TURBINE CASING MADE OF TWO MATERIALS
The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring se...
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| creator | MADEC, ALAIN PAUL GARIN, FABRICE MARCEL NOEL LESAINE, JEAN-MARC MICHEL BON, FLORENCE VALERIE CAMEAU, JEROME ETIENNE ROBERT |
| description | The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterised in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
Linvention propose un carter (30) de turbine (16) conçu pour soutenir un ensemble de secteurs annulaires (28), qui délimite partiellement un canal pour le passage dun flux de gaz dans la turbine (16). Le carter (30) comprend un moyen dajustement dynamique de la position radiale des secteurs annulaires (28) au moyen dune injection contrôlée dun débit dair sur les parties (36) dune paroi annulaire (34) du carter (30). Le carter (30) comprend une languette radiale en amont (38), qui raccorde une extrémité en amont de chaque secteur annulaire (28) dans le sens de circulation du flux de gaz au carter (30) et une languette radiale en aval (40), qui raccorde une extrémité en aval de chaque secteur annulaire (28) au carter (30), les languettes radiales en amont et en aval (38, 40) étant faites dune seule avec le carter (30) et étant faites de deux parties (42, 44) de matériaux différents. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_CA2857869C</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>CA2857869C</sourcerecordid><originalsourceid>FETCH-epo_espacenet_CA2857869C3</originalsourceid><addsrcrecordid>eNrjZFAJCQ1y8vRzVXB2DPb0c1fwdXRxVfB3UwgJ9weyQ1yDPB19gnkYWNMSc4pTeaE0N4O8m2uIs4duakF-fGpxQWJyal5qSbyzo5GFqbmFmaWzMWEVAODSIgE</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>TURBINE CASING MADE OF TWO MATERIALS</title><source>esp@cenet</source><creator>MADEC, ALAIN PAUL ; GARIN, FABRICE MARCEL NOEL ; LESAINE, JEAN-MARC MICHEL ; BON, FLORENCE VALERIE ; CAMEAU, JEROME ETIENNE ROBERT</creator><creatorcontrib>MADEC, ALAIN PAUL ; GARIN, FABRICE MARCEL NOEL ; LESAINE, JEAN-MARC MICHEL ; BON, FLORENCE VALERIE ; CAMEAU, JEROME ETIENNE ROBERT</creatorcontrib><description>The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterised in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
Linvention propose un carter (30) de turbine (16) conçu pour soutenir un ensemble de secteurs annulaires (28), qui délimite partiellement un canal pour le passage dun flux de gaz dans la turbine (16). Le carter (30) comprend un moyen dajustement dynamique de la position radiale des secteurs annulaires (28) au moyen dune injection contrôlée dun débit dair sur les parties (36) dune paroi annulaire (34) du carter (30). Le carter (30) comprend une languette radiale en amont (38), qui raccorde une extrémité en amont de chaque secteur annulaire (28) dans le sens de circulation du flux de gaz au carter (30) et une languette radiale en aval (40), qui raccorde une extrémité en aval de chaque secteur annulaire (28) au carter (30), les languettes radiales en amont et en aval (38, 40) étant faites dune seule avec le carter (30) et étant faites de deux parties (42, 44) de matériaux différents.</description><language>eng ; fre</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; ENGINE PLANTS IN GENERAL ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MACHINES OR ENGINES IN GENERAL ; MECHANICAL ENGINEERING ; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES ; STEAM ENGINES ; 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=20211019&DB=EPODOC&CC=CA&NR=2857869C$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20211019&DB=EPODOC&CC=CA&NR=2857869C$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MADEC, ALAIN PAUL</creatorcontrib><creatorcontrib>GARIN, FABRICE MARCEL NOEL</creatorcontrib><creatorcontrib>LESAINE, JEAN-MARC MICHEL</creatorcontrib><creatorcontrib>BON, FLORENCE VALERIE</creatorcontrib><creatorcontrib>CAMEAU, JEROME ETIENNE ROBERT</creatorcontrib><title>TURBINE CASING MADE OF TWO MATERIALS</title><description>The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterised in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
Linvention propose un carter (30) de turbine (16) conçu pour soutenir un ensemble de secteurs annulaires (28), qui délimite partiellement un canal pour le passage dun flux de gaz dans la turbine (16). Le carter (30) comprend un moyen dajustement dynamique de la position radiale des secteurs annulaires (28) au moyen dune injection contrôlée dun débit dair sur les parties (36) dune paroi annulaire (34) du carter (30). Le carter (30) comprend une languette radiale en amont (38), qui raccorde une extrémité en amont de chaque secteur annulaire (28) dans le sens de circulation du flux de gaz au carter (30) et une languette radiale en aval (40), qui raccorde une extrémité en aval de chaque secteur annulaire (28) au carter (30), les languettes radiales en amont et en aval (38, 40) étant faites dune seule avec le carter (30) et étant faites de deux parties (42, 44) de matériaux différents.</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>ENGINE PLANTS IN GENERAL</subject><subject>GAS-TURBINE PLANTS</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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>STEAM ENGINES</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2021</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZFAJCQ1y8vRzVXB2DPb0c1fwdXRxVfB3UwgJ9weyQ1yDPB19gnkYWNMSc4pTeaE0N4O8m2uIs4duakF-fGpxQWJyal5qSbyzo5GFqbmFmaWzMWEVAODSIgE</recordid><startdate>20211019</startdate><enddate>20211019</enddate><creator>MADEC, ALAIN PAUL</creator><creator>GARIN, FABRICE MARCEL NOEL</creator><creator>LESAINE, JEAN-MARC MICHEL</creator><creator>BON, FLORENCE VALERIE</creator><creator>CAMEAU, JEROME ETIENNE ROBERT</creator><scope>EVB</scope></search><sort><creationdate>20211019</creationdate><title>TURBINE CASING MADE OF TWO MATERIALS</title><author>MADEC, ALAIN PAUL ; GARIN, FABRICE MARCEL NOEL ; LESAINE, JEAN-MARC MICHEL ; BON, FLORENCE VALERIE ; CAMEAU, JEROME ETIENNE ROBERT</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_CA2857869C3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre</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>ENGINE PLANTS IN GENERAL</topic><topic>GAS-TURBINE PLANTS</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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>STEAM ENGINES</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>MADEC, ALAIN PAUL</creatorcontrib><creatorcontrib>GARIN, FABRICE MARCEL NOEL</creatorcontrib><creatorcontrib>LESAINE, JEAN-MARC MICHEL</creatorcontrib><creatorcontrib>BON, FLORENCE VALERIE</creatorcontrib><creatorcontrib>CAMEAU, JEROME ETIENNE ROBERT</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>MADEC, ALAIN PAUL</au><au>GARIN, FABRICE MARCEL NOEL</au><au>LESAINE, JEAN-MARC MICHEL</au><au>BON, FLORENCE VALERIE</au><au>CAMEAU, JEROME ETIENNE ROBERT</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>TURBINE CASING MADE OF TWO MATERIALS</title><date>2021-10-19</date><risdate>2021</risdate><abstract>The invention proposes a casing (30) of an aircraft turbine (16), intended to support a set of ring sectors (28) which partly delimits a channel for the passage of a gas stream through the turbine (16), where the casing (30) includes means for dynamic adjustment of the radial position of the ring sectors (28) by controlled injection of an air stream on to portions (36) of an annular wall (34) of the casing (30), where the casing (30) includes an upstream radial tab (38) which connects an upstream end of each ring sector (28), in the flow direction of the gas stream, to the casing (30), and a downstream radial tab (40) which connects a downstream end of each ring sector (28) to the casing (30), where both upstream and downstream radial tabs (38, 40) are made from a single piece with the casing (30), characterised in that each radial tab (38, 40) is made as two portions (42, 44) from different materials.
Linvention propose un carter (30) de turbine (16) conçu pour soutenir un ensemble de secteurs annulaires (28), qui délimite partiellement un canal pour le passage dun flux de gaz dans la turbine (16). Le carter (30) comprend un moyen dajustement dynamique de la position radiale des secteurs annulaires (28) au moyen dune injection contrôlée dun débit dair sur les parties (36) dune paroi annulaire (34) du carter (30). Le carter (30) comprend une languette radiale en amont (38), qui raccorde une extrémité en amont de chaque secteur annulaire (28) dans le sens de circulation du flux de gaz au carter (30) et une languette radiale en aval (40), qui raccorde une extrémité en aval de chaque secteur annulaire (28) au carter (30), les languettes radiales en amont et en aval (38, 40) étant faites dune seule avec le carter (30) et étant faites de deux parties (42, 44) de matériaux différents.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS |
| title | TURBINE CASING MADE OF TWO MATERIALS |
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