Ducted fan gas turbine engine with secondary duct

The fan duct 12 of a ducted fan gas turbine engine 10 is provided with a secondary duct 24 at least partly within the downstream end of the primary duct. The secondary duct 24 is provided with means such as a translatable, jet pipe 30, flaps (34)(Fig.2) or (36)(figs. 3 and 4), whereby the airflow th...

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1. Verfasser:	ARNOLD CHARLES NEWTON
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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creator	ARNOLD CHARLES NEWTON
description	The fan duct 12 of a ducted fan gas turbine engine 10 is provided with a secondary duct 24 at least partly within the downstream end of the primary duct. The secondary duct 24 is provided with means such as a translatable, jet pipe 30, flaps (34)(Fig.2) or (36)(figs. 3 and 4), whereby the airflow therethrough may be varied to suit flight requirements of an associated aircraft, in a way which will control the maximum diameter of the free stream tube airflow at the intake of the engine, thus effectively reducing the frontal area of the fan duct, and therefor, drag. Flow from the secondary duct 24 may be diverted into the main by-pass flow (fig. 2) or the core flow (figs. 3 and 4), via conduits (38) in the latter case.
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The secondary duct 24 is provided with means such as a translatable, jet pipe 30, flaps (34)(Fig.2) or (36)(figs. 3 and 4), whereby the airflow therethrough may be varied to suit flight requirements of an associated aircraft, in a way which will control the maximum diameter of the free stream tube airflow at the intake of the engine, thus effectively reducing the frontal area of the fan duct, and therefor, drag. Flow from the secondary duct 24 may be diverted into the main by-pass flow (fig. 2) or the core flow (figs. 3 and 4), via conduits (38) in the latter case.</description><edition>6</edition><language>eng</language><subject>BLASTING ; COMBUSTION ENGINES ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; JET-PROPULSION PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>1997</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=19970709&DB=EPODOC&CC=GB&NR=2308866A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,776,881,25542,76289</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=19970709&DB=EPODOC&CC=GB&NR=2308866A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>ARNOLD CHARLES NEWTON</creatorcontrib><title>Ducted fan gas turbine engine with secondary duct</title><description>The fan duct 12 of a ducted fan gas turbine engine 10 is provided with a secondary duct 24 at least partly within the downstream end of the primary duct. The secondary duct 24 is provided with means such as a translatable, jet pipe 30, flaps (34)(Fig.2) or (36)(figs. 3 and 4), whereby the airflow therethrough may be varied to suit flight requirements of an associated aircraft, in a way which will control the maximum diameter of the free stream tube airflow at the intake of the engine, thus effectively reducing the frontal area of the fan duct, and therefor, drag. Flow from the secondary duct 24 may be diverted into the main by-pass flow (fig. 2) or the core flow (figs. 3 and 4), via conduits (38) in the latter case.</description><subject>BLASTING</subject><subject>COMBUSTION ENGINES</subject><subject>HEATING</subject><subject>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</subject><subject>JET-PROPULSION PLANTS</subject><subject>LIGHTING</subject><subject>MECHANICAL ENGINEERING</subject><subject>WEAPONS</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>1997</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZDB0KU0uSU1RSEvMU0hPLFYoKS1KysxLVUjNSwdR5ZklGQrFqcn5eSmJRZUKKUDFPAysaYk5xam8UJqbQd7NNcTZQze1ID8-tbggMTk1L7Uk3t3JyNjAwsLMzNGYsAoAx7wqkg</recordid><startdate>19970709</startdate><enddate>19970709</enddate><creator>ARNOLD CHARLES NEWTON</creator><scope>EVB</scope></search><sort><creationdate>19970709</creationdate><title>Ducted fan gas turbine engine with secondary duct</title><author>ARNOLD CHARLES NEWTON</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_GB2308866A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>1997</creationdate><topic>BLASTING</topic><topic>COMBUSTION ENGINES</topic><topic>HEATING</topic><topic>HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS</topic><topic>JET-PROPULSION PLANTS</topic><topic>LIGHTING</topic><topic>MECHANICAL ENGINEERING</topic><topic>WEAPONS</topic><toplevel>online_resources</toplevel><creatorcontrib>ARNOLD CHARLES NEWTON</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>ARNOLD CHARLES NEWTON</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>Ducted fan gas turbine engine with secondary duct</title><date>1997-07-09</date><risdate>1997</risdate><abstract>The fan duct 12 of a ducted fan gas turbine engine 10 is provided with a secondary duct 24 at least partly within the downstream end of the primary duct. The secondary duct 24 is provided with means such as a translatable, jet pipe 30, flaps (34)(Fig.2) or (36)(figs. 3 and 4), whereby the airflow therethrough may be varied to suit flight requirements of an associated aircraft, in a way which will control the maximum diameter of the free stream tube airflow at the intake of the engine, thus effectively reducing the frontal area of the fan duct, and therefor, drag. Flow from the secondary duct 24 may be diverted into the main by-pass flow (fig. 2) or the core flow (figs. 3 and 4), via conduits (38) in the latter case.</abstract><edition>6</edition><oa>free_for_read</oa></addata></record>
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subjects	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
title	Ducted fan gas turbine engine with secondary duct
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