DE602008004720D1 - Segmentierte keramische Schicht für ein Element eines Gasturbinenantriebs - Google Patents
Segmentierte keramische Schicht für ein Element eines GasturbinenantriebsInfo
- Publication number
- DE602008004720D1 DE602008004720D1 DE602008004720T DE602008004720T DE602008004720D1 DE 602008004720 D1 DE602008004720 D1 DE 602008004720D1 DE 602008004720 T DE602008004720 T DE 602008004720T DE 602008004720 T DE602008004720 T DE 602008004720T DE 602008004720 D1 DE602008004720 D1 DE 602008004720D1
- Authority
- DE
- Germany
- Prior art keywords
- gas turbine
- turbine engine
- ceramic layer
- segmented ceramic
- segmented
- 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
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
- F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2230/00—Manufacture
- F05B2230/90—Coating; Surface treatment
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
-
- 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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US11/946,114 US8079806B2 (en) | 2007-11-28 | 2007-11-28 | Segmented ceramic layer for member of gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| DE602008004720D1 true DE602008004720D1 (de) | 2011-03-10 |
Family
ID=40377350
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| DE602008004720T Active DE602008004720D1 (de) | 2007-11-28 | 2008-11-28 | Segmentierte keramische Schicht für ein Element eines Gasturbinenantriebs |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US8079806B2 (de) |
| EP (1) | EP2065566B1 (de) |
| DE (1) | DE602008004720D1 (de) |
Families Citing this family (59)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US8535783B2 (en) | 2010-06-08 | 2013-09-17 | United Technologies Corporation | Ceramic coating systems and methods |
| US8845272B2 (en) | 2011-02-25 | 2014-09-30 | General Electric Company | Turbine shroud and a method for manufacturing the turbine shroud |
| US9995165B2 (en) | 2011-07-15 | 2018-06-12 | United Technologies Corporation | Blade outer air seal having partial coating |
| EP2586985A1 (de) * | 2011-10-25 | 2013-05-01 | Siemens Aktiengesellschaft | Oberfläche mit speziell ausgeformten Vertiefungen und Bauteil |
| EP2597259A1 (de) * | 2011-11-24 | 2013-05-29 | Siemens Aktiengesellschaft | Modifizierte Oberfläche um ein Loch |
| US9145786B2 (en) | 2012-04-17 | 2015-09-29 | General Electric Company | Method and apparatus for turbine clearance flow reduction |
| US9416675B2 (en) | 2014-01-27 | 2016-08-16 | General Electric Company | Sealing device for providing a seal in a turbomachine |
| US8939707B1 (en) | 2014-02-25 | 2015-01-27 | Siemens Energy, Inc. | Turbine abradable layer with progressive wear zone terraced ridges |
| US9249680B2 (en) | 2014-02-25 | 2016-02-02 | Siemens Energy, Inc. | Turbine abradable layer with asymmetric ridges or grooves |
| US8939705B1 (en) | 2014-02-25 | 2015-01-27 | Siemens Energy, Inc. | Turbine abradable layer with progressive wear zone multi depth grooves |
| US8939716B1 (en) | 2014-02-25 | 2015-01-27 | Siemens Aktiengesellschaft | Turbine abradable layer with nested loop groove pattern |
| US9243511B2 (en) | 2014-02-25 | 2016-01-26 | Siemens Aktiengesellschaft | Turbine abradable layer with zig zag groove pattern |
| WO2015130527A2 (en) | 2014-02-25 | 2015-09-03 | Siemens Aktiengesellschaft | Turbine component thermal barrier coating with depth-varying material properties |
| US9151175B2 (en) | 2014-02-25 | 2015-10-06 | Siemens Aktiengesellschaft | Turbine abradable layer with progressive wear zone multi level ridge arrays |
| US8939706B1 (en) | 2014-02-25 | 2015-01-27 | Siemens Energy, Inc. | Turbine abradable layer with progressive wear zone having a frangible or pixelated nib surface |
| US9957826B2 (en) | 2014-06-09 | 2018-05-01 | United Technologies Corporation | Stiffness controlled abradeable seal system with max phase materials and methods of making same |
| GB201415201D0 (en) * | 2014-08-28 | 2014-10-15 | Rolls Royce Plc | A wear monitor for a gas turbine engine fan |
| EP3029274B1 (de) | 2014-10-30 | 2020-03-11 | United Technologies Corporation | Thermisch gespritztes bonding einer keramikstruktur auf ein substrat |
| US10099290B2 (en) | 2014-12-18 | 2018-10-16 | General Electric Company | Hybrid additive manufacturing methods using hybrid additively manufactured features for hybrid components |
