Blade assembly with splitter shroud

Fluid reaction surfaces (i.e. – impellers) – Rotor having flow confining or deflecting web – shroud or... – Axially extending shroud ring or casing

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415 78, 415 79, F01D 522

Patent

active

059889802

ABSTRACT:
A blade assembly, which may have blisk for a gas turbine engine, includes an annular rim disposed about a rotor axis and a blade assembly disposed around the rim. The blade assembly has circumferentially disposed and radially extending inner and outer rows of inner and outer airfoils, respectively and each airfoil has axially spaced apart leading and trailing airfoil edges. An annular shroud is disposed between and connecting the inner and outer rows of inner and outer airfoils and has axially spaced apart annular leading and trailing shroud edges corresponding to the leading and trailing airfoil edges, respectively. An axially extending cavity is provided in each of the leading and trailing shroud edges for reducing stresses in leading and trailing airfoil edges, respectively and the corresponding airfoil edges are located near the cavities. The cavities preferably extend axially under the corresponding airfoil edges. The cavities may be 360 degree circumferentially extending annular grooves in one embodiment.

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