Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.

Abstract: A nozzle, a nozzle hanger, and a ceramic to metal attachment system are provided. The ceramic to metal attachment system includes the nozzle, a ceramic matrix composite, and the nozzle hanger, a metal. The attachment system also includes a clamping member adjacent a second surface of the nozzle and a mounting member of the nozzle. The attachment system includes a plurality of attachment members securing the nozzle, the clamping member, and the nozzle hanger together. A sealing member of the nozzle hanger seals off an airfoil of the nozzle from adjacent airflow.

Abstract: Gas turbine engine turbine blade assembly includes a hollow airfoil joined to blade root, dovetail slot heat shield bonded or attached to a bottom surface of the root, and a shield outlet from heat shield open to inlet apertures extending radially through a radially inner root end of the root. Heat shield may have body with legs extending upwardly from heat shield bottom, slanted open upstream end, and free ends of the legs longer than the heat shield bottom. Flanges may be located along free ends and bonded to bottom surface. Body, heat shield bottom and/or the legs may be rounded. Disk includes a plurality of dovetail slots formed in a rim, complimentary plurality of turbine blades removably retained in dovetail slots by the roots, slot bottoms of the dovetail slots extending circumferentially between disk posts in rim. Heat shield bottoms may be radially spaced apart the slot bottoms.

Abstract: A nozzle, a nozzle hanger, and a ceramic to metal attachment system are provided. The ceramic to metal attachment system includes the nozzle, a ceramic matrix composite, and the nozzle hanger, a metal. The attachment system also includes a clamping member adjacent a second surface of the nozzle and a mounting member of the nozzle. The attachment system includes a plurality of attachment members securing the nozzle, the clamping member, and the nozzle hanger together. A sealing member of the nozzle hanger seals off an airfoil of the nozzle from adjacent airflow.

Abstract: A ceramic matrix composite (CMC) component and a method of attaching a static seal to a ceramic matrix composite component are provided. The CMC component includes a first end and a second end. A CMC metal interface member is attached to the second end. The CMC metal interface member is operable to join to a static seal in a gas turbine.

Abstract: A method facilitates assembling a gas turbine engine assembly including at least a first member and a second member. The method comprises inserting a threaded fastener through an opening formed in a flange, and providing at least one shank nut including a flanged mating end, an opposite non-mating end, and a body extending therebetween. The body includes an internal surface, an external surface, and a centerline extending between the body ends. The flanged mating end includes a substantially planar exterior surface that is aligned perpendicularly to the centerline and an annular groove that extends from the exterior surface at least partially towards the non-mating end. The method also comprises securing the assembly together such that the mating end is positioned flush against the flange and such that the threaded fastener extends at least partially into a bore extending through the shank nut and defined by the shank nut internal surface.

Abstract: A method facilitates assembling a gas turbine engine assembly including at least a first member and a second member. The method comprises inserting a threaded fastener through an opening formed in a flange, and providing at least one shank nut including a flanged mating end, an opposite non-mating end, and a body extending therebetween. The body includes an internal surface, an external surface, and a centerline extending between the body ends. The flanged mating end includes a substantially planar exterior surface that is aligned perpendicularly to the centerline and an annular groove that extends from the exterior surface at least partially towards the non-mating end. The method also comprises securing the assembly together such that the mating end is positioned flush against the flange and such that the threaded fastener extends at least partially into a bore extending through the shank nut and defined by the shank nut internal surface.

Abstract: A method facilitates assembling a gas turbine engine assembly including at least a first member and a second member. The method comprises inserting a threaded fastener through an opening formed in a flange, and providing at least one shank nut including a flanged mating end, an opposite non-mating end, and a body extending therebetween. The body includes an internal surface, an external surface, and a centerline extending between the body ends. The flanged mating end includes a substantially planar exterior surface that is aligned perpendicularly to the centerline and an annular groove that extends from the exterior surface at least partially towards the non-mating end. The method also comprises securing the assembly together such that the mating end is positioned flush against the flange and such that the threaded fastener extends at least partially into a bore extending through the shank nut and defined by the shank nut internal surface.