| Predicate |
Object |
| assignee |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentassignee/MD5_fd4735dbc2bd2bb60a1673344a4a95c1 |
| classificationCPCAdditional |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-162
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D27-26
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-36
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D27-18 |
| classificationCPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-28
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C3-113
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D5-04
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-20
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-06
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F04D29-388
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F04D29-325
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F01D25-243
http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F04D29-542 |
| classificationIPCInventive |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F04D29-54
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C3-113
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F04D29-32
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F04D29-38
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C7-20
http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-06 |
| filingDate |
2020-04-28^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor |
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_6772a8efe7dd62ebded09fe8844163cb
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_6d96a55c6dacabf788c688835451baee
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_91da88c661b0ba04866b911743f4373e
http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_3df6802492ec1468320950e3d81eeded |
| publicationDate |
2020-11-03^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber |
CN-111878259-A |
| titleOfInvention |
Gas turbine engine with improved bending resistance |
| abstract |
The present disclosure relates to gas turbine engines with improved bending resistance. A gas turbine engine (10) for an aircraft is disclosed, the gas turbine engine comprising: an engine core (11) comprising a first lower pressure compressor (14) and a second higher pressure compressor ( 15); and an outer core housing (70) surrounding the compressor system. The gas turbine engine also includes a fan (23) upstream of the engine core (11), the fan including a plurality of fan blades (23a) and having a fan diameter (112). The outer core shell includes a first flange connection (60) arranged to allow the outer core shell (70) to be in an axial position of the first flange connection (60). At the point of separation, the first flange connection (60) has a first flange radius (104). |
| priorityDate |
2019-05-02^^<http://www.w3.org/2001/XMLSchema#date> |
| type |
http://data.epo.org/linked-data/def/patent/Publication |