| US20160236994A1 (en) * | 2015-02-17 | 2016-08-18 | Rolls-Royce Corporation | Patterned abradable coatings and methods for the manufacture thereof |
| WO2016133581A1 (en) | 2015-02-18 | 2016-08-25 | Siemens Aktiengesellschaft | Turbine shroud with abradable layer having composite non-inflected triple angle ridges and grooves |
| EP3259452A2 (de) | 2015-02-18 | 2017-12-27 | Siemens Aktiengesellschaft | Formung von kühlpassagen in verbrennungsturbine-superlegierungsgussteilen |
| EP3103967B1 (de) * | 2015-06-10 | 2019-07-31 | United Technologies Corporation | Äussere laufschaufelluftdichtung mit partieller beschichtung |
| FR3044945B1 (fr) | 2015-12-14 | 2018-01-12 | Centre National De La Recherche Scientifique | Revetement abradable a densite variable |
| FR3044946B1 (fr) * | 2015-12-14 | 2018-01-12 | Safran Aircraft Engines | Revetement abradable a densite variable |
| ES2922927T3 (es) | 2016-05-10 | 2022-09-21 | Saint Gobain Ceramics & Plastics Inc | Procedimientos de formación de partículas abrasivas |
| US20170335155A1 (en) | 2016-05-10 | 2017-11-23 | Saint-Gobain Ceramics & Plastics, Inc. | Abrasive particles and methods of forming same |
| US10436062B2 (en) | 2016-11-17 | 2019-10-08 | United Technologies Corporation | Article having ceramic wall with flow turbulators |
| US10415407B2 (en) | 2016-11-17 | 2019-09-17 | United Technologies Corporation | Airfoil pieces secured with endwall section |
| US10746038B2 (en) | 2016-11-17 | 2020-08-18 | Raytheon Technologies Corporation | Airfoil with airfoil piece having radial seal |
| US10677079B2 (en) | 2016-11-17 | 2020-06-09 | Raytheon Technologies Corporation | Airfoil with ceramic airfoil piece having internal cooling circuit |
| US10502070B2 (en) | 2016-11-17 | 2019-12-10 | United Technologies Corporation | Airfoil with laterally insertable baffle |
| US10767487B2 (en) | 2016-11-17 | 2020-09-08 | Raytheon Technologies Corporation | Airfoil with panel having flow guide |
| US10711624B2 (en) | 2016-11-17 | 2020-07-14 | Raytheon Technologies Corporation | Airfoil with geometrically segmented coating section |
| US10677091B2 (en) | 2016-11-17 | 2020-06-09 | Raytheon Technologies Corporation | Airfoil with sealed baffle |
| US10731495B2 (en) | 2016-11-17 | 2020-08-04 | Raytheon Technologies Corporation | Airfoil with panel having perimeter seal |
| US10605088B2 (en) | 2016-11-17 | 2020-03-31 | United Technologies Corporation | Airfoil endwall with partial integral airfoil wall |
| US10480334B2 (en) | 2016-11-17 | 2019-11-19 | United Technologies Corporation | Airfoil with geometrically segmented coating section |
| US10309238B2 (en) | 2016-11-17 | 2019-06-04 | United Technologies Corporation | Turbine engine component with geometrically segmented coating section and cooling passage |
| US10408090B2 (en) | 2016-11-17 | 2019-09-10 | United Technologies Corporation | Gas turbine engine article with panel retained by preloaded compliant member |
| US10711616B2 (en) | 2016-11-17 | 2020-07-14 | Raytheon Technologies Corporation | Airfoil having endwall panels |
| US10570765B2 (en) | 2016-11-17 | 2020-02-25 | United Technologies Corporation | Endwall arc segments with cover across joint |
| US10480331B2 (en) | 2016-11-17 | 2019-11-19 | United Technologies Corporation | Airfoil having panel with geometrically segmented coating |
| US10662779B2 (en) | 2016-11-17 | 2020-05-26 | Raytheon Technologies Corporation | Gas turbine engine component with degradation cooling scheme |
| US10428663B2 (en) | 2016-11-17 | 2019-10-01 | United Technologies Corporation | Airfoil with tie member and spring |
| US10458262B2 (en) | 2016-11-17 | 2019-10-29 | United Technologies Corporation | Airfoil with seal between endwall and airfoil section |
| US10711794B2 (en) | 2016-11-17 | 2020-07-14 | Raytheon Technologies Corporation | Airfoil with geometrically segmented coating section having mechanical secondary bonding feature |
| US10662782B2 (en) | 2016-11-17 | 2020-05-26 | Raytheon Technologies Corporation | Airfoil with airfoil piece having axial seal |
| US10808554B2 (en) | 2016-11-17 | 2020-10-20 | Raytheon Technologies Corporation | Method for making ceramic turbine engine article |
| US10309226B2 (en) | 2016-11-17 | 2019-06-04 | United Technologies Corporation | Airfoil having panels |
