ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO
A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111)....
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| creator | MALECKI, Robert E SCHWARZ, Frederick M |
| description | A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). A ratio of the distance to the diameter (Dt) is greater than or equal to about 0.90. |
| format | Patent |
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The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). A ratio of the distance to the diameter (Dt) is greater than or equal to about 0.90.</description><language>eng ; fre ; ger</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 ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; PARACHUTES ; PERFORMING OPERATIONS ; 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=20220713&DB=EPODOC&CC=EP&NR=4027003A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20220713&DB=EPODOC&CC=EP&NR=4027003A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MALECKI, Robert E</creatorcontrib><creatorcontrib>SCHWARZ, Frederick M</creatorcontrib><title>ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO</title><description>A propulsion system (20) includes a fan (100), a gear (112), a turbine (116) configured to drive the gear (112) to, in turn, drive the fan (100). The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). 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The turbine (116) has an exit point (117), and a diameter (Dt) is defined at the exit point (117). A nacelle (102) surrounds a core engine housing (111). The fan (100) is configured to deliver air into a bypass duct defined between the nacelle (102) and the core engine housing (111). A core engine exhaust nozzle (122;222) is provided downstream of the exit point (117). A downstream most point (128; 228) of the core engine exhaust nozzle (122; 222) is defined at a distance from the exit point (117). A ratio of the distance to the diameter (Dt) is greater than or equal to about 0.90.</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 EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS |
| title | ELONGATED GEARED TURBOFAN WITH HIGH BYPASS RATIO |
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