Abstract: According to various aspects and embodiments, a growth adaptive expandable stent is provided. The expandable stent includes a stent structure having a cylindrical shape that is self-expanding in a radial direction and includes a plurality of cylindrical rings disposed along a longitudinal axis of the stent structure. The stent structure is configured to exert a continuous outward radial force over time when implanted such that a diameter of the stent structure expands from a first value to a second value that is at least about 1.5 times the first value.

Abstract: A tail for a projectile includes a body having a longitudinal axis. A steering assembly is secured to the body. The steering assembly includes a flap movable from a first position in which the flap does not extend radially beyond the body to a second position in which the flap extends radially beyond the body and at an angle relative to the longitudinal axis, and a flap release mechanism. A projectile including a tail according to the present disclosure is also provided.

Abstract: According to various aspects and embodiments, a growth adaptive expandable stent is provided. The expandable stent includes a stent structure having a cylindrical shape that is self-expanding in a radial direction and includes a plurality of cylindrical rings disposed along a longitudinal axis of the stent structure. The stent structure is configured to exert a continuous outward radial force over time when implanted such that a diameter of the stent structure expands from a first value to a second value that is at least about 1.5 times the first value.

Abstract: A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.

Abstract: According to various aspects and embodiments, a prosthetic valve assembly for controlling fluid flow in an annulus is provided. The prosthetic valve assembly includes a suture ring formed from two or more segments, where each segment is configured to attach to the annulus, and a leaflet subassembly that attaches to an inner portion of at least one segment of the suture ring. The leaflet subassembly includes at least one leaflet configured for controlling a flow of fluid through the prosthetic valve assembly.

Abstract: According to various aspects and embodiments, a growth adaptive expandable stent is provided. The expandable stent includes a stent structure having a cylindrical shape that is self-expanding in a radial direction and includes a plurality of cylindrical rings disposed along a longitudinal axis of the stent structure. The stent structure is configured to exert a continuous outward radial force over time when implanted such that a diameter of the stent structure expands from a first value to a second value that is at least about 1.5 times the first value.

Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.

Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a flow path, and a turbine fluidly connected to the combustor via the flow path. At least one multi-piece structure is disposed within the flow path such that the multi-piece structure at least partially radially spans the flow path. The at least one multi-piece structure includes a fore portion defining a leading edge, a consumable aft portion defining a trailing edge, a pressure surface at least partially defined by a first surface of the fore portion and a first surface of the consumable aft portion, and a suction surface at least partially defined by a second surface of the fore portion and a second surface of the consumable aft portion.

Abstract: A casting ceramic core includes a ceramic structure having at least one through hole and a plurality of features extending from a main ceramic body. The ceramic body defines a negative space for a casting and a plurality of aligned fibers extending a substantial length of at least one casting feature.

Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.

Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.

Abstract: A surface affixable device incorporating mechanically actuated dry adhesive includes a body and a plurality of tiles affixed to the body. Each of the plurality of tiles includes an array of dry adhesive material elements disposed on front faces thereof. A first of the plurality of tiles is movably affixed to the body. An actuator is constructed and arranged to displace the first of the plurality of tiles in a first direction relative to a second of the plurality of tiles. A biasing element applies a bias to the first of the plurality of tiles in a second direction upon displacement of the first of the plurality of tiles in the first direction.

Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.

Abstract: According to various aspects and embodiments, a prosthetic valve assembly for controlling fluid flow in an annulus is provided. The prosthetic valve assembly includes a suture ring formed from two or more segments, where each segment is configured to attach to the annulus, and a leaflet subassembly that attaches to an inner portion of at least one segment of the suture ring. The leaflet subassembly includes at least one leaflet configured for controlling a flow of fluid through the prosthetic valve assembly.

Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.

Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.

Abstract: A surface affixable device incorporating mechanically actuated dry adhesive includes a body and a plurality of tiles affixed to the body. Each of the plurality of tiles includes an array of dry adhesive material elements disposed on front faces thereof. A first of the plurality of tiles is movably affixed to the body. An actuator is constructed and arranged to displace the first of the plurality of tiles in a first direction relative to a second of the plurality of tiles. A biasing element applies a bias to the first of the plurality of tiles in a second direction upon displacement of the first of the plurality of tiles in the first direction.

Abstract: A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil.

Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.

Abstract: An airfoil fairing shell for a gas turbine engine includes an airfoil section between an outer vane endwall and an inner vane endwall, at least one of the outer vane endwall and the inner vane endwall including a radial attachment face, a suction side tangential attachment face, a pressure side tangential attachment face, and an axial attachment face.