A flow path component assembly includes a flow path component that has a plurality of segments that extend circumferentially about an axis. At least one of the segments have a first radial side and a second radial side and extend from a first circumferential side to a second circumferential side. A mateface seal is arranged on the first radial side near the first circumferential side. The mateface seal has a v-shaped groove.

According to an embodiment, a turbine stator blade disposed in a working fluid flow path in a casing of a gas turbine, includes: a blade effective part disposed in the working fluid flow path; an outer circumferential sidewall having a plate-shaped part that is connected to a radially outer end portion of the blade effective part, and hooks each extending radially outward and circumferentially from the plate-shaped part and having a tip engaged with the casing; and an inner circumferential sidewall connected to a radially inner end portion of the blade effective part. At least one slit is formed at the rear hook or front hook to divide the hook in a circumferential direction, and the hook has a seal member to seal the slit.

A flow path component includes a platform that extends between a first side and a second side. A slot is in the first side. The slot divides the platform into a first portion and a second portion at the first side. There is a groove along the first side in the first portion.

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 gas turbine engine has: a first component and a second component defining a respective first gaspath surface and a second gaspath surface of an annular gaspath, the first and second gaspath surfaces axially spaced apart from one another by an annular recess in the first component; a bushing ring disposed within the annular recess and defining stem pockets therein; variable guide vanes pivotable about respective vane axes extending between first and second stems; and a biasing member received within the annular recess and disposed axially between the bushing ring and one of the first component and the second component, the biasing member exerting a force against the bushing ring in an axial direction relative to the central axis and towards the other of the first component and the second component.

A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.

A seal assembly for a gas turbine engine, including: a first finger seal assembly, the first finger seal assembly including two layers each being secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the first finger seal assembly are secured to each other; a second finger seal assembly, the second finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the second finger seal assembly are secured to each other; and an arc-shaped segment finger seal assembly located between the first finger seal assembly and the second finger seal assembly, the arc-shaped finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the arc-shaped finger seal assembly are secured to each other.

A rotor disk assembly for a gas turbine engine includes a rotor disk with a multiple of blade slots, the rotor disk defined about an axis; a sleeve received within each of the multiple of blade slots; and a ceramic matrix composite rotor blade received within each of the multiple of sleeves.

Rotor blades and turbomachines are provided. The rotor blade includes a main body having a shank, an airfoil extending radially outwardly from the shank, and a platform. The main body further includes a pressure-side slash face and a suction-side slash face. Each of the pressure-side slash face and the suction-side slash face includes a damper land and defines a slot. The damper land is disposed radially inward from the slot.

Turbomachine modules, for example for an aircraft, include a turbine nozzle having several sectors (S), each sector having guide vanes extending between inner and outer platform elements, at least one of the platform elements of each sector carrying, on the one hand, at least one sealing blade configured to ensure fluid sealing between the platform element and the adjacent structural element, and, on the other hand, a device configured to hold the at least one sealing blade in a sealing position. The device includes a leaf spring having a middle portion fixed to the platform element, and opposite end portions which are supported on the sealing blade carried by the platform element.