EP1310735A1 - Hitzeschildanordnung mit Dichtungselement - Google Patents
Hitzeschildanordnung mit Dichtungselement Download PDFInfo
- Publication number
- EP1310735A1 EP1310735A1 EP02020171A EP02020171A EP1310735A1 EP 1310735 A1 EP1310735 A1 EP 1310735A1 EP 02020171 A EP02020171 A EP 02020171A EP 02020171 A EP02020171 A EP 02020171A EP 1310735 A1 EP1310735 A1 EP 1310735A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wall
- heat shield
- shingles
- shield arrangement
- arrangement according
- 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
- 238000007789 sealing Methods 0.000 title claims description 24
- 238000001816 cooling Methods 0.000 claims description 18
- 238000013016 damping Methods 0.000 claims description 3
- 241000283216 Phocidae Species 0.000 description 23
- 238000002485 combustion reaction Methods 0.000 description 9
- 230000008901 benefit Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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 several shingles, each mounted on a wall are, as well as with at least one between adjacent shingles arranged sealing element, the shingles for Wall to form a space to which cooling air can be applied are spaced.
- the heat shield arrangement relates to a hot gas Structure, in particular in the metallic component of a gas turbine plant or combustion chamber of a gas turbine.
- combustion chamber components z. B. heat shields or shingles, without sealing element to be screwed to the wall of a combustion chamber.
- the connection done by means of a bolt, the edges of the Place the shingle directly on the wall of the combustion chamber. No sealing element is used here.
- So-called strip seals are from other designs known. These are divided into adjacent side slots Shingles or heat shields inserted and sealed thus these against each other. Such a construction shows for example DE 10 003 728. There are such Seals formed as checker plates, which in corresponding lateral grooves of the shingles are inserted.
- seals according to EP 1 130 219 A1 because the area between two adjacent heat shields between not the grooves for the clip-like seal with air for the preferred method of effusion or Perspiration cooling can be supplied.
- the Seal has a large radial extension and is therefore in axial direction not flexible. With different Thermal expansion along the edge of the shingle Temperature gradients or radial deformations from others The quality of the Sealing effect.
- the invention is further based on the problem that the usual shingles are rigid with a bolt are screwed to the wall of the combustion chamber.
- the bolt is usually designed as a threaded bolt, he will fixed with a washer and a nut. This rigid attachment leads to a significant increase 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 of a heat shield arrangement to create the type mentioned above, which at simple structure and simple, reliable usability sufficient cooling and a long service life having.
- the object is characterized by the features of Main claim solved, the sub-claims show more advantageous embodiments of the invention.
- the seal Edges of the shingles by means of fasteners from the Wall are kept spaced and that the sealing element spaced from the wall against the edges of the shingles is fitted adjacent, the seal over this Edges can slide.
- the shield arrangement according to the invention is characterized by a number of significant benefits.
- the fastener is designed as a bolt is which passes through a recess in the wall. It is provided that at least on one side of the wall at least one elastic element is interposed, which gives the shingle angular mobility to the wall is achieved. In a preferred development of the invention it is also possible to have at least one on both sides of the wall install elastic element.
- the elastic element By means of the elastic element there is the possibility to keep the bolt elastic, but to seal it gas-tight.
- the elastic element is at the same time designed as a sealing element.
- the elastic element also has vibration damping properties has, for example through the Friction between the several provided in one package elastic elements and / or the wall and the surface the clapboard.
- Fig. 1 is a schematic cross-sectional view a wall 2, for example a combustion chamber, shown. These are, for example, with fasteners 6, several shingles lying next to each other 1 assembled.
- the mounting axes are each with the reference symbol 10 provided.
- Fig. 2 shows a simplified representation in the perspective view the flexible, broken Guides 7.
- a threaded bolt is provided on the shingle 1, which passes through a recess 8 of the wall 2.
- the recess 8 has a larger diameter than that Outside diameter of the fastener 6.
- a fixation takes place by means of an external thread of the bolt 6, on which a nut 13 is screwed on.
- Washer 12 is provided.
- both are between the wall 2 and the shingles 1 as well as between the wall 2 and the washer 12 are each annular, elastic elements inserted.
- a C-shaped Cross section This results in a sufficient Elasticity.
- the elastic elements a seal, which can be gas-tight in particular, to prevent cooling air from escaping.
- the elastic elements in the form of disc springs. These have the additional advantage of vibration damping due to the friction between the individual spring plates on.
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)
Abstract
Description
- Fig. 1
- eine schematische Quer-Schnittansicht der erfindungsgemäßen Hitzeschildanordnung mit Dichtungselement;
- Fig. 2
- eine perspektivische vereinfachte Ansicht der unterbrochenen Führungsflächen für das Dichtungselement;
- Fig. 3
- eine vereinfachte Schnittansicht der erfindungsgemäßen Ausgestaltung des Befestigungselements mit elastischen Elementen; und
- Fig. 4
- eine Ansicht, analog Fig. 3, eines weiteren Ausführungsbeispiels.
