http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-106747531-B
Outgoing Links
| Predicate | Object |
|---|---|
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-5224 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-77 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B2235-96 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B41-81 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-80 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-624 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C04B35-565 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-565 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-80 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B41-81 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C04B35-624 |
| filingDate | 2016-05-30-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| grantDate | 2017-12-22-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 2017-12-22-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | CN-106747531-B |
| titleOfInvention | A kind of polynary carbon and ceramic base thermostructural composite and its turbo blade without surplus preparation method |
| abstract | The present invention relates to a kind of polynary carbon and ceramic base thermostructural composite turbo blade without surplus preparation method, comprise the following steps：Using four step rule three-dimension integrally braiding turbo blade fabric precast body；(C+SiC) is prepared on precast body using chemical vapor infiltration n Compound interface layer；The composite single crystal alumina fibre into the turbo blade fabric precast body with compound interface layer, oozes long-pending matrix material, to prepare polynary carbon and ceramic base thermostructural composite turbo blade；Above-mentioned turbo blade is carried out without surplus densification using precursor infiltration and pyrolysis method and sol-gal process, its density is reached preset value；Environmental Barrier Coatings on Si-based Ceramics is prepared in above-mentioned turbine blade surface.According to a kind of polynary carbon and ceramic base thermostructural composite turbo blade of the present invention without surplus preparation method, fiber entirety enhancing effect is good, intensity is big, excellent in mechanical performance, it is significant to the thrust-weight ratio and avion campaign efficiency of raising military aero-engine. |
| priorityDate | 2016-05-30-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 27.