http://rdf.ncbi.nlm.nih.gov/pubchem/patent/GB-2539781-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/F05D2260-96 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2220-323 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C3-14 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C6-20 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C9-18 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C3-06 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C6-003 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-11 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-02 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K3-105 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C3-107 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-02 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02K3-105 http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/F02C9-18 |
| filingDate | 2016-05-11^^<http://www.w3.org/2001/XMLSchema#date> |
| inventor | http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_3e4fd7ea7e8921e5912783de488a1f83 |
| publicationDate | 2016-12-28^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | GB-2539781-A |
| titleOfInvention | Gas turbine engine |
| abstract | Gas turbine engine 10 comprises core and bypass arrangements defining core and bypass flow paths, the core comprises a first compressor 14 coupled via a first shaft 36 to a first (high pressure) turbine with first and second turbine stages 22, 26, first and second combustors 20, 24 and a further (low pressure) turbine 28 coupled via a further shaft to a further compressor. The bypass arrangement comprises a bypass fan 12 coupled to the further turbine 28 by a further shaft 40, a third combustor 90 in the bypass flow path and a bypass nozzle 92, 94, which may be a variable geometry convergent portion upstream of a divergent portion, which accelerates bypass exhaust flow to a velocity greater than core exhaust flow when the third combustor 90 is in operation. The first and/or second combustors 14, 24 may comprise an isobaric combustor providing no pressure drop from entry to exit of the combustor. The combustors 14, 24, 90 may be rich quick quench or lean burn combustors. The core may comprise a core nozzle 16, 18 which accelerates core exhaust. The combustors may comprise a cooling system. The arrangement increases efficiency and reduces noise at off design conditions. |
| isCitedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/patent/WO-2019025845-A1 |
| priorityDate | 2015-06-11^^<http://www.w3.org/2001/XMLSchema#date> |
| type | http://data.epo.org/linked-data/def/patent/Publication |
Incoming Links
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|---|---|
| isDiscussedBy | http://rdf.ncbi.nlm.nih.gov/pubchem/substance/SID419574377 http://rdf.ncbi.nlm.nih.gov/pubchem/compound/CID114994 |
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