- 1
- Schindel
- 2
- Wandung
- 3
- Dichtungselement
- 4
- Zwischenraum
- 5
- Rand
- 6
- Befestigungselement
- 7
- Führung
- 8
- Ausnehmung
- 9
- elastisches Element
- 10
- Achse
- 12
- Unterlegscheibe
- 13
- Mutter
Claims (10)
- Hitzeschildanordnung mit mehreren Schindeln (1), welche jeweils an einer Wandung (2) gelagert sind, sowie mit zumindest einem zwischen benachbarten Schindeln (1) angeordneten Dichtungselement (3), wobei die Schindeln (1) zur Wandung (2) zur Bildung eines mit Kühlluft beaufschlagbaren Zwischenraums (4) beabstandet sind, dadurch gekennzeichnet, dass abzudichtende Ränder (5) der Schindel (1) mittels Befestigungsmitteln (6) von der Wandung (2) beabstandet gehalten sind und dass das Dichtungselement (3) von der Wandung (2) beabstandet gegen die Ränder (5) der Schindeln (1) anliegend montiert ist, wobei die Dichtung über diese Ränder gleiten kann.
- Hitzeschildanordnung nach Anspruch 1, dadurch gekennzeichnet, dass seitliche Führungen (7) zur Halterung des Dichtungselements (3) vorgesehen sind.
- Hitzeschildanordnung nach Anspruch 2, dadurch gekennzeichnet, dass die seitlichen Führungen (7) sich nur über einen Teil der Länge des Dichtungselements (3) erstrecken.
- Hitzeschildanordnung nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass die Schindeln (1) zueinander beabstandet montiert sind.
- Hitzeschildanordnung nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass das Befestigungselement (6) als Bolzen ausgebildet ist, welcher eine Ausnehmung (8) der Wandung (2) durchgreift, wobei zumindest an einer Seite der Wandung (2) zumindest ein elastisches Element (9) zwischengelegt ist, wodurch eine Winkelbeweglichkeit der Schindel zur Wandung erreicht wird.
- Hitzeschildanordnung nach Anspruch 5, dadurch gekennzeichnet, dass beidseitig der Wandung (2) zumindest ein elastisches Element (9) angeordnet ist.
- Hitzeschildanordnung nach Anspruch 5 oder 6, dadurch gekennzeichnet, dass das elastische Element (9) in Form einer Feder ausgebildet ist.
- Hitzeschildanordnung nach einem der Ansprüche 5 bis 7, dadurch gekennzeichnet, dass das elastische Element (9) als Dichtungselement ausgebildet ist.
- Hitzeschildanordnung nach einem der Ansprüche 5 bis 8, dadurch gekennzeichnet, dass das elastische Element 9 als Schwingungsdämpfungselement ausgebildet ist.
- Hitzeschildanordnung nach einem der Ansprüche 5 bis 9, dadurch gekennzeichnet, dass der Durchmesser der Ausnehmung (8) größer ist als der Durchmesser des Bolzens (6), wodurch eine Verschieblichkeit in axialer und Umfangsrichtung ermöglicht wird.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE10155420A DE10155420A1 (de) | 2001-11-12 | 2001-11-12 | Hitzeschildanordnung mit Dichtungselement |
| DE10155420 | 2001-11-12 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| EP1310735A1 true EP1310735A1 (de) | 2003-05-14 |
| EP1310735B1 EP1310735B1 (de) | 2006-10-18 |
Family
ID=7705416
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| EP02020171A Expired - Lifetime EP1310735B1 (de) | 2001-11-12 | 2002-09-09 | Hitzeschildanordnung mit Dichtungselement |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US6901757B2 (de) |
| EP (1) | EP1310735B1 (de) |
| DE (2) | DE10155420A1 (de) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1635118A3 (de) * | 2004-09-10 | 2006-04-19 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Heissgaskammer und Schindel für eine Heissgaskammer |
| EP1591725A3 (de) * | 2004-04-30 | 2014-03-05 | Siemens Aktiengesellschaft | Heissgas-Dichtung |
| WO2014158252A1 (en) * | 2013-03-14 | 2014-10-02 | Rolls-Royce Corporation | Bi-metal fastener for thermal growth compensation |
| DE102016222099A1 (de) | 2016-11-10 | 2018-05-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
| US10451279B2 (en) | 2015-02-12 | 2019-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing of a radial gap between effusion tiles of a gas-turbine combustion chamber |
Families Citing this family (39)
| 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 (de) * | 2004-01-27 | 2005-08-10 | Siemens Aktiengesellschaft | Hitzeschild |
| 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 |
| US20100095679A1 (en) * | 2008-10-22 | 2010-04-22 | Honeywell International Inc. | Dual wall structure for use in a combustor of a gas turbine engine |
| US20100095680A1 (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 (en) | 2013-03-05 | 2014-09-12 | Rolls-Royce Corporation | Dual-wall impingement, convection, effusion combustor tile |
