Gasturbinenbauteil mit einer Wärmedämmschicht, Wärmedämmschicht für ein Gasturbinenbauteil sowie Verfahren zur Herstellung einer Wärmedämmschicht auf einem Gasturbinenbauteil

• Main Author: MEIER, REINHOLD
• Format: Patent
• Language: German
• Published: 07.02.2008
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; CHEMICAL SURFACE TREATMENT; CHEMISTRY; CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY IONIMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; COATING MATERIAL WITH METALLIC MATERIAL; COATING METALLIC MATERIAL; COMBUSTION APPARATUS; COMBUSTION ENGINES; COMBUSTION PROCESSES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; DIFFUSION TREATMENT OF METALLIC MATERIAL; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS; INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; METALLURGY; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THESURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS; TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE; WEAPONS

Die Erfindung betrifft ein Gasturbinenteil eines Flugtriebwerks mit einem aus zumindest einem ersten Material bestehenden Grundkörper und einer auf diesen Grundkörper aufgebrachten Wärmedämmschicht, die aus einer Oxidkeramik besteht oder eine Oxidkeramik aufweist, wobei zur Reduzierung der Wärmeleitfähigkeit der Wärmedämmschicht Mikrofehlstellen und/oder Nanofehlstellen in der Oxidkeramik eingebaut sind. A gas turbine component of an aircraft engine having a base body, which comprises at least a first material, and a thermal barrier coating that is applied to the base body and consists of or includes an oxide ceramic, is disclosed. Micro-defects and/or nano-defects are included in the oxide ceramic in order to reduce the thermal conductivity of the thermal barrier coating.