http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2004507620-A
Outgoing Links
| Predicate | Object |
|---|---|
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y10T428-24157 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y10T428-24149 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C23C30-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D5-288 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C23C28-044 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/C23C4-00 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D9-02 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C28-04 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C28-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C4-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/C23C30-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D25-24 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D5-28 |
| filingDate | 2001-08-21-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 2004-03-11-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | JP-2004507620-A |
| titleOfInvention | Thermal insulation coating system for turbine parts |
| abstract | The composite thermal barrier coating system includes a first composite thermal barrier coating on a portion of the substrate and a second adherent thermal barrier coating on an edge of the substrate. The first composite coating layer is relatively thick and preferably comprises a brittle graded insulation having an abradable honeycomb metal structure in which ceramic hollow spheres having a high coefficient of thermal expansion are contained within a phosphate binding matrix. Second attachment coating layer edge portion is relatively thin, preferably made of an electron-beam physical vapor deposition thermal barrier coating layer of ZrO 2 and Y 2 O 3. Fragile graded insulation layers can be manufactured to thicknesses greater than current thermal barrier coatings, thus providing greater thermal protection. Excellent erosion resistance and abrasion resistance are also obtained. The composite thermal barrier coating system is useful for components of a combustion turbine such as ring seal segments, vane segment shrouds, transitions and combustors. |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2012531523-A http://rdf.ncbi.nlm.nih.gov/pubchem/patent/JP-2013543073-A |
| priorityDate | 2000-08-31-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 32.