Cárter de escape equipado para turbo reator de fluxo duplo para aeronave e turbo reator de fluxo duplo
suspensão isostática de um turbo reator por duplo suporte traseiro. turbo reator de fluxo duplo que compreende um cárter de escape que apresenta um cubo central (13) e meios de ligação (11) próprios para transmitir os esforços gerados pelo turbo reator à estrutura da aeronave que ele propulsa, os di...
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| creator | MATHIEU ANGE POISSON FRANÇOIS ROBERT BELLABAL GALLET FRANÇOIS |
| description | suspensão isostática de um turbo reator por duplo suporte traseiro. turbo reator de fluxo duplo que compreende um cárter de escape que apresenta um cubo central (13) e meios de ligação (11) próprios para transmitir os esforços gerados pelo turbo reator à estrutura da aeronave que ele propulsa, os ditos meios de ligação sendo dois braços que se estendem radialmente a partir do cubo central para atravessar o fluxo frio do dito turbo reator e sendo caracterizados pelo fato de que eles são rigidamente fixados ao dito cubo central e posicionados de modo diametralmente oposto um em relação ao outro. um meio de ligação suplementar (14) se estende entre o cubo (13) e a zona de fixação (9) do cárter de escape à estrutura (12) da aeronave para transmitir as cargas excepcionais de dimensionamento, o dito meio de ligação sendo, em utilização normal, posicionado em espera, sem transmissão de esforço entre o dito cubo e a dita zona.
The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area. |
| format | Patent |
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The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.</description><language>por</language><subject>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 ; ENGINE PLANTS IN GENERAL ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; PARACHUTES ; PERFORMING OPERATIONS ; STEAM ENGINES ; TRANSPORTING ; WEAPONS</subject><creationdate>2022</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=20220104&DB=EPODOC&CC=BR&NR=112016004104B1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220104&DB=EPODOC&CC=BR&NR=112016004104B1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MATHIEU ANGE POISSON</creatorcontrib><creatorcontrib>FRANÇOIS ROBERT BELLABAL</creatorcontrib><creatorcontrib>GALLET FRANÇOIS</creatorcontrib><title>Cárter de escape equipado para turbo reator de fluxo duplo para aeronave e turbo reator de fluxo duplo</title><description>suspensão isostática de um turbo reator por duplo suporte traseiro. turbo reator de fluxo duplo que compreende um cárter de escape que apresenta um cubo central (13) e meios de ligação (11) próprios para transmitir os esforços gerados pelo turbo reator à estrutura da aeronave que ele propulsa, os ditos meios de ligação sendo dois braços que se estendem radialmente a partir do cubo central para atravessar o fluxo frio do dito turbo reator e sendo caracterizados pelo fato de que eles são rigidamente fixados ao dito cubo central e posicionados de modo diametralmente oposto um em relação ao outro. um meio de ligação suplementar (14) se estende entre o cubo (13) e a zona de fixação (9) do cárter de escape à estrutura (12) da aeronave para transmitir as cargas excepcionais de dimensionamento, o dito meio de ligação sendo, em utilização normal, posicionado em espera, sem transmissão de esforço entre o dito cubo e a dita zona.
The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.</description><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>ENGINE PLANTS IN GENERAL</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</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>MACHINES OR ENGINES IN GENERAL</subject><subject>MECHANICAL ENGINEERING</subject><subject>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>STEAM ENGINES</subject><subject>TRANSPORTING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2022</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZEh3PrywqCS1SCElVSG1ODmxAEgVlmYWJKbkKxQkFiUqlJQWJeUrFKUmluSDFaXllFbkK6SUFuRAFSSmFuXnJZYB9eFTy8PAmpaYU5zKC6W5GVTdXEOcPXRTC_LjU4sLEpNT81JL4p2CDA2NDAzNDAxMDA1MnAyNiVUHANW1QYQ</recordid><startdate>20220104</startdate><enddate>20220104</enddate><creator>MATHIEU ANGE POISSON</creator><creator>FRANÇOIS ROBERT BELLABAL</creator><creator>GALLET FRANÇOIS</creator><scope>EVB</scope></search><sort><creationdate>20220104</creationdate><title>Cárter de escape equipado para turbo reator de fluxo duplo para aeronave e turbo reator de fluxo duplo</title><author>MATHIEU ANGE POISSON ; FRANÇOIS ROBERT BELLABAL ; GALLET FRANÇOIS</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_BR112016004104B13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>por</language><creationdate>2022</creationdate><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>ENGINE PLANTS IN GENERAL</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</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>MACHINES OR ENGINES IN GENERAL</topic><topic>MECHANICAL ENGINEERING</topic><topic>NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>STEAM ENGINES</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MATHIEU ANGE POISSON</creatorcontrib><creatorcontrib>FRANÇOIS ROBERT BELLABAL</creatorcontrib><creatorcontrib>GALLET FRANÇOIS</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MATHIEU ANGE POISSON</au><au>FRANÇOIS ROBERT BELLABAL</au><au>GALLET FRANÇOIS</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Cárter de escape equipado para turbo reator de fluxo duplo para aeronave e turbo reator de fluxo duplo</title><date>2022-01-04</date><risdate>2022</risdate><abstract>suspensão isostática de um turbo reator por duplo suporte traseiro. turbo reator de fluxo duplo que compreende um cárter de escape que apresenta um cubo central (13) e meios de ligação (11) próprios para transmitir os esforços gerados pelo turbo reator à estrutura da aeronave que ele propulsa, os ditos meios de ligação sendo dois braços que se estendem radialmente a partir do cubo central para atravessar o fluxo frio do dito turbo reator e sendo caracterizados pelo fato de que eles são rigidamente fixados ao dito cubo central e posicionados de modo diametralmente oposto um em relação ao outro. um meio de ligação suplementar (14) se estende entre o cubo (13) e a zona de fixação (9) do cárter de escape à estrutura (12) da aeronave para transmitir as cargas excepcionais de dimensionamento, o dito meio de ligação sendo, em utilização normal, posicionado em espera, sem transmissão de esforço entre o dito cubo e a dita zona.
The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | 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 ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS |
| title | Cárter de escape equipado para turbo reator de fluxo duplo para aeronave e turbo reator de fluxo duplo |
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