TURBINE ENGINE COMPRISING SUSPENSION MEANS
The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure...
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| creator | LECLERC BENOIT BERNARD RENE GARNAUD QUENTIN MATTHIAS EMMANUEL MOUTON HERVE JEAN ALBERT GLEMAREC GUILLAUME SEIZE GUILHEM |
| description | The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and suspension means (12, 13) of the turbine engine (1), for attaching the turbine engine (1) on a pylon (11) of an aircraft.
本发明涉及一种沿着轴线(X)延伸的涡轮机(1)，所述涡轮机包括：高压主体，所述高压主体具有旋转地联接到高压涡轮(6)的高压压缩机(4)，以及低压主体，所述低压主体包含旋转地联接到低压涡轮(7)的低压压缩机(3)；上游壳体(14)，所述上游壳体位于所述高压压缩机(4)的上游；以及所述涡轮机(1)的悬架构件(12、13)，其预期用于将所述涡轮机(1)附接到飞机吊架(11)。 |
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本发明涉及一种沿着轴线(X)延伸的涡轮机(1)，所述涡轮机包括：高压主体，所述高压主体具有旋转地联接到高压涡轮(6)的高压压缩机(4)，以及低压主体，所述低压主体包含旋转地联接到低压涡轮(7)的低压压缩机(3)；上游壳体(14)，所述上游壳体位于所述高压压缩机(4)的上游；以及所述涡轮机(1)的悬架构件(12、13)，其预期用于将所述涡轮机(1)附接到飞机吊架(11)。</description><language>chi ; eng</language><subject>AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; COSMONAUTICS ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; PARACHUTES ; PERFORMING OPERATIONS ; TRANSPORTING</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=20210514&DB=EPODOC&CC=CN&NR=112805219A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25543,76294</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20210514&DB=EPODOC&CC=CN&NR=112805219A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LECLERC BENOIT BERNARD RENE</creatorcontrib><creatorcontrib>GARNAUD QUENTIN MATTHIAS EMMANUEL</creatorcontrib><creatorcontrib>MOUTON HERVE JEAN ALBERT</creatorcontrib><creatorcontrib>GLEMAREC GUILLAUME</creatorcontrib><creatorcontrib>SEIZE GUILHEM</creatorcontrib><title>TURBINE ENGINE COMPRISING SUSPENSION MEANS</title><description>The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and suspension means (12, 13) of the turbine engine (1), for attaching the turbine engine (1) on a pylon (11) of an aircraft.
本发明涉及一种沿着轴线(X)延伸的涡轮机(1)，所述涡轮机包括：高压主体，所述高压主体具有旋转地联接到高压涡轮(6)的高压压缩机(4)，以及低压主体，所述低压主体包含旋转地联接到低压涡轮(7)的低压压缩机(3)；上游壳体(14)，所述上游壳体位于所述高压压缩机(4)的上游；以及所述涡轮机(1)的悬架构件(12、13)，其预期用于将所述涡轮机(1)附接到飞机吊架(11)。</description><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNAKCQ1y8vRzVXD1cwdRzv6-AUGewZ5-7grBocEBrn7Bnv5-Cr6ujn7BPAysaYk5xam8UJqbQdHNNcTZQze1ID8-tbggMTk1L7Uk3tnP0NDIwsDUyNDS0ZgYNQBsYiTg</recordid><startdate>20210514</startdate><enddate>20210514</enddate><creator>LECLERC BENOIT BERNARD RENE</creator><creator>GARNAUD QUENTIN MATTHIAS EMMANUEL</creator><creator>MOUTON HERVE JEAN ALBERT</creator><creator>GLEMAREC GUILLAUME</creator><creator>SEIZE GUILHEM</creator><scope>EVB</scope></search><sort><creationdate>20210514</creationdate><title>TURBINE ENGINE COMPRISING SUSPENSION MEANS</title><author>LECLERC BENOIT BERNARD RENE ; GARNAUD QUENTIN MATTHIAS EMMANUEL ; MOUTON HERVE JEAN ALBERT ; GLEMAREC GUILLAUME ; SEIZE GUILHEM</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN112805219A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2021</creationdate><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>LECLERC BENOIT BERNARD RENE</creatorcontrib><creatorcontrib>GARNAUD QUENTIN MATTHIAS EMMANUEL</creatorcontrib><creatorcontrib>MOUTON HERVE JEAN ALBERT</creatorcontrib><creatorcontrib>GLEMAREC GUILLAUME</creatorcontrib><creatorcontrib>SEIZE GUILHEM</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LECLERC BENOIT BERNARD RENE</au><au>GARNAUD QUENTIN MATTHIAS EMMANUEL</au><au>MOUTON HERVE JEAN ALBERT</au><au>GLEMAREC GUILLAUME</au><au>SEIZE GUILHEM</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBINE ENGINE COMPRISING SUSPENSION MEANS</title><date>2021-05-14</date><risdate>2021</risdate><abstract>The invention concerns a turbine engine (1) extending along an axis (X), including a high-pressure body comprising a high-pressure compressor (4) coupled to rotate with a high-pressure turbine (6), and a low-pressure body including a low-pressure compressor (3) coupled to rotate with a low-pressure turbine (7), an upstream casing (14) located upstream of the high-pressure compressor (4), and suspension means (12, 13) of the turbine engine (1), for attaching the turbine engine (1) on a pylon (11) of an aircraft.
本发明涉及一种沿着轴线(X)延伸的涡轮机(1)，所述涡轮机包括：高压主体，所述高压主体具有旋转地联接到高压涡轮(6)的高压压缩机(4)，以及低压主体，所述低压主体包含旋转地联接到低压涡轮(7)的低压压缩机(3)；上游壳体(14)，所述上游壳体位于所述高压压缩机(4)的上游；以及所述涡轮机(1)的悬架构件(12、13)，其预期用于将所述涡轮机(1)附接到飞机吊架(11)。</abstract><oa>free_for_read</oa></addata></record> |
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| language | chi ; eng |
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| subjects | AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS PARACHUTES PERFORMING OPERATIONS TRANSPORTING |
| title | TURBINE ENGINE COMPRISING SUSPENSION MEANS |
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