FIELD: engine building.
SUBSTANCE: group of inventions relates to heat insulation of parts under high-temperature conditions. Part for gas turbine engine, having at least one first layer of thermal barrier, containing ceramic material and first ceramic fibers, dispersed in first layer. First layer can have chemical composition difference between thermal barrier material and calcium and magnesium aluminosilicate protection material, which content is more significant in outer zone of first layer, and/or first layer can be made porous and contain porosity difference, at which outer part of first layer has reduced porosity.
EFFECT: provides protection against environmental effects, longer service life.
9 cl, 6 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| COATED PART FOR GAS TURBINE ENGINE AND ITS MANUFACTURING METHOD | 2018 |
|
RU2762611C2 |
| COATED PART FOR GAS TURBINE ENGINE AND ITS MANUFACTURING METHOD | 2018 |
|
RU2764153C2 |
| PART CONTAINING COATING FOR PROTECTION AGAINST CMAS COMPOUNDS | 2016 |
|
RU2719964C2 |
| GAS TURBINE ENGINE PART COMPRISING A PROTECTIVE CERAMIC COATING, A METHOD OF MAKING AND USING SUCH PART | 2016 |
|
RU2722376C2 |
| FABRICATION OF HEAT-BARRIER PROTECTION AND SANDWICHED COATING THAT CAN GENERATE SAID HEAT BARRIER | 2011 |
|
RU2561550C2 |
| METHOD OF PERFORMING HEAT BARRIER IN MULTILAYER METAL PART PROTECTION SYSTEM AND PART EQUIPPED WITH SUCH PROTECTIVE SYSTEM | 2012 |
|
RU2600781C2 |
| METHOD FOR COATING SOLID BASE SURFACE WITH LAYER CONTAINING CERAMIC COMPOUND, AND BASE WITH COATING OBTAINED BY THIS METHOD | 2017 |
|
RU2761397C2 |
| METHOD FOR PRODUCTION OF A THERMAL BARRIER SYSTEM BASED ON A METAL TURBOMACHINE PART | 2017 |
|
RU2742862C2 |
| PROCESS FOR LOCALISED REPAIR OF DAMAGED THERMAL BARRIER | 2014 |
|
RU2678347C2 |
| METHOD OF APPLYING HEAT-PROTECTIVE COATING TO PARTS OF GAS TURBINE UNIT | 2023 |
|
RU2813539C1 |
