http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-108239737-A
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_ff25f1cb49009413b4714e8e340b76f4 |
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-9607 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-74 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-3229 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-3225 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-443 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-444 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-62695 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-62605 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-48 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-62222 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C4-134 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C4-11 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-626 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-622 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-48 |
| filingDate | 2016-12-27-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor | http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_d4d5939d69b6e060067d7e2b2f599880 |
| publicationDate | 2018-07-03-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | CN-108239737-A |
| titleOfInvention | Method for preparing heat barrier coating |
| abstract | Method for preparing heat barrier coating.Since the operating temperature of aircraft engine hot junction component may be up to 1350 DEG C, it is therefore desirable to use many advanced configuration material preparation thermal barrier coatings (TBCs) to cool down numbers of hot-side engine component.A kind of to use nanometer CYSZ ceramic layer materials, fusing point is up to 2700 DEG C；Thermal conductivity is 1.29Wm 1K 1, and coefficient of thermal expansion is 11 × 10 6 DEG C 1, low-density (6.4 g/cm 3 ) engine quality can be mitigated；Low elastic modulus can reduce thermal stress；CeO is prepared with coprecipitation 2 —Y 2 O 3 Stable CYSZ nano ceramic powders altogether, again to CYSZ nano powder mist projection granulatings after, nanometer CYSZ ceramic heat-barrier coatings are prepared using plasma spraying technology method, rare earth material is combined with heat barrier coat material with nano material is exclusive the characteristics of, relationship between thermal barrier coating microstructure and macro property is obtained by research, makes CeO 2 —Y 2 O 3 Stable CYSZ thermal barrier coatings are advantageously applied to the engine thermal end pieces of operating temperature continuous improvement altogether.The engine component surface that the present invention is prepared for plasma thermal sprayed method. |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-113649772-B http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-114480999-A http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-112176275-A http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-113649772-A |
| priorityDate | 2016-12-27-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
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