TURBINE ENGINE SHROUD WITH NEAR WALL COOLING

An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the sh...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Gallier, Kirk D, Groves, II, Robert Charles
Format:	Patent
Sprache:	eng
Schlagworte:	DEVICES OR ARRANGEMENTS, THE OPTICAL OPERATION OF WHICH ISMODIFIED BY CHANGING THE OPTICAL PROPERTIES OF THE MEDIUM OF THEDEVICES OR ARRANGEMENTS FOR THE CONTROL OF THE INTENSITY,COLOUR, PHASE, POLARISATION OR DIRECTION OF LIGHT, e.g.SWITCHING, GATING, MODULATING OR DEMODULATING FREQUENCY-CHANGING MEASURING MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER,MECHANICAL EFFICIENCY, OR FLUID PRESSURE NON-LINEAR OPTICS OPTICAL ANALOGUE/DIGITAL CONVERTERS OPTICAL LOGIC ELEMENTS OPTICS PHYSICS TECHNIQUES OR PROCEDURES FOR THE OPERATION THEREOF TESTING
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Beschreibung
Zusammenfassung:	An apparatus for a shroud assembly for a turbine engine and a method of manufacturing such can include the shroud assembly having one or more shroud segments having an inner face in a circumferential organization around a rotating blade assembly. A near wall cooling passage can be provided in the shroud assembly to cool the inner face of the shroud. The near wall cooling passage can exhaust to a purge cavity, a split line, or at the inner face.