A blade outer air seal segment including a radially outward surface, a radially inward surface oriented away from the radially outward surface, and a cooling channel located between the radially outward surface and the radially inward surface. The blade outer air seal segment also including a stress-relief boss extending into the cooling channel and an inlet orifice fluidly coupled to the cooling channel through the stress-relief boss. The blade outer air seal segment further including a stress-relief recess. The stress-relief boss being located within the stress relief recess.

An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

An assembly includes first and second core gaspath walls. Each of the core gaspath walls defines a core gas path side and a non-core gas path side. The first and second core gaspath walls are arranged next to each other and define a gap therebetween. There is a seal arranged on the non-core gas path side that bridges over the gap to seal the gap. A spring device has a plurality of spring elements. The spring elements bias the seal against the non-core gas path sides of the first and second core gaspath walls.

A turbine blade includes a root arranged to attach the turbine blade to a rotor and a vane extending in a radial direction from the root to a tip surface. The vane includes a leading edge, a trailing edge, a pressure-side surface, and a suction-side surface that cooperate to define a vane perimeter. A perimeter wall extends radially from the tip surface and surrounds a portion of the vane perimeter. A first trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a pressure-side pocket and a second trench wall extends across the tip surface and cooperates with the perimeter wall to substantially enclose a suction-side pocket.

An internal cooling system (10) for an airfoil (12) in a turbine engine (14) whereby the cooling system (10) includes a chordwise extending tip cooling channel (16) radially inward of a squealer tip (18) and formed at least in part by an inner wall (20) with a nonlinear outer surface (22) is disclosed. The nonlinear outer surface (22) of the inner wall (20) of the chordwise extending tip cooling channel (16) may be formed from pressure and suction side sections (24, 26) that intersect at a point (74) that is closer to the inner surface (30) of an outer wall (32) forming at least a portion of the squealer tip (18) than other aspects of the pressure side section (24) and the suction side section (26). The configurations of the pressure and suction side sections (24, 26) reduces the flow cross-sectional area, which accelerates the cooling fluid flow in a chordwise direction within the chordwise extending tip cooling channel (16) and directs cooling fluid toward the pressure and suction side outer walls (34, 36) for improved cooling efficiency.

A fan blade of a gas turbine engine may include a blade body having an inner surface defining a cavity in the blade body. A blade filler may be disposed in the cavity. The blade filler may include a bump integrally formed on a first surface of the blade filler. An adhesive may be formed on the first surface of the blade filler. The first surface of the blade filler may be bonded to a fan blade component.

There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.

There is provided a blade tip for a rotary blade. The blade tip is formed of a metal foam and comprises at least one vortex generator. The vortex generator may comprise at least one passageway and/or cavity in the blade tip. In use, a vortex is created between the blade tip and a fan casing adjacent the blade tip.

A dust mitigation system for airfoils includes a plurality of contoured tip turns which curve about at least two axes. This inhibits recirculation areas common within airfoils and further inhibits dust build up within the cooling flow path of the airfoil.

A dust mitigation system for airfoils includes a plurality of contoured tip turns which curve about at least two axes. This inhibits recirculation areas common within airfoils and further inhibits dust build up within the cooling flow path of the airfoil.