Gas turbine engine nacelle with sound damping means in the fan intake area
The housing (29) has a honeycomb structural layer arranged in a region of an inflow-side air inlet (11) at the housing arranged upstream of a fan (12). Sound proofing elements arranged at radially outside the honeycomb structural layer that extends in axial direction. The sound damping elements are...
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| creator | Todorovic, Predrag Kubisch, Thomas |
| description | The housing (29) has a honeycomb structural layer arranged in a region of an inflow-side air inlet (11) at the housing arranged upstream of a fan (12). Sound proofing elements arranged at radially outside the honeycomb structural layer that extends in axial direction. The sound damping elements are arranged annularly adjacent to one another in circumferential direction. Each sound-damping element comprises a hollow chamber extending in axial direction through recesses in communication with the honeycomb structural layer. |
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Sound proofing elements arranged at radially outside the honeycomb structural layer that extends in axial direction. The sound damping elements are arranged annularly adjacent to one another in circumferential direction. Each sound-damping element comprises a hollow chamber extending in axial direction through recesses in communication with the honeycomb structural layer.</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>2017</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=20171025&DB=EPODOC&CC=EP&NR=2620628A3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20171025&DB=EPODOC&CC=EP&NR=2620628A3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Todorovic, Predrag</creatorcontrib><creatorcontrib>Kubisch, Thomas</creatorcontrib><title>Gas turbine engine nacelle with sound damping means in the fan intake area</title><description>The housing (29) has a honeycomb structural layer arranged in a region of an inflow-side air inlet (11) at the housing arranged upstream of a fan (12). 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Sound proofing elements arranged at radially outside the honeycomb structural layer that extends in axial direction. The sound damping elements are arranged annularly adjacent to one another in circumferential direction. Each sound-damping element comprises a hollow chamber extending in axial direction through recesses in communication with the honeycomb structural layer.</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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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 | Gas turbine engine nacelle with sound damping means in the fan intake area |
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