AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET
The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11). The second shaft (16) is rotated by a third shaft (9) of a turbine, and the first shaft (10) is guided in rotation with respe...
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| creator | BRAULT MICHEL GILBERT ROLAND MORREALE SERGE RENE VERDIER MARION JEANNE PIERRETTE BENSLAMA YANIS CUVILLIER ROMAIN GUILLAUME |
| description | The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11). The second shaft (16) is rotated by a third shaft (9) of a turbine, and the first shaft (10) is guided in rotation with respect to a fixed structure (12) via a first bearing (17) and a second bearing (18) placed upstream of the speed reduction gearset (11). The turbomachine is characterised in that the second shaft (16) is guided in rotation with respect to the first shaft (10) via a third, rolling bearing (19) placed upstream of the speed reduction gearset (11), and the third, rolling bearing (19) comprises an outer ring housed in the first shaft (10), an inner ring connected to the second shaft (16) and rolling elements arranged between the inner and outer rings.
本发明涉及一种涡轮机(1)，该涡轮机包括单个函道风扇(2)，该单个函道风扇包括由第二轴(16)经由减速齿轮组(11)旋转的第一轴(10)，第二轴(16)由涡轮的第三轴(9)旋转，第一轴(10)经由位于减速齿轮组(11)上游的第一轴承(17)和第二轴承(18)相对于固定结构(12)被旋转地引导，其特征在于，第二轴(16)经由位于减速齿轮组(11)上游 |
| format | Patent |
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本发明涉及一种涡轮机(1)，该涡轮机包括单个函道风扇(2)，该单个函道风扇包括由第二轴(16)经由减速齿轮组(11)旋转的第一轴(10)，第二轴(16)由涡轮的第三轴(9)旋转，第一轴(10)经由位于减速齿轮组(11)上游的第一轴承(17)和第二轴承(18)相对于固定结构(12)被旋转地引导，其特征在于，第二轴(16)经由位于减速齿轮组(11)上游</description><language>chi ; eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2021</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=20210507&DB=EPODOC&CC=CN&NR=112771261A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210507&DB=EPODOC&CC=CN&NR=112771261A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BRAULT MICHEL GILBERT ROLAND</creatorcontrib><creatorcontrib>MORREALE SERGE RENE</creatorcontrib><creatorcontrib>VERDIER MARION JEANNE PIERRETTE</creatorcontrib><creatorcontrib>BENSLAMA YANIS</creatorcontrib><creatorcontrib>CUVILLIER ROMAIN GUILLAUME</creatorcontrib><title>AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET</title><description>The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11). The second shaft (16) is rotated by a third shaft (9) of a turbine, and the first shaft (10) is guided in rotation with respect to a fixed structure (12) via a first bearing (17) and a second bearing (18) placed upstream of the speed reduction gearset (11). The turbomachine is characterised in that the second shaft (16) is guided in rotation with respect to the first shaft (10) via a third, rolling bearing (19) placed upstream of the speed reduction gearset (11), and the third, rolling bearing (19) comprises an outer ring housed in the first shaft (10), an inner ring connected to the second shaft (16) and rolling elements arranged between the inner and outer rings.
本发明涉及一种涡轮机(1)，该涡轮机包括单个函道风扇(2)，该单个函道风扇包括由第二轴(16)经由减速齿轮组(11)旋转的第一轴(10)，第二轴(16)由涡轮的第三轴(9)旋转，第一轴(10)经由位于减速齿轮组(11)上游的第一轴承(17)和第二轴承(18)相对于固定结构(12)被旋转地引导，其特征在于，第二轴(16)经由位于减速齿轮组(11)上游</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>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNBx9AxyDnJ0C1EICQ1y8vd1dPbw9HNVCPcM8VAIcnUJdQ7x9PdTcHd1DAp2DeFhYE1LzClO5YXS3AyKbq4hzh66qQX58anFBYnJqXmpJfHOfoaGRubmhkZmho7GxKgBAKiWJUw</recordid><startdate>20210507</startdate><enddate>20210507</enddate><creator>BRAULT MICHEL GILBERT ROLAND</creator><creator>MORREALE SERGE RENE</creator><creator>VERDIER MARION JEANNE PIERRETTE</creator><creator>BENSLAMA YANIS</creator><creator>CUVILLIER ROMAIN GUILLAUME</creator><scope>EVB</scope></search><sort><creationdate>20210507</creationdate><title>AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET</title><author>BRAULT MICHEL GILBERT ROLAND ; MORREALE SERGE RENE ; VERDIER MARION JEANNE PIERRETTE ; BENSLAMA YANIS ; CUVILLIER ROMAIN GUILLAUME</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN112771261A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2021</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>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>BRAULT MICHEL GILBERT ROLAND</creatorcontrib><creatorcontrib>MORREALE SERGE RENE</creatorcontrib><creatorcontrib>VERDIER MARION JEANNE PIERRETTE</creatorcontrib><creatorcontrib>BENSLAMA YANIS</creatorcontrib><creatorcontrib>CUVILLIER ROMAIN GUILLAUME</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BRAULT MICHEL GILBERT ROLAND</au><au>MORREALE SERGE RENE</au><au>VERDIER MARION JEANNE PIERRETTE</au><au>BENSLAMA YANIS</au><au>CUVILLIER ROMAIN GUILLAUME</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET</title><date>2021-05-07</date><risdate>2021</risdate><abstract>The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11). The second shaft (16) is rotated by a third shaft (9) of a turbine, and the first shaft (10) is guided in rotation with respect to a fixed structure (12) via a first bearing (17) and a second bearing (18) placed upstream of the speed reduction gearset (11). The turbomachine is characterised in that the second shaft (16) is guided in rotation with respect to the first shaft (10) via a third, rolling bearing (19) placed upstream of the speed reduction gearset (11), and the third, rolling bearing (19) comprises an outer ring housed in the first shaft (10), an inner ring connected to the second shaft (16) and rolling elements arranged between the inner and outer rings.
本发明涉及一种涡轮机(1)，该涡轮机包括单个函道风扇(2)，该单个函道风扇包括由第二轴(16)经由减速齿轮组(11)旋转的第一轴(10)，第二轴(16)由涡轮的第三轴(9)旋转，第一轴(10)经由位于减速齿轮组(11)上游的第一轴承(17)和第二轴承(18)相对于固定结构(12)被旋转地引导，其特征在于，第二轴(16)经由位于减速齿轮组(11)上游</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
| recordid | cdi_epo_espacenet_CN112771261A |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS |
| title | AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET |
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