DAMPFGEKÜHLTER TURBINENMANTEL MIT GESCHLOSSENEM KÜHLKREISLAUF

A turbine shroud cooling cavity is partitioned to define a plurality of cooling chambers (40, 42, 44, 46) for sequentially receiving cooling steam and impingement cooling of the radially inner wall of the shoud (20). An impingement baffle (48, 50, 52, 54) is provided in each cooling chamber (40, 42,...

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Bibliographische Detailangaben
Hauptverfasser:	KELLOCK, IAIN ROBERTSON, BURDGICK, STEVEN SEBASTIAN, SEXTON, BRENDAN FRANCIS
Format:	Patent
Sprache:	ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine shroud cooling cavity is partitioned to define a plurality of cooling chambers (40, 42, 44, 46) for sequentially receiving cooling steam and impingement cooling of the radially inner wall of the shoud (20). An impingement baffle (48, 50, 52, 54) is provided in each cooling chamber (40, 42, 44, 46) for receiving the cooling media from a cooling media inlet in the case of the first chamber or from the immediately upstream chamber in the case of the second through fourth chambers and includes a plurality of impingement holes for effecting the impingement cooling of the shroud inner wall.