A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure via a carrier. At least one of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. The first and second walls extend at an angle less than 90 from the base portion. The carrier has a flat portion that extends from the first wall to the second wall.

A blade outer air seal assembly includes a blade outer air seal that has a plurality of segments that extend circumferentially about an axis and are mounted in a support structure. At least two of the segments have a first wall circumferentially spaced from a second wall. A base portion extends from the first wall to the second wall. A first hook extends from the first wall and a second hook extends from the second wall. A wedge seal is arranged between the at least two adjacent seal segments. A clip is configured to bias the wedge seal radially inward.

There is disclosed a fan track liner assembly 53 for a containment arrangement 50 of a gas turbine engine, the assembly 53 comprising a cellular reactive impact structure 60, wherein cells of the reactive impact structure 60 contain a reactive material having shear-thickening or shear-stiffening properties; whereby the reactive impact structure 60 is compliant during assembly to accommodate geometrical non-compliance in the fan track liner assembly.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly, a blade assembly and a method for installing a locking spacer assembly into a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly are presented. The locking spacer assembly includes a first side piece, a second side piece, a bolt and a mid piece. The mid piece includes a hollow cylindrical body to receive the bolt and a top platform to flush with top surfaces of the first and second side pieces and a middle platform disposed at bottom of the hollow cylindrical body. At least two pins are radially inserted through apertures of the first and second side pieces respectively extending toward the middle platform of the mid piece to prevent radial movement of the mid piece.

A gas path component for a gas turbine engine includes a film cooling hole disposed in the gas path component. The film cooling hole includes a metering section, a diffuser, and a tapered surface extending between the metering section and the diffuser. The tapered surface is oriented between twenty degrees and seventy degrees with respect to a centerline axis of the metering section. The tapered surface is oriented at an obtuse angle with respect to an immediately adjacent surface of the diffuser, the obtuse angle is open towards the centerline axis. The tapered surface is configured to mitigate flow separation in the diffuser.

A vane arm assembly for a gas turbine engine includes a vane stem having a circumferential groove axially spaced from an outer end of the vane stem. The assembly also includes a vane arm defining an arm aperture that the vane stem is disposed within. The assembly further includes a mechanical fastener retaining an axial position of the vane arm in the axial direction. The assembly yet further includes a retention clip having a base portion and at least one clip arm, the base portion defining a clip aperture that the vane stem is disposed within, the base portion disposed within the circumferential groove of the vane stem to couple the retention clip to the vane stem, the at least one clip arm including a retention member engaged with the vane arm to provide redundant axial retention of the vane arm.

An airfoil defining a span extending between a root and a tip and a chord at each point along the span extending between a leading edge and a trailing edge. The airfoil includes a blade extending between the root and tip and extending between the leading edge and trailing edge. The blade includes a pressure side and a suction side defining a thickness therebetween at each point along the span. The blade defines a first chord reduction on at least one of the leading edge or trailing edge along a first portion of the span. Further, the blade defines a frangible line extending from the first chord reduction at least partially along the chord at a point along the span within the first portion of the span.

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

A planetary gearbox device, a gas turbine engine with a planetary gearbox device, and a method for producing a scoop pump. The planetary gearbox device includes an oil supply appliance, wherein the oil supply appliance has a ring-shaped scoop pump that is connected to the rotatable shaft of the planetary gearbox device and an oil supply fixedly arranged at the housing and by which oil is supplied to the scoop pump. The scoop pump has multiple blades that extend in a circumferentially arranged manner and extend from a radially outer area in the direction of a radially inner area. The blades delimit grooves extending in the circumferential direction in the radial direction and respectively form a groove base of the grooves. The oil is conducted from the oil supply to outlets via which oil is conducted out of the scoop pump in the radial direction outwards.