EP1310735B1 - Ensemble écran thermique comportant des éléments d'étanchéité - Google Patents
Ensemble écran thermique comportant des éléments d'étanchéité Download PDFInfo
- Publication number
- EP1310735B1 EP1310735B1 EP02020171A EP02020171A EP1310735B1 EP 1310735 B1 EP1310735 B1 EP 1310735B1 EP 02020171 A EP02020171 A EP 02020171A EP 02020171 A EP02020171 A EP 02020171A EP 1310735 B1 EP1310735 B1 EP 1310735B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- heat shield
- shield arrangement
- accordance
- sealing element
- 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.)
- Expired - Fee Related
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
- F23M5/04—Supports for linings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M5/00—Casings; Linings; Walls
-
- 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
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05005—Sealing means between wall tiles or panels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00012—Details of sealing devices
Definitions
- the invention relates to a heat shield arrangement with a plurality of shingles, which are each mounted on a wall, and with at least one arranged between adjacent shingles sealing element, wherein the shingles are spaced from the wall to form a loadable with cooling air gap.
- the heat shield arrangement relates to a structure which conducts hot gas, in particular into a metallic component of a gas turbine plant or combustion chamber of a gas turbine.
- combustion chamber components for.
- heat shields or shingles to screw without sealing element with the wall of a combustion chamber.
- the connection is made by means of a bolt, wherein the edges of the shingle rest directly on the wall of the combustion chamber. In this case, no sealing element is used.
- Strip seals are known. These are inserted into lateral slots between adjacent shingles or heat shields and thus seal them against each other. Such a construction, for example, DE 10 003 728. There are such Seals designed as Riffelbleche, which are inserted into corresponding lateral grooves of the shingles.
- seals according to EP 1 130 219 A1 since the region between two adjacent heat shields between the grooves for the clamp-like seal can not be supplied with air for the preferred method of effusion or transpiration cooling.
- the seal has a large radial extent and is therefore not flexible in the axial direction. At different thermal expansions along the shingle edge due to temperature gradients or radial deformations from others Due to reasons results in a reduced quality of the sealing effect.
- the invention is further based on the problem that the usual shingles are bolted by a bolt rigidly with the wall of the combustion chamber.
- the bolt is usually designed as a threaded bolt, it is fixed by means of a washer and a nut. This rigid attachment leads to a significant increase in the mechanical stresses in the component. When the temperature rises, these quickly exceed the permissible values, so that cracks occur in the material of the wall of the combustion chamber.
- the invention is based on the object to provide a heat shield assembly of the type mentioned, which allows a simple design and simple, reliable applicability sufficient cooling and has a long service life.
- edges of the shingles to be sealed are held spaced apart from the wall by means of fastening elements and that the sealing element is mounted so as to rest against the edges of the shingles spaced from the wall, wherein the seal can slide over these edges.
- the shield assembly according to the invention is characterized by a number of significant advantages.
- the seal Since the seal is not inserted in slots of the shingles, but is mounted between shingles and wall, there is the decisive advantage that the edges of the shingle do not rest against the wall. Rather, they are held by the fasteners at a certain distance from the wall. This makes it possible that on the one hand, the seal can always rest on both shingles and that on the other hand, a sufficient implementation of cooling air is ensured even in the region of the seals. Even if the shingles (or even the wall) deform by the action of heat, but it is always ensured a sufficient seal.
- lateral guides are provided for holding the sealing element. These prevent slipping out of the seal, so that it can be reliably fixed even when vibrations occur o. ⁇ ., The lateral guidance of the seal leaves enough play for the compensation of a relative displacement of two adjacent shingles by sliding the seal on the shingle edges.
- the lateral guides extend only over part of the length of the sealing element.
- the fastening element is designed as a bolt, which passes through a recess of the wall. It is provided that at least on one side of the wall, at least one elastic element is interposed, whereby an angular mobility of the shingle is achieved to the wall. In a preferred embodiment of the invention, it is also possible to install at least one elastic element on both sides of the wall.
