SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS
The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring being equipped with a plurality of anti-rotation pegs (66) for preventing it from rotating in relation to the rotor disc, each peg (66) protruding axiall...
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| creator | CASALIGGI, PASCAL PASQUIET, DIDIER POUZET, EMILIE |
| description | The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring being equipped with a plurality of anti-rotation pegs (66) for preventing it from rotating in relation to the rotor disc, each peg (66) protruding axially from a ring body (63) and having two opposite circumferential-end surfaces (72) which are intended respectively to be located facing two directly consecutive blades carried on the rotor disc. According to the invention, an axially opening slot (70) passes radially through at least one of the anti-rotation pegs (66).
L' invention concerne un flasque d'étanchéité (60) destiné à être plaqué contre un disque de rotor d'étage de turbine pour turbomachine d'aéronef, le flasque étant équipé d'une pluralité de tenons anti-rotation (66) permettant de bloquer sa rotation relativement au disque de rotor, chaque tenon (66) étant en saillie axialement à partir d'un corps de flasque (63) et présentant deux surfaces opposées d'extrémité circonférentielle (72), respectivement destinées à se situer en regard de deux aubes directement consécutives portées par le disque de rotor. Selon l'invention, au moins l'un des tenons anti-rotation (66) est traversé radialement par une fente (70) s' ouvrant axialement. |
| format | Patent |
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L' invention concerne un flasque d'étanchéité (60) destiné à être plaqué contre un disque de rotor d'étage de turbine pour turbomachine d'aéronef, le flasque étant équipé d'une pluralité de tenons anti-rotation (66) permettant de bloquer sa rotation relativement au disque de rotor, chaque tenon (66) étant en saillie axialement à partir d'un corps de flasque (63) et présentant deux surfaces opposées d'extrémité circonférentielle (72), respectivement destinées à se situer en regard de deux aubes directement consécutives portées par le disque de rotor. Selon l'invention, au moins l'un des tenons anti-rotation (66) est traversé radialement par une fente (70) s' ouvrant axialement.</description><language>eng ; fre</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>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=20180612&DB=EPODOC&CC=CA&NR=2831522C$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,778,883,25551,76302</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180612&DB=EPODOC&CC=CA&NR=2831522C$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CASALIGGI, PASCAL</creatorcontrib><creatorcontrib>PASQUIET, DIDIER</creatorcontrib><creatorcontrib>POUZET, EMILIE</creatorcontrib><title>SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS</title><description>The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring being equipped with a plurality of anti-rotation pegs (66) for preventing it from rotating in relation to the rotor disc, each peg (66) protruding axially from a ring body (63) and having two opposite circumferential-end surfaces (72) which are intended respectively to be located facing two directly consecutive blades carried on the rotor disc. According to the invention, an axially opening slot (70) passes radially through at least one of the anti-rotation pegs (66).
L' invention concerne un flasque d'étanchéité (60) destiné à être plaqué contre un disque de rotor d'étage de turbine pour turbomachine d'aéronef, le flasque étant équipé d'une pluralité de tenons anti-rotation (66) permettant de bloquer sa rotation relativement au disque de rotor, chaque tenon (66) étant en saillie axialement à partir d'un corps de flasque (63) et présentant deux surfaces opposées d'extrémité circonférentielle (72), respectivement destinées à se situer en regard de deux aubes directement consécutives portées par le disque de rotor. Selon l'invention, au moins l'un des tenons anti-rotation (66) est traversé radialement par une fente (70) s' ouvrant axialement.</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>2018</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNqFyzELwjAQBeAsDqL-Bu8H2MEUwfWMSRpoc-VyzqWUOIkW6v_HVtxd3hve99ZqSBbrED3wEo4YEOTGlxAtJEFvgRxgBAxsGJ18R2rQVLM4gKGm5ZCWb6pJxF5nLKFgEpRAEVrr01at7v1jyrtfb9TeWTFVkcdXl6exH_IzvzuD-lweT1qb8r_4AByBMxU</recordid><startdate>20180612</startdate><enddate>20180612</enddate><creator>CASALIGGI, PASCAL</creator><creator>PASQUIET, DIDIER</creator><creator>POUZET, EMILIE</creator><scope>EVB</scope></search><sort><creationdate>20180612</creationdate><title>SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS</title><author>CASALIGGI, PASCAL ; PASQUIET, DIDIER ; POUZET, EMILIE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2831522C3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2018</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>CASALIGGI, PASCAL</creatorcontrib><creatorcontrib>PASQUIET, DIDIER</creatorcontrib><creatorcontrib>POUZET, EMILIE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>CASALIGGI, PASCAL</au><au>PASQUIET, DIDIER</au><au>POUZET, EMILIE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS</title><date>2018-06-12</date><risdate>2018</risdate><abstract>The invention relates to a sealing ring (60) intended to be pressed against a rotor disc of a turbine stage for an aircraft turbomachine, the ring being equipped with a plurality of anti-rotation pegs (66) for preventing it from rotating in relation to the rotor disc, each peg (66) protruding axially from a ring body (63) and having two opposite circumferential-end surfaces (72) which are intended respectively to be located facing two directly consecutive blades carried on the rotor disc. According to the invention, an axially opening slot (70) passes radially through at least one of the anti-rotation pegs (66).
L' invention concerne un flasque d'étanchéité (60) destiné à être plaqué contre un disque de rotor d'étage de turbine pour turbomachine d'aéronef, le flasque étant équipé d'une pluralité de tenons anti-rotation (66) permettant de bloquer sa rotation relativement au disque de rotor, chaque tenon (66) étant en saillie axialement à partir d'un corps de flasque (63) et présentant deux surfaces opposées d'extrémité circonférentielle (72), respectivement destinées à se situer en regard de deux aubes directement consécutives portées par le disque de rotor. Selon l'invention, au moins l'un des tenons anti-rotation (66) est traversé radialement par une fente (70) s' ouvrant axialement.</abstract><oa>free_for_read</oa></addata></record> |
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| 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 | SEALING RING FOR A TURBINE STAGE OF AN AIRCRAFT TURBOMACHINE, COMPRISING SLOTTED ANTI-ROTATION PEGS |
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