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.

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 airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

An airfoil includes an airfoil section defining suction and pressure sides and leading and a trailing ends, the airfoil section being formed of a fiber-reinforced composite comprised of fiber plies, the fiber plies including at least one core fiber ply defining a tube that circumscribes an internal cavity and an overwrap fiber ply that wraps around the at least one core fiber ply, and aft of the internal cavity the overwrap fiber ply on the pressure side including first fingers and the overwrap ply on the suction side including second fingers, the first fingers being interdigitated with the second fingers to form an interlocked joint in the trailing end.

This fin tip position measurement method comprises: a jig installation step for installing a jig having a flat measurement surface expanded in a circumferential direction and an axial direction to a tip of at least one among a plurality of seal fins that protrude in a radial direction with respect to an axial line, extend in the circumferential direction, and are arranged in a direction in which the axial line extends; a first measurement step for measuring a distance from the axial line to the measurement surface by scanning the measurement surface with a laser beam; and a first calculation step for calculating a distance from the axial line to the tip of the seal fin by adding a radial dimension of the jig to the distance to the measurement surface.

This fin tip position measurement method comprises: a jig installation step for installing a jig having a flat measurement surface expanded in a circumferential direction and an axial direction to a tip of at least one among a plurality of seal fins that protrude in a radial direction with respect to an axial line, extend in the circumferential direction, and are arranged in a direction in which the axial line extends; a first measurement step for measuring a distance from the axial line to the measurement surface by scanning the measurement surface with a laser beam; and a first calculation step for calculating a distance from the axial line to the tip of the seal fin by adding a radial dimension of the jig to the distance to the measurement surface.

The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.

The invention relates to an airfoil as well as to a method for producing an airfoil for a turbomachine, comprising a leading edge and a trailing edge joined to each other by a suction side and a pressure side and which, in at least one region, extends in a curved manner from an airfoil root to an airfoil tip, wherein the airfoil tip has a squealer tip, which is arranged at the airfoil tip.

An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.

A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.