- This embodiment according to the invention which can also be used completely independently of the above-described sealing arrangement with differently designed shingles, gives, inter alia, the following advantages: Even very small displacements and changes in angle between the shingle and the wall of the combustion chamber can drastically reduce the stress level in the shingle , This mobility is ensured by the inventive design. Since an elastic element is arranged in the region of the recess of the wall, which of course must have a slightly larger diameter according to the invention than the outer diameter of the bolt, a corresponding displacement path is ensured. This mobility is feasible without an enlargement of the required for mounting wall surface. Furthermore, it can be ensured that the aero-dynamic behavior of the shingle does not change due to the mobility. Thus, the cooling air flows as well as we will not affect the overall cooling efficiency.
- the elastic element By means of the elastic element there is the possibility to hold the bolt elastic, but seal gas-tight.
- the elastic element is at the same time designed as a sealing element.
- the elastic element also has vibration damping properties, for example by the friction between the plurality of provided in a package elastic elements and / or the wall and the surface of the shingle.
- This configuration results in a reduced component load, which can be exploited to extend the life or even to an increase in the allowable temperature.
- a wall 2 for example a combustion chamber is shown in a schematic manner in the cross-sectional view. On these are, for example, with fasteners 6, side by side lying several shingles 1 mounted.
- the mounting axes are each provided with the reference numeral 10.
- a gap 4 is formed through which cooling air is passed.
- the arrows schematically show the cooling air flows. It becomes clear that according to the invention the seal in any way hinders the effusion or transpiration cooling in the region of the shingle edge.
- possible passage openings o. ⁇ . Reference should be made to the prior art, so that can be dispensed with detailed representations at this point.
- the cross section of the gap 4 is so large that the edges 5 of the shingles 1 do not rest against the wall 2. Rather, it is below the edges 5 a strip-shaped or plate-shaped sealing element 3 is arranged, to whose guidance lateral guides 7 are provided.
- Fig. 2 shows a simplified representation in the perspective view of the flexible, interrupted guides 7.
- the segmentation of the lateral guide results in a flexibility of the seal, which is hardly inferior to that of strip seals. With deformation of the shingle by temperature gradients, a good seal is still guaranteed.
- a threaded bolt is provided, which passes through a recess 8 of the wall 2.
- the recess 8 has a larger diameter than the outer diameter of the fastening element 6.
- a washer 12 is provided.
- each annular elastic elements 9 are inserted. These can, as with the embodiment of FIG. 3, have a C-shaped cross-section. This results in a sufficient elasticity. At the same time, the elastic elements 9 lead to a seal, which may in particular be gas-tight in order to prevent the escape of cooling air. By appropriate dimensioning results in an angular and lateral mobility of the fastener 6 and the shingle 1 relative to the wall second
- the elastic elements 9 are formed in the form of disc springs. These have the additional advantage of vibration damping by the friction between the individual spring plates.
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)
- Gasket Seals (AREA)
Claims (10)
- Ensemble écran thermique avec plusieurs bardeaux (1), chacun d'eux logé dans une paroi (2), ainsi qu'avec au moins un élément d'étanchéité (3) placé entre des bardeaux (1) voisins, sachant que les bardeaux (1) sont écartés de la paroi (2) pour former un espace intermédiaire (4) pouvant être alimenté en air de refroidissement, et que les bords (5) des bardeaux (1) à étanchéifier sont maintenus à une certaine distance de la paroi (2) au moyen d'éléments de fixation (6), caractérisé en ce que l'élément d'étanchéité (3) est monté en appui contre les bords (5) des bardeaux (1) à une certaine distance de la paroi (2), le joint pouvant glisser sur ces bords.
- Ensemble écran thermique selon la revendication n° 1, caractérisé en ce que des guides (7) latéraux sont prévus pour maintenir l'élément d'étanchéité (3).
- Ensemble écran thermique selon la revendication n° 2, caractérisé en ce que les guides (7) latéraux s'étendent uniquement sur une partie de la longueur de l'élément d'étanchéité (3).
- Ensemble écran thermique selon une des revendications n° 1 à 3, caractérisé en ce que les bardeaux (1) sont montés à une certaine distance les uns par rapport aux autres.
