| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_38b046f78fec8bcbee8db010dbeb4e0b |
| classificationCPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-60
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2300-603 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F04D29-542
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-005
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D5-282
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D9-044
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D5-146 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F04D29-54
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D9-04
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D5-14 |
| filingDate |
2018-12-18^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_7614b4a9d190ae44176a79204fed4203 |
| publicationDate |
2020-07-13^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
BE-1026884-A1 |
| titleOfInvention |
Stator stage of a compressor of an aircraft turbomachine |
| abstract |
This document presents an invention relating to a stator stage (1) of a compressor of an aircraft turbomachine. The stator stage (1) comprises an inner shell (2) comprising at least one segment (21) made of a composite material, an outer shell, stator vanes (3) extending radially from the inner shell (2) to the outer shell, and at least one auxiliary vane (4) comprising a root (42) embedded at least partially in said composite material, and extending radially, from this root (42), essentially parallel to and between two of the stator vanes (3). |
| priorityDate |
2018-12-18^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |