http://rdf.ncbi.nlm.nih.gov/pubchem/patent/CN-111350602-A
Outgoing Links
| Predicate | Object |
|---|---|
| assignee | http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_fd4735dbc2bd2bb60a1673344a4a95c1 |
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-60 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2250-38 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2260-40311 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K1-06 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-02 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-057 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C9-18 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-06 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K1-06 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-02 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-06 |
| filingDate | 2019-12-16^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor | http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_fab80d14e1746dc5bbdd224ac4555127 http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_627ee4194fa5b93e09349e3a09d6deff |
| publicationDate | 2020-06-30^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | CN-111350602-A |
| titleOfInvention | Turbofan gas turbine engine with bypass duct |
| abstract | The invention provides a turbofan gas turbine engine with a bypass duct. The invention provides a gas turbine engine (10) for an aircraft, comprising: an engine core (11); a fan (23) located upstream of the engine core (11), the fan (23) including a plurality of fan blades (64); a nacelle (21) surrounding the gas turbine engine (10), the nacelle (21) comprising an inner surface at least partially defining a bypass duct (22); and bypass duct outlet guide vanes (58) extending radially across the bypass duct (22) between an outer surface of the engine core (11) and an inner surface of the nacelle. An outer wall axis (59) is defined to join a radially outer tip of a trailing edge of the bypass duct outlet guide wheel vane (58) with a rearmost tip (21b) of an inner surface of the nacelle (21), wherein the outer wall axis (59) lies in a longitudinal plane containing a centerline (9) of the gas turbine engine (10), an outer bypass duct wall angle (126) is defined as an angle between the outer wall axis (59) and the centerline (9), and the outer bypass duct wall angle (126) is in a range between-15 degrees and 1 degree. |
| priorityDate | 2018-12-21^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
| Predicate | Subject |
|---|---|
| isDiscussedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/substance/SID419545405 http://rdf.ncbi.nlm.nih.gov/pubchem/compound/CID91778 |
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