AIR INFLOW LIP FOR TURBOJET NACELLE
The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic treatment device; and a pneumatic de-icing device comprising a d...
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| creator | BEHAGHEL PIERRE-FRANCOIS BOILEAU PATRICK COAT-LENZOTTI CAROLINE VERSAEVEL MARC DIGEOS VIRGINIE EMMANUELLE ANNE MARIE |
| description | The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic treatment device; and a pneumatic de-icing device comprising a de-icing fluid supply device. The invention is characterised in that the inner wall (23) of the lip comprises a plurality of acoustic boreholes (28) and in that the pneumatic de-icing device comprises a honeycombed de-icing plate (27) mounted inside said cavity on said inner wall (23) of the lip andcomprising a plurality of conduits (35) for the circulation of a de-icing fluid and a plurality of acoustic wells communicating with said acoustic boreholes (28).
本发明涉及一种用于飞行器的涡轮喷气发动机的机舱的进气唇缘，包括由机舱的前缘和环形壁限定的空腔，所述进气唇缘包括：内壁(23)；声学处理装置；以及包括除冰流体供应装置的气动除冰装置。本发明的特征在于，唇缘的内壁(23)包括多个声学孔(28)，并且在于气动除冰装置包括蜂窝状除冰板(27)，该除冰板安装在唇缘的所述内壁(23)上的所述空腔内，并且包括用于除冰流体的循环的多个管道(35)和与所述声学钻孔(28)连通的多个声学井。 |
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本发明涉及一种用于飞行器的涡轮喷气发动机的机舱的进气唇缘，包括由机舱的前缘和环形壁限定的空腔，所述进气唇缘包括：内壁(23)；声学处理装置；以及包括除冰流体供应装置的气动除冰装置。本发明的特征在于，唇缘的内壁(23)包括多个声学孔(28)，并且在于气动除冰装置包括蜂窝状除冰板(27)，该除冰板安装在唇缘的所述内壁(23)上的所述空腔内，并且包括用于除冰流体的循环的多个管道(35)和与所述声学钻孔(28)连通的多个声学井。</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>2020</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=20200728&DB=EPODOC&CC=CN&NR=111465557A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76290</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200728&DB=EPODOC&CC=CN&NR=111465557A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>BEHAGHEL PIERRE-FRANCOIS</creatorcontrib><creatorcontrib>BOILEAU PATRICK</creatorcontrib><creatorcontrib>COAT-LENZOTTI CAROLINE</creatorcontrib><creatorcontrib>VERSAEVEL MARC</creatorcontrib><creatorcontrib>DIGEOS VIRGINIE EMMANUELLE ANNE MARIE</creatorcontrib><title>AIR INFLOW LIP FOR TURBOJET NACELLE</title><description>The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic treatment device; and a pneumatic de-icing device comprising a de-icing fluid supply device. The invention is characterised in that the inner wall (23) of the lip comprises a plurality of acoustic boreholes (28) and in that the pneumatic de-icing device comprises a honeycombed de-icing plate (27) mounted inside said cavity on said inner wall (23) of the lip andcomprising a plurality of conduits (35) for the circulation of a de-icing fluid and a plurality of acoustic wells communicating with said acoustic boreholes (28).
本发明涉及一种用于飞行器的涡轮喷气发动机的机舱的进气唇缘，包括由机舱的前缘和环形壁限定的空腔，所述进气唇缘包括：内壁(23)；声学处理装置；以及包括除冰流体供应装置的气动除冰装置。本发明的特征在于，唇缘的内壁(23)包括多个声学孔(28)，并且在于气动除冰装置包括蜂窝状除冰板(27)，该除冰板安装在唇缘的所述内壁(23)上的所述空腔内，并且包括用于除冰流体的循环的多个管道(35)和与所述声学钻孔(28)连通的多个声学井。</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>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFB29AxS8PRz8_EPV_DxDFBw8w9SCAkNcvL3cg1R8HN0dvXxceVhYE1LzClO5YXS3AyKbq4hzh66qQX58anFBYnJqXmpJfHOfoaGhiZmpqam5o7GxKgBAETyIoo</recordid><startdate>20200728</startdate><enddate>20200728</enddate><creator>BEHAGHEL PIERRE-FRANCOIS</creator><creator>BOILEAU PATRICK</creator><creator>COAT-LENZOTTI CAROLINE</creator><creator>VERSAEVEL MARC</creator><creator>DIGEOS VIRGINIE EMMANUELLE ANNE MARIE</creator><scope>EVB</scope></search><sort><creationdate>20200728</creationdate><title>AIR INFLOW LIP FOR TURBOJET NACELLE</title><author>BEHAGHEL PIERRE-FRANCOIS ; BOILEAU PATRICK ; COAT-LENZOTTI CAROLINE ; VERSAEVEL MARC ; DIGEOS VIRGINIE EMMANUELLE ANNE MARIE</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CN111465557A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>chi ; eng</language><creationdate>2020</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>BEHAGHEL PIERRE-FRANCOIS</creatorcontrib><creatorcontrib>BOILEAU PATRICK</creatorcontrib><creatorcontrib>COAT-LENZOTTI CAROLINE</creatorcontrib><creatorcontrib>VERSAEVEL MARC</creatorcontrib><creatorcontrib>DIGEOS VIRGINIE EMMANUELLE ANNE MARIE</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>BEHAGHEL PIERRE-FRANCOIS</au><au>BOILEAU PATRICK</au><au>COAT-LENZOTTI CAROLINE</au><au>VERSAEVEL MARC</au><au>DIGEOS VIRGINIE EMMANUELLE ANNE MARIE</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>AIR INFLOW LIP FOR TURBOJET NACELLE</title><date>2020-07-28</date><risdate>2020</risdate><abstract>The invention relates to an air inflow lip of a nacelle for a turbojet of an aircraft, comprising a cavity defined by a leading edge of the nacelle and by an annular wall, said air inflow lip comprising: an inner wall (23); an acoustic treatment device; and a pneumatic de-icing device comprising a de-icing fluid supply device. The invention is characterised in that the inner wall (23) of the lip comprises a plurality of acoustic boreholes (28) and in that the pneumatic de-icing device comprises a honeycombed de-icing plate (27) mounted inside said cavity on said inner wall (23) of the lip andcomprising a plurality of conduits (35) for the circulation of a de-icing fluid and a plurality of acoustic wells communicating with said acoustic boreholes (28).
本发明涉及一种用于飞行器的涡轮喷气发动机的机舱的进气唇缘，包括由机舱的前缘和环形壁限定的空腔，所述进气唇缘包括：内壁(23)；声学处理装置；以及包括除冰流体供应装置的气动除冰装置。本发明的特征在于，唇缘的内壁(23)包括多个声学孔(28)，并且在于气动除冰装置包括蜂窝状除冰板(27)，该除冰板安装在唇缘的所述内壁(23)上的所述空腔内，并且包括用于除冰流体的循环的多个管道(35)和与所述声学钻孔(28)连通的多个声学井。</abstract><oa>free_for_read</oa></addata></record> |
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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 | AIR INFLOW LIP FOR TURBOJET NACELLE |
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