AIRCRAFT TURBINE ENGINE WITH AT LEAST TWO BODIES AND MEANS FOR DRAWING POWER
Aircraft turbine engine (10), said turbine engine comprising at least a low-pressure body (12a) and a high-pressure body (12b), as well as means (54) for drawing power on said low-pressure body, said means comprising a first shaft (54a) for drawing power, the radially inner end of said first shaft b...
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| creator | GUILLOTEL, LOIC PAUL YVES CHARIER, GILLES ALAIN MARIE FRANTZ, CAROLINE MARIE MILLIER, VINCENT FRANCOIS GEORGES |
| description | Aircraft turbine engine (10), said turbine engine comprising at least a low-pressure body (12a) and a high-pressure body (12b), as well as means (54) for drawing power on said low-pressure body, said means comprising a first shaft (54a) for drawing power, the radially inner end of said first shaft bearing a first bevel gear (54b) meshed with a first idler bevel wheel (54c) driven by the low-pressure body, the turbine engine further comprising a first annular bearing support (76) which extends about an axis and is rigidly connected to a stator. The invention is characterised in that the first bearing support comprises a first substantially cylindrical portion (76b) which extends coaxially with a second substantially cylindrical portion (54ca) of the idler wheel, said first and second portions being guided one inside the other by bearings (78, 80), and the idler wheel is driven by the low-pressure body by means of an annular damping piece (86, 86) which is independent of the first bearing support.
Turbomachine (10) d'aéronef, cette turbomachine comportant au moins un corps basse pression (12a) et un corps haute pression (12b), ainsi que des moyens (54) de prélèvement de puissance sur ledit corps basse pression, qui comportent un premier arbre (54a) de prélèvement de puissance dont une extrémité radialement interne porte un premier pignon conique (54b) engrené avec une première roue conique de renvoi (54c) entraînée par ledit corps basse pression, la turbomachine comportant en outre un premier support annulaire de palier (76) s'étendant autour dudit axe et solidaire d'un stator, caractérisée en ce que ledit premier support de palier comprend une première portion (76b) sensiblement cylindrique qui s'étend coaxialement à une seconde portion (54ca) sensiblement cylindrique de ladite roue de renvoi, ces première et seconde portions étant guidées l'une à l'intérieur de l'autre par des paliers (78, 80), et ladite roue de renvoi est entraînée par ledit corps basse pression par l'intermédiaire d'une pièce annulaire d'amortissement (86, 86) qui est indépendante dudit premier support de palier. |
| format | Patent |
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Turbomachine (10) d'aéronef, cette turbomachine comportant au moins un corps basse pression (12a) et un corps haute pression (12b), ainsi que des moyens (54) de prélèvement de puissance sur ledit corps basse pression, qui comportent un premier arbre (54a) de prélèvement de puissance dont une extrémité radialement interne porte un premier pignon conique (54b) engrené avec une première roue conique de renvoi (54c) entraînée par ledit corps basse pression, la turbomachine comportant en outre un premier support annulaire de palier (76) s'étendant autour dudit axe et solidaire d'un stator, caractérisée en ce que ledit premier support de palier comprend une première portion (76b) sensiblement cylindrique qui s'étend coaxialement à une seconde portion (54ca) sensiblement cylindrique de ladite roue de renvoi, ces première et seconde portions étant guidées l'une à l'intérieur de l'autre par des paliers (78, 80), et ladite roue de renvoi est entraînée par ledit corps basse pression par l'intermédiaire d'une pièce annulaire d'amortissement (86, 86) qui est indépendante dudit premier support de palier.</description><language>eng ; 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>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=20191226&DB=EPODOC&CC=CA&NR=3103855A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20191226&DB=EPODOC&CC=CA&NR=3103855A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>GUILLOTEL, LOIC PAUL YVES</creatorcontrib><creatorcontrib>CHARIER, GILLES ALAIN MARIE</creatorcontrib><creatorcontrib>FRANTZ, CAROLINE MARIE</creatorcontrib><creatorcontrib>MILLIER, VINCENT FRANCOIS GEORGES</creatorcontrib><title>AIRCRAFT TURBINE ENGINE WITH AT LEAST TWO BODIES AND MEANS FOR DRAWING POWER</title><description>Aircraft turbine engine (10), said turbine engine comprising at least a low-pressure body (12a) and a high-pressure body (12b), as well as means (54) for drawing power on said low-pressure body, said means comprising a first shaft (54a) for drawing power, the radially inner end of said first shaft bearing a first bevel gear (54b) meshed with a first idler bevel wheel (54c) driven by the low-pressure body, the turbine engine further comprising a first annular bearing support (76) which extends about an axis and is rigidly connected to a stator. The invention is characterised in that the first bearing support comprises a first substantially cylindrical portion (76b) which extends coaxially with a second substantially cylindrical portion (54ca) of the idler wheel, said first and second portions being guided one inside the other by bearings (78, 80), and the idler wheel is driven by the low-pressure body by means of an annular damping piece (86, 86) which is independent of the first bearing support.
