Transition Manifolds for Cooling Channel Connections in Cooled Structures

A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and are arranged along the first side portion. A second set of cooling air...

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Hauptverfasser:	Burnos, Daniel Robert, Sezer, Ibrahim
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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creator	Burnos, Daniel Robert Sezer, Ibrahim
description	A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and are arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and are arranged along the second side portion. Each set of cooling air micro-channels has at least one transition manifold in fluid communication with an adjacent micro-channel and also in fluid communication with at least one of an intake end, an exhaust end, and mixtures thereof. The cooled structure described above is also embodied in a gas turbine.
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The cooled structure described above is also embodied in a gas turbine.</description><language>eng</language><subject>AIR INTAKES FOR JET-PROPULSION PLANTS ; BLASTING ; COMBUSTION ENGINES ; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ; GAS-TURBINE PLANTS ; HEATING ; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS ; LIGHTING ; MECHANICAL ENGINEERING ; WEAPONS</subject><creationdate>2018</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=20180510&DB=EPODOC&CC=US&NR=2018128174A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20180510&DB=EPODOC&CC=US&NR=2018128174A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Burnos, Daniel Robert</creatorcontrib><creatorcontrib>Sezer, Ibrahim</creatorcontrib><title>Transition Manifolds for Cooling Channel Connections in Cooled Structures</title><description>A cooled structure of a gas turbine engine having a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. 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subjects	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
title	Transition Manifolds for Cooling Channel Connections in Cooled Structures
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