http://rdf.ncbi.nlm.nih.gov/pubchem/patent/FR-3060652-B1
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_9f240453e620e11bf59a7bfbae9d099e |
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2300-6012 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2201-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2230-90 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-60 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2260-311 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D2045-009 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/A62C2-065 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-25 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D29-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/A62C3-08 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D29-00 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-25 |
| filingDate | 2016-12-21-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| grantDate | 2019-08-23-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor | http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_cd809cf51359c6bf2c70659196f85a81 http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_a5b7db061ff40426bb723101398b9fd0 |
| publicationDate | 2019-08-23-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | FR-3060652-B1 |
| titleOfInvention | NACELLE FOR AIRCRAFT TURBOJET ENGINE EQUIPPED WITH A FIRE EXTINGUISHING DEVICE |
| abstract | The present invention relates to a nacelle (41) for a turbojet engine comprising: an upstream section forming an air inlet; a median section downstream from said upstream section, comprising: a fan cowl surrounding a fan casing; a turbojet, a median annular space delimited by said fan cowl and said fan case, said median annular space defining a median fire zone of the nacelle, a downstream section comprising a fixed internal structure (25) surrounding a central compartment (21) of said turbojet, forming a downstream annular space defined by said fixed internal structure and an outer wall (27) of said turbojet, said central compartment defining a downstream fire zone (29) of the nacelle. The nacelle according to the invention is remarkable in that it comprises a fire extinguishing device designed to stifle a fire by constriction when a fire is triggered in said zones (29) of fire. |
| priorityDate | 2016-12-21-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
Total number of triples: 31.