SHROUD ASSEMBLY AND SHROUD FOR GAS TURBINE ENGINE

Shrouds (102) and shroud assemblies (100) for gas turbine engines are provided. A shroud includes a shroud body (110). The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and...

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Bibliographische Detailangaben
Hauptverfasser:	HEITMAN, BRYCE LORING, SENILE, DARRELL GLENN, RADWANSKI, MICHAEL TODD
Format:	Patent
Sprache:	eng ; fre ; 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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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:	Shrouds (102) and shroud assemblies (100) for gas turbine engines are provided. A shroud includes a shroud body (110). The shroud body includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a flange (120) extending from the shroud body, and a bore hole (130) defined in the flange. The bore hole (130) extends generally circumferentially through the flange between a first opening (132) and a second opening (134).