- Ensemble écran thermique selon une des revendications n° 1 à 4, caractérisé en ce que l'élément de fixation (6) est formé comme boulon qui s'engage dans un évidement (8) de la paroi (2), sachant qu'au moins un élément élastique (9) est intercalé sur au moins un côté de la paroi (2), ce qui permet d'obtenir une mobilité angulaire des bardeaux par rapport à la paroi.
- Ensemble écran thermique selon la revendication n° 5, caractérisé en ce qu'au moins un élément élastique (9) est monté des deux côtés de la paroi (2).
- Ensemble écran thermique selon la revendication n° 5 ou 6, caractérisé en ce que l'élément élastique (9) est formé comme ressort.
- Ensemble écran thermique selon une des revendications n° 5 à 7, caractérisé en ce que l'élément élastique (9) est formé comme élément d'étanchéité.
- Ensemble écran thermique selon une des revendications n° 5 à 8, caractérisé en ce que l'élément élastique (9) est formé comme amortisseur de vibrations.
- Ensemble écran thermique selon une des revendications n° 5 à 9, caractérisé en ce que le diamètre de l'évidement (8) est plus grand que le diamètre du boulon (6), ce qui permet une mobilité dans les sens axial et circonférentiel.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE10155420 | 2001-11-12 | ||
DE10155420A DE10155420A1 (de) | 2001-11-12 | 2001-11-12 | Hitzeschildanordnung mit Dichtungselement |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1310735A1 EP1310735A1 (fr) | 2003-05-14 |
EP1310735B1 true EP1310735B1 (fr) | 2006-10-18 |
Family
ID=7705416
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02020171A Expired - Fee Related EP1310735B1 (fr) | 2001-11-12 | 2002-09-09 | Ensemble écran thermique comportant des éléments d'étanchéité |
Country Status (3)
Country | Link |
---|---|
US (1) | US6901757B2 (fr) |
EP (1) | EP1310735B1 (fr) |
DE (2) | DE10155420A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3056813A1 (fr) | 2015-02-12 | 2016-08-17 | Rolls-Royce Deutschland Ltd & Co KG | Joint pour un interstice marginal entre les bardeaux d'effusion d'une chambre de combustion de turbines a gaz |
Families Citing this family (43)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10003728A1 (de) * | 2000-01-28 | 2001-08-09 | Siemens Ag | Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
US20070095071A1 (en) * | 2003-09-29 | 2007-05-03 | Kastrup David A | Apparatus for assembling gas turbine engine combustors |
EP1561997A1 (fr) * | 2004-01-27 | 2005-08-10 | Siemens Aktiengesellschaft | Bouclier thermique |
US8695989B2 (en) * | 2004-04-30 | 2014-04-15 | Siemens Aktiengesellschaft | Hot gas seal |
DE102004044852A1 (de) * | 2004-09-10 | 2006-03-16 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Heißgaskammer und Schindel für eine Heißgaskammer |
DE102005046731A1 (de) * | 2005-04-19 | 2006-11-02 | Siemens Ag | Hitzeschildanordnung |
DE102006060857B4 (de) * | 2006-12-22 | 2014-02-13 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | CMC-Brennkammerauskleidung in Doppelschichtbauweise |
GB2453946B (en) * | 2007-10-23 | 2010-07-14 | Rolls Royce Plc | A Wall Element for use in Combustion Apparatus |
US7866158B2 (en) * | 2007-12-05 | 2011-01-11 | United Technologies Corporation | Exhaust liner attachment arrangement |
GB0800294D0 (en) * | 2008-01-09 | 2008-02-20 | Rolls Royce Plc | Gas heater |
GB0801839D0 (en) * | 2008-02-01 | 2008-03-05 | Rolls Royce Plc | combustion apparatus |
GB2457281B (en) * | 2008-02-11 | 2010-09-08 | Rolls Royce Plc | A Combustor Wall Arrangement with Parts Joined by Mechanical Fasteners |
GB0803366D0 (en) * | 2008-02-26 | 2008-04-02 | Rolls Royce Plc | Nose cone assembly |
GB2460634B (en) * | 2008-06-02 | 2010-07-07 | Rolls Royce Plc | Combustion apparatus |
