A sealing system for a gas turbine engine includes a first surface and a second surface spaced a dimension away from the first surface defining a gap through which a fluid can flow. At least one recess is formed in one of the first surface and the second surface and is oriented such that the fluid flow through the gap crosses the at least one recess. The recess is configured to restrict the fluid flow through the gap in comparison to if the at least one recess were not present, all other things being equal.

A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.

The invention relates to a guide vane ring for a turbomachine comprising at least one guide vane, at least one bearing body, and at least two inner ring segments. The guide vane has a bearing journal that is arranged in a in form-fitting manner in a bearing bush of the at least one bearing body. The at least two inner ring segments have on their respective outer radial faces a guide channel running along a circumferential direction of the guide vane ring for receiving the bearing body, into which project at least two opposite-lying guide projections of the inner ring segments, said projections running along the circumferential direction of the guide vane ring. The bearing bodyis arranged in the guide channel of the inner ring segments, and the at least two guide projections of the inner ring segments engage in at least two guide grooves of the bearing body.

A sealing assembly and a turbomachine including the sealing assembly are provided. The sealing assembly includes a sealing body configured to be inserted into an insertion hole of a second component adjacent to a first component, and a sealing protrusion, formed on one circumferential side of the sealing body, protruding toward one circumferential direction from the sealing body and configured to be inserted into a sealing groove formed on the other circumferential side of a sealing body of the first adjacent sealing assembly, the sealing body of the first adjacent sealing assembly being adjacent to the sealing body in a circumferential direction.

Methods, apparatus, systems and articles of manufacture are disclosed. An example apparatus includes a compressor comprising a rotor defining a radial direction and a circumferential direction, the rotor including a slot; a first blade and a second blade disposed in the slot, the first blade including a first platform and a first dovetail, the second blade including a second platform and a second dovetail; and a hollow block disposed circumferentially between the first blade and the second blade in the slot, the hollow block including: a platform interface portion to interface with the first platform and the second platform, the platform interface portion including a central opening defined by a circumferential face of the platform interface portion; and a hollow dovetail interface portion to couple the first dovetail and the second dovetail.

In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

A seal structure may comprise a cavity defined at least partially by an axial surface and a radial surface. A brush seal may be disposed in the cavity. The brush seal may comprise a bristle pack and a backing plate coupled to the bristle pack. A first surface of the backing plate may contact the axial surface, and a second surface of the backing plate may contact the radial surface.

A system is presented for directing the flow of cooling fluid in a rotational machine having co-axial rotatable shafts. The system comprises a first shaft rotatable about an axis, a second shaft rotatable about the axis and having a portion axially overlapping with the first shaft, and a fluid catcher. The fluid catcher is coupled between the first shaft and the second shaft. The fluid catcher comprises a first interface region interfacing with the first shaft, a second interface region interfacing with the second shaft, a fluid retention lip at least partly defining an oil capture region; and a body. The body is coupled to the oil retention lip and defines a channel in fluid communication with the oil capture region. The channel is positioned to direct fluid to one of the first interface region or the second interface region.

Assembly in a turbine comprising: —at least one turbine ring made of a ceramic composite having a silicon carbide SiC matrix and fibers, the ring comprising a plurality of sectors (10) arranged circumferentially end to end, each of the ring sectors (10) comprises at least one circumferential edge (26, 28) provided with at least one slot (30a, 30b, 30c) opening circumferentially, —at least one sealing member being inserted for a first part into one of the slots (30a, 30b, 30c) of an edge of a first ring sector and for a second part into one of the slots (30a, 30b, 30c) of an edge of a second ring sector, circumferentially adjacent to the first ring sector, the assembly being characterized in that the sealing member is made of a ceramic matrix composite.

Methods, apparatus, systems and articles of manufacture are disclosed for a compressor including a rotor defining a circumferential direction, wherein the rotor includes a slot, the slot including a first neck portion, a first blade and a second blade disposed circumferentially apart in the slot, and a block disposed in the slot circumferentially between the first blade and the second blade, the block including second neck portion, the first neck portion to at least partially interface the second neck portion.