Blade tip shroud for a compression stage of a gas turbine engine

A blade tip shroud structure for a compression stage of a gas turbine engine is disclosed. Various concepts relating to shroud designs and their influence on blade performance are discussed. In accordance with the teaching contained herein, one shroud geometry includes a circumferentially extending...

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Bibliographische Detailangaben
1. Verfasser:	ROBERTS, FRANK JR
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 NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A blade tip shroud structure for a compression stage of a gas turbine engine is disclosed. Various concepts relating to shroud designs and their influence on blade performance are discussed. In accordance with the teaching contained herein, one shroud geometry includes a circumferentially extending recess in the wall of a case which circumscribes the tips of the blades. A surface at the bottom of the recess has discontinuities therein. The tips of the blades run line on line with the respective wall at the design operating condition of the engine in which the shroud structure is incorporated. In one embodiment axially skewed grooves and circumferentially extending grooves form the surface discontinuities.