REDUCTION GEAR HAVING AN EPICYCLIC GEAR TRAIN FOR A TURBINE ENGINE
The invention relates to a reduction gear (11) having an epicyclic gear train for a turbine engine (1), in particular of an aircraft, comprising: a planetary shaft (15) having an axis of rotation A; a ring gear (19) having an axis A extending around said planetary shaft (15); planet gears (18) distr...
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| creator | BELMONTE, OLIVIER LAO, JEREMY PHORLA NGUYEN VAN, THOMAS JULIEN PATSOURIS, EMMANUEL PIERRE DIMITRI MOUTON, CLEMENTINE CHARLOTTE MARIE |
| description | The invention relates to a reduction gear (11) having an epicyclic gear train for a turbine engine (1), in particular of an aircraft, comprising: a planetary shaft (15) having an axis of rotation A; a ring gear (19) having an axis A extending around said planetary shaft (15); planet gears (18) distributed around said axis A, which mesh with said ring gear (19) and the planetary shaft (15); and a planet carrier including members (21) for supporting bearings (23a, 23b) of the planet gears (18a, 18b), having axes of rotation B, which are evenly distributed around the axis A, as well as a part (38) holding each supporting member (21) substantially by the middle thereof along the axis B thereof, characterised in that said supporting members (21) are made as a single part having means (45, 46, 41) for supplying lubricating oil to said bearings (23a, 23b). The invention also relates to a method for assembling said reduction gear.
L'invention concerne un réducteur (11) à train épicycloïdal pour une turbomachine (1), en particulier d'aéronef, comportant un arbre planétaire (15) d'axe A de rotation, une couronne (19) d'axe A s'étendant autour dudit arbre planétaire (15), des satellites (18) répartis autour dudit axe A, qui sont engrenés avec ladite couronne (19) et l'arbre planétaire (15), et un support-satellites comprenant, d'une part, des organes de support (21) de paliers (23a, 23b) des satellites (18a, 18b), d'axes de rotation B, qui sont régulièrement répartis autour de l'axe A, et d'autre part, une pièce (38) maintenant chaque organe de support (21) sensiblement par son milieu suivant son axe B, caractérisé en ce que lesdits organes (21) de support sont formés d'une seule pièce avec des moyens (45, 46, 41) d'alimentation en huile de lubrification desdits paliers (23a, 23b). Elle concerne également un procédé d'assemblage dudit réducteur. |
| format | Patent |
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L'invention concerne un réducteur (11) à train épicycloïdal pour une turbomachine (1), en particulier d'aéronef, comportant un arbre planétaire (15) d'axe A de rotation, une couronne (19) d'axe A s'étendant autour dudit arbre planétaire (15), des satellites (18) répartis autour dudit axe A, qui sont engrenés avec ladite couronne (19) et l'arbre planétaire (15), et un support-satellites comprenant, d'une part, des organes de support (21) de paliers (23a, 23b) des satellites (18a, 18b), d'axes de rotation B, qui sont régulièrement répartis autour de l'axe A, et d'autre part, une pièce (38) maintenant chaque organe de support (21) sensiblement par son milieu suivant son axe B, caractérisé en ce que lesdits organes (21) de support sont formés d'une seule pièce avec des moyens (45, 46, 41) d'alimentation en huile de lubrification desdits paliers (23a, 23b). Elle concerne également un procédé d'assemblage dudit réducteur.</description><language>eng ; fre</language><subject>AEROPLANES ; AIR INTAKES FOR JET-PROPULSION PLANTS ; AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; COSMONAUTICS ; ENGINEERING ELEMENTS AND UNITS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GAS-TURBINE PLANTS ; GEARING ; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS ; HEATING ; HELICOPTERS ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; PARACHUTES ; PERFORMING OPERATIONS ; THERMAL INSULATION IN GENERAL ; TRANSPORTING ; 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&date=20230718&DB=EPODOC&CC=CA&NR=2982888C$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76293</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20230718&DB=EPODOC&CC=CA&NR=2982888C$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BELMONTE, OLIVIER</creatorcontrib><creatorcontrib>LAO, JEREMY PHORLA</creatorcontrib><creatorcontrib>NGUYEN VAN, THOMAS JULIEN</creatorcontrib><creatorcontrib>PATSOURIS, EMMANUEL PIERRE DIMITRI</creatorcontrib><creatorcontrib>MOUTON, CLEMENTINE CHARLOTTE MARIE</creatorcontrib><title>REDUCTION GEAR HAVING AN EPICYCLIC GEAR TRAIN FOR A TURBINE ENGINE</title><description>The invention relates to a reduction gear (11) having an epicyclic gear train for a turbine engine (1), in particular of an aircraft, comprising: a planetary shaft (15) having an axis of rotation A; a ring gear (19) having an axis A extending around said planetary shaft (15); planet gears (18) distributed around said axis A, which mesh with said ring gear (19) and the planetary shaft (15); and a planet carrier including members (21) for supporting bearings (23a, 23b) of the planet gears (18a, 18b), having axes of rotation B, which are evenly distributed around the axis A, as well as a part (38) holding each supporting member (21) substantially by the middle thereof along the axis B thereof, characterised in that said supporting members (21) are made as a single part having means (45, 46, 41) for supplying lubricating oil to said bearings (23a, 23b). The invention also relates to a method for assembling said reduction gear.
