2008-04-25 |
| FR2896854A1 (en) | 2007-08-03 |
| US20070175029A1 (en) | 2007-08-02 |
| CA2576704A1 (en) | 2007-08-01 |
| JP2007237294A (en) | 2007-09-20 |
| RU2007103789A (en) | 2008-08-10 |
| CA2576704C (en) | 2015-04-21 |
| US8015707B2 (en) | 2011-09-13 |
| CN101012937A (en) | 2007-08-08 |
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