| US10598029B2 (en) | 2016-11-17 | 2020-03-24 | United Technologies Corporation | Airfoil with panel and side edge cooling |
| US10598025B2 (en) | 2016-11-17 | 2020-03-24 | United Technologies Corporation | Airfoil with rods adjacent a core structure |
| US10436049B2 (en) | 2016-11-17 | 2019-10-08 | United Technologies Corporation | Airfoil with dual profile leading end |
| US10408082B2 (en) | 2016-11-17 | 2019-09-10 | United Technologies Corporation | Airfoil with retention pocket holding airfoil piece |
| US10428658B2 (en) | 2016-11-17 | 2019-10-01 | United Technologies Corporation | Airfoil with panel fastened to core structure |
| US10428674B2 (en) * | 2017-01-31 | 2019-10-01 | Rolls-Royce North American Technologies Inc. | Gas turbine engine features for tip clearance inspection |
| US11131206B2 (en) * | 2018-11-08 | 2021-09-28 | Raytheon Technologies Corporation | Substrate edge configurations for ceramic coatings |
| FR3091548B1 (fr) * | 2019-01-09 | 2022-12-09 | Safran Aircraft Engines | Elément abradable de turbomachine pourvu de témoins d’usure visuels |
| US11149581B2 (en) * | 2019-11-22 | 2021-10-19 | Rolls-Royce Plc | Turbine engine component with overstress indicator |
Family Cites Families (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4289447A (en) | 1979-10-12 | 1981-09-15 | General Electric Company | Metal-ceramic turbine shroud and method of making the same |
| US4652209A (en) * | 1985-09-13 | 1987-03-24 | Rockwell International Corporation | Knurled turbine tip seal |
| US4758480A (en) | 1987-12-22 | 1988-07-19 | United Technologies Corporation | Substrate tailored coatings |
| US5352540A (en) | 1992-08-26 | 1994-10-04 | Alliedsignal Inc. | Strain-tolerant ceramic coated seal |
| EP0705911B1 (de) | 1994-10-04 | 2001-12-05 | General Electric Company | Hochtemperatur-Schutzschicht |
| WO1996011288A1 (en) | 1994-10-05 | 1996-04-18 | United Technologies Corporation | Multiple nanolayer coating system |
| US6102656A (en) | 1995-09-26 | 2000-08-15 | United Technologies Corporation | Segmented abradable ceramic coating |
| US5951892A (en) | 1996-12-10 | 1999-09-14 | Chromalloy Gas Turbine Corporation | Method of making an abradable seal by laser cutting |
| US6224963B1 (en) | 1997-05-14 | 2001-05-01 | Alliedsignal Inc. | Laser segmented thick thermal barrier coatings for turbine shrouds |
| US5933976A (en) | 1997-05-30 | 1999-08-10 | Pressutti; Joseph E. | Method of installing a ridge cover and guide tool for practicing this method |
| US6113347A (en) * | 1998-12-28 | 2000-09-05 | General Electric Company | Blade containment system |
| US6589600B1 (en) * | 1999-06-30 | 2003-07-08 | General Electric Company | Turbine engine component having enhanced heat transfer characteristics and method for forming same |
| US6435835B1 (en) | 1999-12-20 | 2002-08-20 | United Technologies Corporation | Article having corrosion resistant coating |
| GB2361033B (en) * | 2000-04-08 | 2004-06-09 | Rolls Royce Plc | A gas turbine engine blade containment assembly |
| US6703137B2 (en) | 2001-08-02 | 2004-03-09 | Siemens Westinghouse Power Corporation | Segmented thermal barrier coating and method of manufacturing the same |
| FR2832180B1 (fr) * | 2001-11-14 | 2005-02-18 | Snecma Moteurs | Revetement abradable pour parois de turbines a gaz |
| US7302990B2 (en) * | 2004-05-06 | 2007-12-04 | General Electric Company | Method of forming concavities in the surface of a metal component, and related processes and articles |
| EP1808507A1 (de) | 2006-01-16 | 2007-07-18 | Siemens Aktiengesellschaft | Bauteil mit Beschichtung und Verfahren zum Herstellen einer Beschichtung |
| EP1844863A1 (de) | 2006-04-12 | 2007-10-17 | General Electric Company | Artikel enthaltend eine Oberfläche mit niedriger Benetzbarkeit und dessen Herstellungsverfahren |
-
2007
- 2007-11-28 US US11/946,114 patent/US8079806B2/en active Active
-
2008
- 2008-11-28 DE DE602008004720T patent/DE602008004720D1/de active Active
- 2008-11-28 EP EP08253835A patent/EP2065566B1/de active Active
Also Published As
| Publication number | Publication date |
|---|---|
| US8079806B2 (en) | 2011-12-20 |
| EP2065566A1 (de) | 2009-06-03 |
| EP2065566B1 (de) | 2011-01-26 |
| US20090136345A1 (en) | 2009-05-28 |
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