TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE
A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine...
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| creator | Cretin Fabrice Michel François René Toribio Leny Perdrigeon Christophe Marcel Lucien Jacquemard Christophe Paul Cottet Clément |
| description | A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft. |
| format | Patent |
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The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COSMONAUTICS ; ENGINE PLANTS IN GENERAL ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; HEATING ; HELICOPTERS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; PARACHUTES ; PERFORMING OPERATIONS ; STEAM ENGINES ; TRANSPORTING ; WEAPONS</subject><creationdate>2018</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180301&DB=EPODOC&CC=US&NR=2018058260A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76516</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180301&DB=EPODOC&CC=US&NR=2018058260A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Cretin Fabrice Michel François René</creatorcontrib><creatorcontrib>Toribio Leny</creatorcontrib><creatorcontrib>Perdrigeon Christophe Marcel Lucien</creatorcontrib><creatorcontrib>Jacquemard Christophe Paul</creatorcontrib><creatorcontrib>Cottet Clément</creatorcontrib><title>TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE</title><description>A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COSMONAUTICS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>HEATING</subject><subject>HELICOPTERS</subject><subject>LIGHTING</subject><subject>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>STEAM ENGINES</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZIgMCQ1y8vRzVXD1cwdR4Z4hHgqOfgr-nj4K7qGeLp5-7gourmGezq5AURcFX9cQD38XBTf_IAUXz2DH4GBXXycfkJoQD1cFVKN4GFjTEnOKU3mhNDeDsptriLOHbmpBfnxqcUFicmpeakl8aLCRgaGFgamFkZmBo6ExcaoApRMx-Q</recordid><startdate>20180301</startdate><enddate>20180301</enddate><creator>Cretin Fabrice Michel François René</creator><creator>Toribio Leny</creator><creator>Perdrigeon Christophe Marcel Lucien</creator><creator>Jacquemard Christophe Paul</creator><creator>Cottet Clément</creator><scope>EVB</scope></search><sort><creationdate>20180301</creationdate><title>TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE</title><author>Cretin Fabrice Michel François René ; Toribio Leny ; Perdrigeon Christophe Marcel Lucien ; Jacquemard Christophe Paul ; Cottet Clément</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2018058260A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2018</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COSMONAUTICS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>HEATING</topic><topic>HELICOPTERS</topic><topic>LIGHTING</topic><topic>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>STEAM ENGINES</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Cretin Fabrice Michel François René</creatorcontrib><creatorcontrib>Toribio Leny</creatorcontrib><creatorcontrib>Perdrigeon Christophe Marcel Lucien</creatorcontrib><creatorcontrib>Jacquemard Christophe Paul</creatorcontrib><creatorcontrib>Cottet Clément</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Cretin Fabrice Michel François René</au><au>Toribio Leny</au><au>Perdrigeon Christophe Marcel Lucien</au><au>Jacquemard Christophe Paul</au><au>Cottet Clément</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE</title><date>2018-03-01</date><risdate>2018</risdate><abstract>A turbine engine is provided with a longitudinal rotation axis having at least one shaft with a radial axis, in particular a pitch change system for the blades of a propeller, said shaft traversing a radial passage of a substantially cylindrical case around the longitudinal axis. The turbine engine includes an annular oil guiding device around the radial shaft. The device has first and second annular parts nested in one another and secured to one another by hooping. The first part is secured by hooping to the radial shaft, and the second part is configured so as to be separated from the first part under the action of a force oriented along the radial axis and exerted on the second part by a member of the turbine engine forming a stop during a radial movement of the radial shaft.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
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| subjects | AEROPLANES AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HELICOPTERS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS |
| title | TURBINE ENGINE WITH AN OIL GUIDING DEVICE AND METHOD FOR DISASSEMBLING THE TURBINE ENGINE |
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