http://rdf.ncbi.nlm.nih.gov/pubchem/patent/RU-2009149458-A
Outgoing Links
| Predicate | Object |
|---|---|
| classificationCPCAdditional | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/Y02T50-60 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2260-96 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F05D2250-41 |
| classificationCPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D33-04 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/B64D29-08 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02C7-20 http://rdf.ncbi.nlm.nih.gov/pubchem/patentcpc/F02K1-72 |
| classificationIPCInventive | http://rdf.ncbi.nlm.nih.gov/pubchem/patentipc/B64D29-08 |
| filingDate | 2008-05-30^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationDate | 2011-07-20^^<http://www.w3.org/2001/XMLSchema#date> |
| publicationNumber | RU-2009149458-A |
| titleOfInvention | AIRCRAFT ENGINE ASSEMBLY WITH MOBILE ENGINE GONDOLA |
| abstract | 1. An aircraft engine unit (1) containing a turbojet engine (2), a pylon (4) for attaching a turbojet engine and a nacelle (3) mounted on a mounting pylon and surrounding a turbojet engine (2), wherein the nacelle contains at least one movable section (40) of the nacelle, forming a single one-piece casing around the section of the turbojet engine, the movable section (40) of the nacelle is freely positioned so that it can slide on the attachment pylon so that it can be moved from the forward position towards the rear, and vice versa, ! characterized in that the movable section (40) of the nacelle has an annular wall (50) providing an internal delimitation of the channel (24) of the annular secondary flow and an annular wall (46) providing an external delimitation of the channel of the annular secondary flow. ! 2. A unit according to claim 1, characterized in that the annular wall (50), providing an internal delimitation of the channel (24) of the annular secondary flow, and the annular wall (46), providing an external delimitation of the annular secondary flow channel, both are equipped with a lining (80) acoustic protection. ! 3. A unit according to claim 2, characterized in that each acoustic protection casing (80) is made continuous around the annular wall (46, 50) interacting with it. !4. The assembly according to claim 1, characterized in that the nacelle also contains a fixed section (30) of the nacelle, forming a single one-piece casing around the section of the turbojet engine, while the fixed section of the nacelle is fixed on the turbojet engine (2), and also in that the fixed section ( 30) of the nacelle forms an internal radial support for the movable section (40) of the nacelle. !five. � |
| priorityDate | 2007-06-01^^<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/compound/CID91778 http://rdf.ncbi.nlm.nih.gov/pubchem/substance/SID419545405 |
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