Abstract: A stator assembly having: an inner air seal carrier having a mounting body; a plurality of guide vanes secured to the mounting body via a plurality of fasteners; and a fastener retention mechanism secured to the mounting body via the plurality of fasteners. The fastener retention mechanism having: a housing defining an inner chamber; and a filler located within the inner chamber. The portions of the plurality of fasteners are encapsulated within the filler.

Abstract: A stator assembly for a stator of a gas turbine engine is provided. The stator assembly having: a shroud defining a cavity; a plurality of inserts located within the cavity, each of the plurality of inserts defining a cavity; a plurality of vanes secured to the shroud, wherein each of the plurality of vanes has a tab portion located in the cavity of the shroud; and a rubber material disposed in the cavity of the shroud, the rubber material securing the tab portion of each of the plurality of vanes to the shroud.

Abstract: A stator assembly for a stator of a gas turbine engine is provided. The stator assembly having: a shroud defining a cavity; a plurality of inserts located within the cavity, each of the plurality of inserts defining a cavity; a plurality of vanes secured to the shroud, wherein each of the plurality of vanes has a tab portion located in the cavity of the shroud; and a rubber material disposed in the cavity of the shroud, the rubber material securing the tab portion of each of the plurality of vanes to the shroud.

Abstract: A stator assembly having: an inner air seal carrier having a mounting body; a plurality of guide vanes secured to the mounting body via a plurality of fasteners; and a fastener retention mechanism secured to the mounting body via the plurality of fasteners. The fastener retention mechanism having: a housing defining an inner chamber; and a filler located within the inner chamber. The portions of the plurality of fasteners are encapsulated within the filler.

Abstract: A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case. An anti-rotation plate extends from a flange of the case between adjacent ones of the plurality of vanes for preventing rotation of the plurality of vanes relative to the case.

Abstract: A stator vane assembly for a gas turbine engine is disclosed and includes a plurality of vanes received within channels defined within a case. An anti-rotation plate extends from a flange of the case between adjacent ones of the plurality of vanes for preventing rotation of the plurality of vanes relative to the case.

Abstract: A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction.

Abstract: A vane for a gas turbine engine includes an airfoil portion, a platform, and a first flange. The airfoil portion has first and second ends spaced apart in a first direction, and the first end of the airfoil portion defines an unshrouded tip. The platform is integrally formed at the second end of the airfoil, and is configured to define a flowpath boundary segment. The first flange extends from the platform away from the airfoil portion. The first flange defines a first circumferential extension and an adjacent second circumferential extension, each defining forward and aft faces. The first and second circumferential extensions are offset in a second direction such that the forward face of the first circumferential extension is substantially aligned with the aft face of the second circumferential extension in the second direction.