L'invention concerne un réducteur (11) à train épicycloïdal pour une turbomachine (1), en particulier d'aéronef, comportant un arbre planétaire (15) d'axe A de rotation, une couronne (19) d'axe A s'étendant autour dudit arbre planétaire (15), des satellites (18) répartis autour dudit axe A, qui sont engrenés avec ladite couronne (19) et l'arbre planétaire (15), et un support-satellites comprenant, d'une part, des organes de support (21) de paliers (23a, 23b) des satellites (18a, 18b), d'axes de rotation B, qui sont régulièrement répartis autour de l'axe A, et d'autre part, une pièce (38) maintenant chaque organe de support (21) sensiblement par son milieu suivant son axe B, caractérisé en ce que lesdits organes (21) de support sont formés d'une seule pièce avec des moyens (45, 46, 41) d'alimentation en huile de lubrification desdits paliers (23a, 23b). Elle concerne également un procédé d'assemblage dudit réducteur.</description><subject>AEROPLANES</subject><subject>AIR INTAKES FOR JET-PROPULSION PLANTS</subject><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</subject><subject>COSMONAUTICS</subject><subject>ENGINEERING ELEMENTS AND UNITS</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</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>HELICOPTERS</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>THERMAL INSULATION IN GENERAL</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2023</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZHAKcnUJdQ7x9PdTcHd1DFLwcAzz9HNXcPRTcA3wdI509vF0hkiEBDl6-im4-QcpOCqEhAY5efq5Krj6uQMpHgbWtMSc4lReKM3NIO_mGuLsoZtakB-fWlyQmJyal1oS7-xoZGlhZGFh4WxMWAUAIQ8p6g</recordid><startdate>20230718</startdate><enddate>20230718</enddate><creator>BELMONTE, OLIVIER</creator><creator>LAO, JEREMY PHORLA</creator><creator>NGUYEN VAN, THOMAS JULIEN</creator><creator>PATSOURIS, EMMANUEL PIERRE DIMITRI</creator><creator>MOUTON, CLEMENTINE CHARLOTTE MARIE</creator><scope>EVB</scope></search><sort><creationdate>20230718</creationdate><title>REDUCTION GEAR HAVING AN EPICYCLIC GEAR TRAIN FOR A TURBINE ENGINE</title><author>BELMONTE, OLIVIER ; LAO, JEREMY PHORLA ; NGUYEN VAN, THOMAS JULIEN ; PATSOURIS, EMMANUEL PIERRE DIMITRI ; MOUTON, CLEMENTINE CHARLOTTE MARIE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2982888C3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</language><creationdate>2023</creationdate><topic>AEROPLANES</topic><topic>AIR INTAKES FOR JET-PROPULSION PLANTS</topic><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS</topic><topic>COSMONAUTICS</topic><topic>ENGINEERING ELEMENTS AND UNITS</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</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>HELICOPTERS</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>THERMAL INSULATION IN GENERAL</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>BELMONTE, OLIVIER</creatorcontrib><creatorcontrib>LAO, JEREMY PHORLA</creatorcontrib><creatorcontrib>NGUYEN VAN, THOMAS JULIEN</creatorcontrib><creatorcontrib>PATSOURIS, EMMANUEL PIERRE DIMITRI</creatorcontrib><creatorcontrib>MOUTON, CLEMENTINE CHARLOTTE MARIE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BELMONTE, OLIVIER</au><au>LAO, JEREMY PHORLA</au><au>NGUYEN VAN, THOMAS JULIEN</au><au>PATSOURIS, EMMANUEL PIERRE DIMITRI</au><au>MOUTON, CLEMENTINE CHARLOTTE MARIE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>REDUCTION GEAR HAVING AN EPICYCLIC GEAR TRAIN FOR A TURBINE ENGINE</title><date>2023-07-18</date><risdate>2023</risdate><abstract>The invention relates to a reduction gear (11) having an epicyclic gear train for a turbine engine (1), in particular of an aircraft, comprising: a planetary shaft (15) having an axis of rotation A; a ring gear (19) having an axis A extending around said planetary shaft (15); planet gears (18) distributed around said axis A, which mesh with said ring gear (19) and the planetary shaft (15); and a planet carrier including members (21) for supporting bearings (23a, 23b) of the planet gears (18a, 18b), having axes of rotation B, which are evenly distributed around the axis A, as well as a part (38) holding each supporting member (21) substantially by the middle thereof along the axis B thereof, characterised in that said supporting members (21) are made as a single part having means (45, 46, 41) for supplying lubricating oil to said bearings (23a, 23b). The invention also relates to a method for assembling said reduction gear.
L'invention concerne un réducteur (11) à train épicycloïdal pour une turbomachine (1), en particulier d'aéronef, comportant un arbre planétaire (15) d'axe A de rotation, une couronne (19) d'axe A s'étendant autour dudit arbre planétaire (15), des satellites (18) répartis autour dudit axe A, qui sont engrenés avec ladite couronne (19) et l'arbre planétaire (15), et un support-satellites comprenant, d'une part, des organes de support (21) de paliers (23a, 23b) des satellites (18a, 18b), d'axes de rotation B, qui sont régulièrement répartis autour de l'axe A, et d'autre part, une pièce (38) maintenant chaque organe de support (21) sensiblement par son milieu suivant son axe B, caractérisé en ce que lesdits organes (21) de support sont formés d'une seule pièce avec des moyens (45, 46, 41) d'alimentation en huile de lubrification desdits paliers (23a, 23b). Elle concerne également un procédé d'assemblage dudit réducteur.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINEERING ELEMENTS AND UNITS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS THERMAL INSULATION IN GENERAL TRANSPORTING WEAPONS |
| title | REDUCTION GEAR HAVING AN EPICYCLIC GEAR TRAIN FOR A TURBINE ENGINE |
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