Tail cone for a microjet rotary turbine engine
The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engin...
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| creator | Vuillemin Alexandre Alfred Gaston Gervais Yves Koenig Maxime Jordan Peter Comte Pierre |
| description | The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body. |
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The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.</description><language>eng</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; 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=20180206&DB=EPODOC&CC=US&NR=9885315B2$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180206&DB=EPODOC&CC=US&NR=9885315B2$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Vuillemin Alexandre Alfred Gaston</creatorcontrib><creatorcontrib>Gervais Yves</creatorcontrib><creatorcontrib>Koenig Maxime</creatorcontrib><creatorcontrib>Jordan Peter</creatorcontrib><creatorcontrib>Comte Pierre</creatorcontrib><title>Tail cone for a microjet rotary turbine engine</title><description>The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNALSczMUUjOz0tVSMsvUkhUyM1MLsrPSi1RKMovSSyqVCgpLUrKBMqm5qUDKR4G1rTEnOJUXijNzaDg5hri7KGbWpAfn1pckJicmpdaEh8abGlhYWpsaOpkZEyEEgCE_ioZ</recordid><startdate>20180206</startdate><enddate>20180206</enddate><creator>Vuillemin Alexandre Alfred Gaston</creator><creator>Gervais Yves</creator><creator>Koenig Maxime</creator><creator>Jordan Peter</creator><creator>Comte Pierre</creator><scope>EVB</scope></search><sort><creationdate>20180206</creationdate><title>Tail cone for a microjet rotary turbine engine</title><author>Vuillemin Alexandre Alfred Gaston ; Gervais Yves ; Koenig Maxime ; Jordan Peter ; Comte Pierre</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US9885315B23</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2018</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Vuillemin Alexandre Alfred Gaston</creatorcontrib><creatorcontrib>Gervais Yves</creatorcontrib><creatorcontrib>Koenig Maxime</creatorcontrib><creatorcontrib>Jordan Peter</creatorcontrib><creatorcontrib>Comte Pierre</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Vuillemin Alexandre Alfred Gaston</au><au>Gervais Yves</au><au>Koenig Maxime</au><au>Jordan Peter</au><au>Comte Pierre</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Tail cone for a microjet rotary turbine engine</title><date>2018-02-06</date><risdate>2018</risdate><abstract>The invention relates to a rear casing for a turbine engine comprising a primary body generating a primary flow (10) to be ejected through a primary nozzle (6), said rear casing (7) being shaped so as to be positioned downstream from the primary body and to define, on the inside of the turbine engine, the path followed by the primary flow downstream from the primary nozzle (6). The tail cone is characterised in that it comprises a connection to a system for supplying a pressurised gas and at least one perforation (8) for injecting the pressurised gas through the perforation and into the primary flow. The casing preferably comprises at least one means for rotating same about the axis of rotation of the mobile elements of the primary body.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng |
| recordid | cdi_epo_espacenet_US9885315B2 |
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| subjects | BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | Tail cone for a microjet rotary turbine engine |
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