Turbomachine (10) d'aéronef, cette turbomachine comportant au moins un corps basse pression (12a) et un corps haute pression (12b), ainsi que des moyens (54) de prélèvement de puissance sur ledit corps basse pression, qui comportent un premier arbre (54a) de prélèvement de puissance dont une extrémité radialement interne porte un premier pignon conique (54b) engrené avec une première roue conique de renvoi (54c) entraînée par ledit corps basse pression, la turbomachine comportant en outre un premier support annulaire de palier (76) s'étendant autour dudit axe et solidaire d'un stator, caractérisée en ce que ledit premier support de palier comprend une première portion (76b) sensiblement cylindrique qui s'étend coaxialement à une seconde portion (54ca) sensiblement cylindrique de ladite roue de renvoi, ces première et seconde portions étant guidées l'une à l'intérieur de l'autre par des paliers (78, 80), et ladite roue de renvoi est entraînée par ledit corps basse pression par l'intermédiaire d'une pièce annulaire d'amortissement (86, 86) qui est indépendante dudit premier support de palier.</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>2019</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPBx9AxyDnJ0C1EICQ1y8vRzVXD1cwdR4Z4hHgqOIQo-ro7BQMlwfwUnfxdP12AFRz8XBV9XR79gBTf_IAWXIMdwTz93hQD_cNcgHgbWtMSc4lReKM3NoODmGuLsoZtakB-fWlyQmJyal1oS7-xobGhgbGFq6mhoTIQSADAvLQc</recordid><startdate>20191226</startdate><enddate>20191226</enddate><creator>GUILLOTEL, LOIC PAUL YVES</creator><creator>CHARIER, GILLES ALAIN MARIE</creator><creator>FRANTZ, CAROLINE MARIE</creator><creator>MILLIER, VINCENT FRANCOIS GEORGES</creator><scope>EVB</scope></search><sort><creationdate>20191226</creationdate><title>AIRCRAFT TURBINE ENGINE WITH AT LEAST TWO BODIES AND MEANS FOR DRAWING POWER</title><author>GUILLOTEL, LOIC PAUL YVES ; CHARIER, GILLES ALAIN MARIE ; FRANTZ, CAROLINE MARIE ; MILLIER, VINCENT FRANCOIS GEORGES</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA3103855A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</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>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>GUILLOTEL, LOIC PAUL YVES</creatorcontrib><creatorcontrib>CHARIER, GILLES ALAIN MARIE</creatorcontrib><creatorcontrib>FRANTZ, CAROLINE MARIE</creatorcontrib><creatorcontrib>MILLIER, VINCENT FRANCOIS GEORGES</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>GUILLOTEL, LOIC PAUL YVES</au><au>CHARIER, GILLES ALAIN MARIE</au><au>FRANTZ, CAROLINE MARIE</au><au>MILLIER, VINCENT FRANCOIS GEORGES</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT TURBINE ENGINE WITH AT LEAST TWO BODIES AND MEANS FOR DRAWING POWER</title><date>2019-12-26</date><risdate>2019</risdate><abstract>Aircraft turbine engine (10), said turbine engine comprising at least a low-pressure body (12a) and a high-pressure body (12b), as well as means (54) for drawing power on said low-pressure body, said means comprising a first shaft (54a) for drawing power, the radially inner end of said first shaft bearing a first bevel gear (54b) meshed with a first idler bevel wheel (54c) driven by the low-pressure body, the turbine engine further comprising a first annular bearing support (76) which extends about an axis and is rigidly connected to a stator. The invention is characterised in that the first bearing support comprises a first substantially cylindrical portion (76b) which extends coaxially with a second substantially cylindrical portion (54ca) of the idler wheel, said first and second portions being guided one inside the other by bearings (78, 80), and the idler wheel is driven by the low-pressure body by means of an annular damping piece (86, 86) which is independent of the first bearing support.
Turbomachine (10) d'aéronef, cette turbomachine comportant au moins un corps basse pression (12a) et un corps haute pression (12b), ainsi que des moyens (54) de prélèvement de puissance sur ledit corps basse pression, qui comportent un premier arbre (54a) de prélèvement de puissance dont une extrémité radialement interne porte un premier pignon conique (54b) engrené avec une première roue conique de renvoi (54c) entraînée par ledit corps basse pression, la turbomachine comportant en outre un premier support annulaire de palier (76) s'étendant autour dudit axe et solidaire d'un stator, caractérisée en ce que ledit premier support de palier comprend une première portion (76b) sensiblement cylindrique qui s'étend coaxialement à une seconde portion (54ca) sensiblement cylindrique de ladite roue de renvoi, ces première et seconde portions étant guidées l'une à l'intérieur de l'autre par des paliers (78, 80), et ladite roue de renvoi est entraînée par ledit corps basse pression par l'intermédiaire d'une pièce annulaire d'amortissement (86, 86) qui est indépendante dudit premier support de palier.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre |
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| 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 | AIRCRAFT TURBINE ENGINE WITH AT LEAST TWO BODIES AND MEANS FOR DRAWING POWER |
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