COMPRESSORS WITH CASING TREATMENTS IN GAS TURBINE ENGINES

A compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction betwe...

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Bibliographische Detailangaben
Hauptverfasser:	GOSWAMI SHRAMAN NARAYAN, MANSOUR MAHMOUD, CHOUGULE HASHAM HAMZAMIYAN
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 compressor section includes a rotor platform; a rotor blade extending radially outwardly from the rotor platform, the rotor blade including a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between a leading edge and a trailing edge; a casing having an inner surface surrounding the tip and spaced radially outwardly thereform to define a gap therebetween; a plurality of grooves disposed in the inner surface of the casing and extending in a generally circumferential direction, the plurality of grooves including a first groove and a second groove; and a channel system comprising at least a first channel positioned within the casing and configured to provide fluid communication between the first groove and the second groove.