US20100095680A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
US20100095679A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
US8359866B2 (en) * | 2010-02-04 | 2013-01-29 | United Technologies Corporation | Combustor liner segment seal member |
US8955331B2 (en) | 2011-05-20 | 2015-02-17 | Siemens Energy, Inc. | Turbine combustion system coupling with adjustable wear pad |
US9534783B2 (en) * | 2011-07-21 | 2017-01-03 | United Technologies Corporation | Insert adjacent to a heat shield element for a gas turbine engine combustor |
CA2904200A1 (fr) | 2013-03-05 | 2014-09-12 | Rolls-Royce Corporation | Tuile de chambre de combustion a effusion, convexion, impact a double paroi |
US9422865B2 (en) | 2013-03-14 | 2016-08-23 | Rolls-Royce Corporation | Bi-metal fastener for thermal growth compensation |
EP2984317B1 (fr) | 2013-04-12 | 2019-03-13 | United Technologies Corporation | Refroidissement de jonction en t de panneau de chambre de combustion |
US8984896B2 (en) | 2013-08-23 | 2015-03-24 | Pratt & Whitney Canada Corp. | Interlocking combustor heat shield panels |
US9534784B2 (en) | 2013-08-23 | 2017-01-03 | Pratt & Whitney Canada Corp. | Asymmetric combustor heat shield panels |
WO2015038232A1 (fr) * | 2013-09-13 | 2015-03-19 | United Technologies Corporation | Panneau de chemisage de chambre de combustion hermétiquement scellé pour une turbine à gaz |
WO2015039074A1 (fr) | 2013-09-16 | 2015-03-19 | United Technologies Corporation | Variation contrôlée de la chute de pression par refroidissement par effusion dans une chambre de combustion à double paroi d'une turbine à gaz |
EP3922829B1 (fr) | 2013-09-16 | 2023-11-08 | RTX Corporation | Chambre de combustion de turbine à gaz comprenant une chemise munie de trous de refroidissement à travers une structure transversale |
EP3060847B1 (fr) | 2013-10-24 | 2019-09-18 | United Technologies Corporation | Géométrie de passage pour chambre de combustion de moteur de type turbine à gaz |
US9890953B2 (en) * | 2014-01-10 | 2018-02-13 | United Technologies Corporation | Attachment of ceramic matrix composite panel to liner |
US9416675B2 (en) * | 2014-01-27 | 2016-08-16 | General Electric Company | Sealing device for providing a seal in a turbomachine |
US10012385B2 (en) * | 2014-08-08 | 2018-07-03 | Pratt & Whitney Canada Corp. | Combustor heat shield sealing |
GB201501817D0 (en) * | 2015-02-04 | 2015-03-18 | Rolls Royce Plc | A combustion chamber and a combustion chamber segment |
DE202016102795U1 (de) * | 2016-05-25 | 2017-08-28 | Reinz-Dichtungs-Gmbh | Abschirmvorrichtung |
US10247106B2 (en) | 2016-06-15 | 2019-04-02 | General Electric Company | Method and system for rotating air seal with integral flexible heat shield |
DE102016222099A1 (de) | 2016-11-10 | 2018-05-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
US10739001B2 (en) | 2017-02-14 | 2020-08-11 | Raytheon Technologies Corporation | Combustor liner panel shell interface for a gas turbine engine combustor |
US10718521B2 (en) | 2017-02-23 | 2020-07-21 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling interface passage for a gas turbine engine combustor |
US10677462B2 (en) | 2017-02-23 | 2020-06-09 | Raytheon Technologies Corporation | Combustor liner panel end rail angled cooling interface passage for a gas turbine engine combustor |
US10830434B2 (en) | 2017-02-23 | 2020-11-10 | Raytheon Technologies Corporation | Combustor liner panel end rail with curved interface passage for a gas turbine engine combustor |
US10823411B2 (en) | 2017-02-23 | 2020-11-03 | Raytheon Technologies Corporation | Combustor liner panel end rail cooling enhancement features for a gas turbine engine combustor |
