TURBINE BLADE SHROUD FOR GAS TURBINE ENGINE WITH POWER TURBINE AND METHOD OF MANUFACTURING SAME

A blade (50) for a gas turbine engine (20) includes an airfoil (58) that includes an internal passage (70). A shroud (52) is arranged at an end of the airfoil (58) and has a shroud perimeter (64). Axially spaced knife edges (54) extend radially from the shroud (52). An area is provided between the k...

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Bibliographic Details
Main Authors STONER, Alan W, BERGMAN, Russell J
Format Patent
LanguageEnglish
French
German
Published 17.02.2021
Subjects
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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Summary:A blade (50) for a gas turbine engine (20) includes an airfoil (58) that includes an internal passage (70). A shroud (52) is arranged at an end of the airfoil (58) and has a shroud perimeter (64). Axially spaced knife edges (54) extend radially from the shroud (52). An area is provided between the knife edges (54). A pocket (72) is recessed into the area and is circumscribed by a perimeter edge (74) that is arranged interiorly of the shroud perimeter (64). An outlet (76) fluidly connects the internal passage (70) to the pocket (72).
Bibliography:Application Number: EP20190167563