ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE

Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) compr...

Ausführliche Beschreibung

Gespeichert in:
Bibliographische Detailangaben
Hauptverfasser: PELLATON, BERTRAND GUILLAUME ROBIN, BENASSIS, LUCAS
Format: Patent
Sprache:eng ; pol
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 PELLATON, BERTRAND GUILLAUME ROBIN
BENASSIS, LUCAS
description Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).
format Patent
fullrecord <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_PL4010562TT3</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>PL4010562TT3</sourcerecordid><originalsourceid>FETCH-epo_espacenet_PL4010562TT33</originalsourceid><addsrcrecordid>eNrjZCgM8g_xD1Jw8nF0cVVwA7IcFSAi_m4Kjn4Kjp5BzkGObiEKIaFBTv6-js4enn6uOlAlYOU41AAlXLDL8DCwpiXmFKfyQmluBkU31xBnD93Ugvz41OKCxOTUvNSS-AAfEwNDA1Mzo5AQY2Ni1AAAwwk4CA</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE</title><source>esp@cenet</source><creator>PELLATON, BERTRAND GUILLAUME ROBIN ; BENASSIS, LUCAS</creator><creatorcontrib>PELLATON, BERTRAND GUILLAUME ROBIN ; BENASSIS, LUCAS</creatorcontrib><description>Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).</description><language>eng ; pol</language><subject>BLASTING ; ENGINE PLANTS IN GENERAL ; HEATING ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; WEAPONS</subject><creationdate>2023</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&amp;date=20231211&amp;DB=EPODOC&amp;CC=PL&amp;NR=4010562T3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&amp;date=20231211&amp;DB=EPODOC&amp;CC=PL&amp;NR=4010562T3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>PELLATON, BERTRAND GUILLAUME ROBIN</creatorcontrib><creatorcontrib>BENASSIS, LUCAS</creatorcontrib><title>ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE</title><description>Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).</description><subject>BLASTING</subject><subject>ENGINE PLANTS IN GENERAL</subject><subject>HEATING</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>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZCgM8g_xD1Jw8nF0cVVwA7IcFSAi_m4Kjn4Kjp5BzkGObiEKIaFBTv6-js4enn6uOlAlYOU41AAlXLDL8DCwpiXmFKfyQmluBkU31xBnD93Ugvz41OKCxOTUvNSS-AAfEwNDA1Mzo5AQY2Ni1AAAwwk4CA</recordid><startdate>20231211</startdate><enddate>20231211</enddate><creator>PELLATON, BERTRAND GUILLAUME ROBIN</creator><creator>BENASSIS, LUCAS</creator><scope>EVB</scope></search><sort><creationdate>20231211</creationdate><title>ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE</title><author>PELLATON, BERTRAND GUILLAUME ROBIN ; BENASSIS, LUCAS</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_PL4010562TT33</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; pol</language><creationdate>2023</creationdate><topic>BLASTING</topic><topic>ENGINE PLANTS IN GENERAL</topic><topic>HEATING</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>PELLATON, BERTRAND GUILLAUME ROBIN</creatorcontrib><creatorcontrib>BENASSIS, LUCAS</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>PELLATON, BERTRAND GUILLAUME ROBIN</au><au>BENASSIS, LUCAS</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE</title><date>2023-12-11</date><risdate>2023</risdate><abstract>Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).</abstract><oa>free_for_read</oa></addata></record>
fulltext fulltext_linktorsrc
identifier
ispartof
issn
language eng ; pol
recordid cdi_epo_espacenet_PL4010562TT3
source esp@cenet
subjects BLASTING
ENGINE PLANTS IN GENERAL
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
title ROTOR BLADE FOR A ROTOR OF AN AIRCRAFT TURBOMACHINE, ROTOR FOR AN AIRCRAFT TURBOMACHINE AND AIRCRAFT TURBOMACHINE
url https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-01-05T00%3A58%3A45IST&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=PELLATON,%20BERTRAND%20GUILLAUME%20ROBIN&rft.date=2023-12-11&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EPL4010562TT3%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