US10941937B2 (en) | 2017-03-20 | 2021-03-09 | Raytheon Technologies Corporation | Combustor liner with gasket for gas turbine engine |
US11536454B2 (en) | 2019-05-09 | 2022-12-27 | Pratt & Whitney Canada Corp. | Combustor wall assembly for gas turbine engine |
CN116291871B (zh) * | 2023-05-16 | 2023-07-21 | 北京航空航天大学 | 加力燃烧室隔热屏与机匣之间的低约束高阻尼连接结构 |
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US3295280A (en) * | 1964-04-09 | 1967-01-03 | S Obermayer Co | Furnace wall anchoring structures |
US4555901A (en) * | 1972-12-19 | 1985-12-03 | General Electric Company | Combustion chamber construction |
JPS5857658B2 (ja) | 1980-04-02 | 1983-12-21 | 工業技術院長 | セラミツクスによる高熱曝露壁面の熱遮断構造 |
FR2592145B1 (fr) * | 1985-12-23 | 1989-08-18 | Cometherm Sa Cie Expl Thermiqu | Procede de realisation de parois refractaires de protection de fours ou chambres de combustion et brique refractaire pour la mise en oeuvre dudit procede. |
US4838031A (en) * | 1987-08-06 | 1989-06-13 | Avco Corporation | Internally cooled combustion chamber liner |
DE58908665D1 (de) * | 1988-06-13 | 1995-01-05 | Siemens Ag | Hitzeschildanordnung mit geringem kühlfluidbedarf. |
FR2644209B1 (fr) * | 1989-03-08 | 1991-05-03 | Snecma | Chemise de protection thermique pour canal chaud de turboreacteur |
US5176495A (en) * | 1991-07-09 | 1993-01-05 | General Electric Company | Thermal shielding apparatus or radiositor for a gas turbine engine |
US5333443A (en) * | 1993-02-08 | 1994-08-02 | General Electric Company | Seal assembly |
FR2714152B1 (fr) * | 1993-12-22 | 1996-01-19 | Snecma | Dispositif de fixation d'une tuile de protection thermique dans une chambre de combustion. |
US5755093A (en) * | 1995-05-01 | 1998-05-26 | United Technologies Corporation | Forced air cooled gas turbine exhaust liner |
EP0895027B1 (fr) * | 1997-07-28 | 2002-03-06 | Alstom | Garniture céramique |
JP3999395B2 (ja) * | 1999-03-03 | 2007-10-31 | 三菱重工業株式会社 | ガスタービン分割環 |
EP1118806A1 (fr) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Structure de paroi sous charge thermique et méthode pour fermer des fentes dans une tel structure |
DE10003728A1 (de) | 2000-01-28 | 2001-08-09 | Siemens Ag | Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
EP1130219A1 (fr) | 2000-03-02 | 2001-09-05 | Siemens Aktiengesellschaft | Turbine avec joints d'étanchéitée entre les panneaux des parois |
GB2361303B (en) * | 2000-04-14 | 2004-10-20 | Rolls Royce Plc | Wall structure for a gas turbine engine combustor |
EP1284390A1 (fr) * | 2001-06-27 | 2003-02-19 | Siemens Aktiengesellschaft | Ensemble bouclier thermique pour un composant acheminant un gaz chaud, notamment pour des pièces de structure de turbines à gaz |
-
2001
- 2001-11-12 DE DE10155420A patent/DE10155420A1/de not_active Withdrawn
-
2002
- 2002-09-09 DE DE50208487T patent/DE50208487D1/de not_active Expired - Lifetime
- 2002-09-09 EP EP02020171A patent/EP1310735B1/fr not_active Expired - Fee Related
- 2002-11-12 US US10/291,425 patent/US6901757B2/en not_active Expired - Fee Related
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3056813A1 (fr) | 2015-02-12 | 2016-08-17 | Rolls-Royce Deutschland Ltd & Co KG | Joint pour un interstice marginal entre les bardeaux d'effusion d'une chambre de combustion de turbines a gaz |
DE102015202570A1 (de) | 2015-02-12 | 2016-08-18 | Rolls-Royce Deutschland Ltd & Co Kg | Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer |
Also Published As
Publication number | Publication date |
---|---|
DE50208487D1 (de) | 2006-11-30 |
US6901757B2 (en) | 2005-06-07 |
EP1310735A1 (fr) | 2003-05-14 |
DE10155420A1 (de) | 2003-05-22 |
US20030089115A1 (en) | 2003-05-15 |
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