| US10634351B2 (en) | 2013-04-12 | 2020-04-28 | United Technologies Corporation | Combustor panel T-junction cooling |
| US9534784B2 (en) | 2013-08-23 | 2017-01-03 | Pratt & Whitney Canada Corp. | Asymmetric combustor heat shield panels |
| US8984896B2 (en) | 2013-08-23 | 2015-03-24 | Pratt & Whitney Canada Corp. | Interlocking combustor heat shield panels |
| US10816201B2 (en) * | 2013-09-13 | 2020-10-27 | Raytheon Technologies Corporation | Sealed combustor liner panel for a gas turbine engine |
| WO2015039075A1 (en) | 2013-09-16 | 2015-03-19 | United Technologies Corporation | Angled combustor liner cooling holes through transverse structure within a gas turbine engine combustor |
| EP3047128B1 (de) | 2013-09-16 | 2018-10-31 | United Technologies Corporation | Kontrollierte variation des druckabfalls durch effusionskühlung in einer doppelwandigen brennkammer eines gasturbinentriebwerks |
| US10684017B2 (en) | 2013-10-24 | 2020-06-16 | Raytheon Technologies Corporation | Passage geometry for gas turbine engine combustor |
| 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 |
| US10739001B2 (en) | 2017-02-14 | 2020-08-11 | Raytheon Technologies Corporation | Combustor liner panel shell interface 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 |
| 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 |
| 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 |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1118806A1 (de) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand |
| DE10003728A1 (de) | 2000-01-28 | 2001-08-09 | Siemens Ag | Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
| EP1130219A1 (de) | 2000-03-02 | 2001-09-05 | Siemens Aktiengesellschaft | Turbinenanlage mit Dichtungen zwischen Plattenelementen |
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| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| JPH03504999A (ja) * | 1988-06-13 | 1991-10-31 | シーメンス、アクチエンゲゼルシヤフト | 高温流体を導く構造物のための熱遮蔽装置 |
| 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 (de) * | 1997-07-28 | 2002-03-06 | Alstom | Keramische Auskleidung |
| 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 |
| GB2361303B (en) * | 2000-04-14 | 2004-10-20 | Rolls Royce Plc | Wall structure for a gas turbine engine combustor |
| EP1284390A1 (de) * | 2001-06-27 | 2003-02-19 | Siemens Aktiengesellschaft | Hitzeschildanordnung für eine Heissgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
-
2001
- 2001-11-12 DE DE10155420A patent/DE10155420A1/de not_active Withdrawn
-
2002
- 2002-09-09 EP EP02020171A patent/EP1310735B1/de not_active Expired - Lifetime
- 2002-09-09 DE DE50208487T patent/DE50208487D1/de not_active Expired - Lifetime
- 2002-11-12 US US10/291,425 patent/US6901757B2/en not_active Expired - Fee Related
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1118806A1 (de) * | 2000-01-20 | 2001-07-25 | Siemens Aktiengesellschaft | Thermisch belastbare Wand und Verfahren zur Abdichtung eines Spaltes in einer thermisch belasteten Wand |
| DE10003728A1 (de) | 2000-01-28 | 2001-08-09 | Siemens Ag | Hitzeschildanordnung für eine Heißgas führende Komponente, insbesondere für Strukturteile von Gasturbinen |
| EP1130219A1 (de) | 2000-03-02 | 2001-09-05 | Siemens Aktiengesellschaft | Turbinenanlage mit Dichtungen zwischen Plattenelementen |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1591725A3 (de) * | 2004-04-30 | 2014-03-05 | Siemens Aktiengesellschaft | Heissgas-Dichtung |
| US8695989B2 (en) | 2004-04-30 | 2014-04-15 | Siemens Aktiengesellschaft | Hot gas seal |
| EP1635118A3 (de) * | 2004-09-10 | 2006-04-19 | DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. | Heissgaskammer und Schindel für eine Heissgaskammer |
| WO2014158252A1 (en) * | 2013-03-14 | 2014-10-02 | Rolls-Royce Corporation | Bi-metal fastener for thermal growth compensation |
| US9422865B2 (en) | 2013-03-14 | 2016-08-23 | Rolls-Royce Corporation | Bi-metal fastener for thermal growth compensation |
| US10451279B2 (en) | 2015-02-12 | 2019-10-22 | Rolls-Royce Deutschland Ltd & Co Kg | Sealing of a radial gap between effusion tiles of a gas-turbine combustion chamber |
| DE102016222099A1 (de) | 2016-11-10 | 2018-05-17 | Rolls-Royce Deutschland Ltd & Co Kg | Brennkammer einer Gasturbine |
Also Published As
| Publication number | Publication date |
|---|---|
| US6901757B2 (en) | 2005-06-07 |
| EP1310735B1 (de) | 2006-10-18 |
| DE10155420A1 (de) | 2003-05-22 |
| US20030089115A1 (en) | 2003-05-15 |
| DE50208487D1 (de) | 2006-11-30 |
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