AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO
An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (...
Gespeichert in:
| Hauptverfasser: | , , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| 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 | Cazaux, Yannick Lecouvreur, Damien Fulleringer, Benjamin |
| description | An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2019218969A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2019218969A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2019218969A13</originalsourceid><addsrcrecordid>eNqNyrEKwjAQANAsDqL-w4GzYCqIGa_xmhyUKGfS4lSKxEm0UP8fFRwcnd7ypqpFFitYRYhJSg4EFNyHlqMHOrI925otCO2TjXwI4AgFPDYcHCA0KIxlTT9B8M1cTa79bcyLrzO1rChav8rDo8vj0F_yPT-7dCrW2hR6Z7YG9ea_9QJyVzHY</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO</title><source>esp@cenet</source><creator>Cazaux, Yannick ; Lecouvreur, Damien ; Fulleringer, Benjamin</creator><creatorcontrib>Cazaux, Yannick ; Lecouvreur, Damien ; Fulleringer, Benjamin</creatorcontrib><description>An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINEERING ELEMENTS AND UNITS ; GAS-TURBINE PLANTS ; GEARING ; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; THERMAL INSULATION IN GENERAL ; WEAPONS</subject><creationdate>2019</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=20190718&DB=EPODOC&CC=US&NR=2019218969A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20190718&DB=EPODOC&CC=US&NR=2019218969A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Cazaux, Yannick</creatorcontrib><creatorcontrib>Lecouvreur, Damien</creatorcontrib><creatorcontrib>Fulleringer, Benjamin</creatorcontrib><title>AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO</title><description>An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator.</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>ENGINEERING ELEMENTS AND UNITS</subject><subject>GAS-TURBINE PLANTS</subject><subject>GEARING</subject><subject>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>THERMAL INSULATION IN GENERAL</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqNyrEKwjAQANAsDqL-w4GzYCqIGa_xmhyUKGfS4lSKxEm0UP8fFRwcnd7ypqpFFitYRYhJSg4EFNyHlqMHOrI925otCO2TjXwI4AgFPDYcHCA0KIxlTT9B8M1cTa79bcyLrzO1rChav8rDo8vj0F_yPT-7dCrW2hR6Z7YG9ea_9QJyVzHY</recordid><startdate>20190718</startdate><enddate>20190718</enddate><creator>Cazaux, Yannick</creator><creator>Lecouvreur, Damien</creator><creator>Fulleringer, Benjamin</creator><scope>EVB</scope></search><sort><creationdate>20190718</creationdate><title>AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO</title><author>Cazaux, Yannick ; Lecouvreur, Damien ; Fulleringer, Benjamin</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2019218969A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2019</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>ENGINEERING ELEMENTS AND UNITS</topic><topic>GAS-TURBINE PLANTS</topic><topic>GEARING</topic><topic>GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>THERMAL INSULATION IN GENERAL</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>Cazaux, Yannick</creatorcontrib><creatorcontrib>Lecouvreur, Damien</creatorcontrib><creatorcontrib>Fulleringer, Benjamin</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Cazaux, Yannick</au><au>Lecouvreur, Damien</au><au>Fulleringer, Benjamin</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO</title><date>2019-07-18</date><risdate>2019</risdate><abstract>An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (50) configured to be rotationally secured to said shaft, a second element (56) rotationally secured to said member, and a third element configured to be selectively secured to a stator of the turbine engine and disengaged from the stator, wherein the turbine engine comprises driving means to rotationally drive said third element at a piloted speed when it is disengaged from said stator.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US2019218969A1 |
| source | esp@cenet |
| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING THERMAL INSULATION IN GENERAL WEAPONS |
| title | AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2025-02-10T00%3A20%3A54IST&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=Cazaux,%20Yannick&rft.date=2019-07-18&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS2019218969A1%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 |