DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE
A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and...
Gespeichert in:
| Hauptverfasser: | , , |
|---|---|
| Format: | Patent |
| Sprache: | fre |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | AMOEDO SIMON SCHOLTES CHRISTOPHE BRUNET ANTOINE ROBERT ALAIN |
| description | A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_FR3047042B1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>FR3047042B1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_FR3047042B13</originalsourceid><addsrcrecordid>eNqNS70KwjAQ7uIg6jtk6yRUKzhf0mt7g0m9XFxLkThJLdT3xxR9AOGD73-djRX5znkSqlWFCQ3dGJqk8mCVRrOkHjtgEHJWoaQGgkavKmI0wmQWnaMVxu8NlQTW7gKmpWQA2VkIQteA22z1GJ5z3P14k6kaxbT7OL36OE_DPY7x3ddcFqdzcTrqQ_nH5AOM0jYz</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE</title><source>esp@cenet</source><creator>AMOEDO SIMON ; SCHOLTES CHRISTOPHE ; BRUNET ANTOINE ROBERT ALAIN</creator><creatorcontrib>AMOEDO SIMON ; SCHOLTES CHRISTOPHE ; BRUNET ANTOINE ROBERT ALAIN</creatorcontrib><description>A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice.</description><language>fre</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; 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=20180216&DB=EPODOC&CC=FR&NR=3047042B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180216&DB=EPODOC&CC=FR&NR=3047042B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>AMOEDO SIMON</creatorcontrib><creatorcontrib>SCHOLTES CHRISTOPHE</creatorcontrib><creatorcontrib>BRUNET ANTOINE ROBERT ALAIN</creatorcontrib><title>DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE</title><description>A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice.</description><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNS70KwjAQ7uIg6jtk6yRUKzhf0mt7g0m9XFxLkThJLdT3xxR9AOGD73-djRX5znkSqlWFCQ3dGJqk8mCVRrOkHjtgEHJWoaQGgkavKmI0wmQWnaMVxu8NlQTW7gKmpWQA2VkIQteA22z1GJ5z3P14k6kaxbT7OL36OE_DPY7x3ddcFqdzcTrqQ_nH5AOM0jYz</recordid><startdate>20180216</startdate><enddate>20180216</enddate><creator>AMOEDO SIMON</creator><creator>SCHOLTES CHRISTOPHE</creator><creator>BRUNET ANTOINE ROBERT ALAIN</creator><scope>EVB</scope></search><sort><creationdate>20180216</creationdate><title>DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE</title><author>AMOEDO SIMON ; SCHOLTES CHRISTOPHE ; BRUNET ANTOINE ROBERT ALAIN</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_FR3047042B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>fre</language><creationdate>2018</creationdate><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>AMOEDO SIMON</creatorcontrib><creatorcontrib>SCHOLTES CHRISTOPHE</creatorcontrib><creatorcontrib>BRUNET ANTOINE ROBERT ALAIN</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>AMOEDO SIMON</au><au>SCHOLTES CHRISTOPHE</au><au>BRUNET ANTOINE ROBERT ALAIN</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE</title><date>2018-02-16</date><risdate>2018</risdate><abstract>A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | fre |
| recordid | cdi_epo_espacenet_FR3047042B1 |
| source | esp@cenet |
| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | DISPOSITIF DE DEGIVRAGE D'UN BEC DE SEPARATION ET D'AUBES DIRECTRICES D'ENTREE D'UNE TURBOMACHINE AERONAUTIQUE |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-30T06%3A55%3A21IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=AMOEDO%20SIMON&rft.date=2018-02-16&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EFR3047042B1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |