ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE
The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode d...
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| creator | LeDuigou, Loic Vallart, Philippe Bazet, Jean-Michel |
| description | The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes. |
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| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2022024568A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2022024568A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2022024568A13</originalsourceid><addsrcrecordid>eNqNjM0KwjAQhHvxIOo7LHgWtP7gdZtum0BNSrIReipF4km0UF_F9zWFXgVhYGBmvpknH7RCKibB3hIUxgJCbU3tK6eMBtc4pguYIsaSKiVMzWRBaVH5XOlyjJvMqhwinxknsWAgXSpNgDqP9fQwPltCweqKPIIOI_SLXSaze_cYwmryRbIuiIXchP7VhqHvbuEZ3q136TaNOhxPZ9zt_1t9AZ49QtI</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE</title><source>esp@cenet</source><creator>LeDuigou, Loic ; Vallart, Philippe ; Bazet, Jean-Michel</creator><creatorcontrib>LeDuigou, Loic ; Vallart, Philippe ; Bazet, Jean-Michel</creatorcontrib><description>The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.</description><language>eng</language><subject>AEROPLANES ; 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 ; HELICOPTERS ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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=20220127&DB=EPODOC&CC=US&NR=2022024568A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220127&DB=EPODOC&CC=US&NR=2022024568A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>LeDuigou, Loic</creatorcontrib><creatorcontrib>Vallart, Philippe</creatorcontrib><creatorcontrib>Bazet, Jean-Michel</creatorcontrib><title>ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE</title><description>The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.</description><subject>AEROPLANES</subject><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>HELICOPTERS</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>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>eNqNjM0KwjAQhHvxIOo7LHgWtP7gdZtum0BNSrIReipF4km0UF_F9zWFXgVhYGBmvpknH7RCKibB3hIUxgJCbU3tK6eMBtc4pguYIsaSKiVMzWRBaVH5XOlyjJvMqhwinxknsWAgXSpNgDqP9fQwPltCweqKPIIOI_SLXSaze_cYwmryRbIuiIXchP7VhqHvbuEZ3q136TaNOhxPZ9zt_1t9AZ49QtI</recordid><startdate>20220127</startdate><enddate>20220127</enddate><creator>LeDuigou, Loic</creator><creator>Vallart, Philippe</creator><creator>Bazet, Jean-Michel</creator><scope>EVB</scope></search><sort><creationdate>20220127</creationdate><title>ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE</title><author>LeDuigou, Loic ; Vallart, Philippe ; Bazet, Jean-Michel</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2022024568A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2022</creationdate><topic>AEROPLANES</topic><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>HELICOPTERS</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>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>STEAM ENGINES</topic><topic>TRANSPORTING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>LeDuigou, Loic</creatorcontrib><creatorcontrib>Vallart, Philippe</creatorcontrib><creatorcontrib>Bazet, Jean-Michel</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>LeDuigou, Loic</au><au>Vallart, Philippe</au><au>Bazet, Jean-Michel</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE</title><date>2022-01-27</date><risdate>2022</risdate><abstract>The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES 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 HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE 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 | ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE |
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