| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_fd4735dbc2bd2bb60a1673344a4a95c1 |
| classificationCPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2240-14 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-28
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D33-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-20
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-162 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D25-16
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D27-18
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D29-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-20
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F01D25-28 |
| filingDate |
2011-04-15-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_1a1512852d59216dabf7badc8e3c4641
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_ff45fbe66a6dfddb80e8874574a52904 |
| publicationDate |
2011-11-02-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
EP-2383442-A2 |
| titleOfInvention |
Gas turbine engine |
| abstract |
A gas turbine engine (1) has an annular bypass duct (4) defined between a fan nacelle (2) and a core fairing (3) through which fan air is discharged. One or more bifurcator members (5a-5i) are positioned inside the exit of the bypass duct (4) to bifurcate the air flow in the bypass duct around the bifurcator members (5a-5i) prior to exiting the bypass duct (4). The bifurcator members (5a-5i) modify the flow field of the air in the bypass duct radially and/or tangentially with respect to the axis of the annular bypass duct (4). |
| priorityDate |
2010-04-30-04:00^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |