Stator vane mistake proofing

摘要

An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID shroud. A first stator airfoil extends from the ID shroud to the OD shroud. The first stator airfoil is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A first end of the first stator airfoil has one of a raised tab and an indented notch.

主权项

1. An assembly for use in a gas turbine engine, the assembly comprising:
an inner diameter (ID) shroud having a plurality of ID slots; an outer diameter (OD) shroud having a plurality of OD slots and positioned radially outward from the ID shroud; and
a first stator airfoil extending from the ID shroud to the OD shroud, wherein the first stator airfoil has a leading edge and a trailing edge and is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots, and wherein a first radially outer end of the first stator airfoil includes:
a shoulder; anda free portion extending outward from the shoulder and having a leading end and a trailing end, wherein the free portion comprises:
a reference surface; andat least one of: a raised tab extending outward of the reference surface having a leading tab surface facing the leading end and a trailing tab surface facing the trailing end between the leading end and the trailing end of the free portion; and an indented notch indented inward of the reference surface having a leading notch surface facing the trailing end and a trailing notch surface facing the leading end between the leading end and the trailing end of the free portion.