A retaining member particularly suitable for use as part of a foreign material exclusion device that can be used to temporarily seal an area of a construction from foreign material or debris, wherein the retaining member includes a post adapted to be inserted through a body of the foreign material exclusion device and cap having a rim and a fitting, the latter mateably engageable with an end of the post. The post and fitting each include through bores that are alignable such that they can be connected, for example with an extraction member of the foreign exclusion material device. Foreign material exclusion devices including the retaining member are disclosed.

During a method for forming a structural panel, a core structure is formed that includes a plurality of corrugated ribbons and a plurality of walls. Each of the corrugated ribbons is laterally between a respective adjacent pair of the walls. Each of the corrugated ribbons includes a plurality of baffles and a plurality of porous septums. Each of the porous septums is longitudinally between a respective adjacent pair of the baffles. The forming of the core structure includes bonding a first of the walls to a first of the corrugated ribbons and subsequently bonding a second of the walls to the first of the corrugated ribbons. The core structure is bonded to a first skin. The core structure is bonded to a second skin. The core structure is vertically between the first skin and the second skin, and the first skin is configured with a plurality of perforations.

A heat shield may include a base portion, wherein the base portion bounds a triangular void, a top portion, wherein the top portion bounds an ovular void, and a tapered portion, wherein the tapered portion extends between the base portion and the top portion, the top portion having a smaller cross-sectional area than the base portion.

A turbine blade having a labyrinth of internal channels for circulation of coolant received through an inlet formed in a terminal portion of a blade root. A labyrinth geometry includes: (i) the inlet arranged on an axially upstream face of the terminal portion leading to an upstream duct portion having a first section adjacent the inlet and a second section having a reduced cross-section compared to the first section, (ii) a leading edge passage intersecting with the first section and extending through a blade body towards a tip of the blade, where a proximal end of the leading edge passage is angled towards a direction of incoming air flow, (iii) a main blade passage intersecting with a downstream duct portion arranged in axial alignment with, and separate from, the upstream duct portion, and (iv) a restrictor passage intersecting with a mid-blade passage and extending towards a mid-blade duct portion.

A gas turbine engine component with a core includes a first core portion configured to provide a first cooling passage. A second core portion is spaced from the first core portion and configured to provide a second cooling passage. The second core portion includes a longitudinal leg and a resupply leg transverse to and intersecting the longitudinal leg. The resupply leg has a terminal end and is configured to provide a resupply channel A connector interconnects the terminal end to the first core portion. The connector is configured to provide a resupply hole.

An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni.sub.3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.

A hybrid additive manufacturing process is utilized for creating a shrouded rotor with the shrouded rotor having a hub at a radial center, a shroud at a radial outer side, and vanes extending therebetween. The hybrid additive manufacturing process includes forming the shrouded rotor in stages, with a first stage being formed by depositing material in an axial direction through a first stage of the hub, machining an outer surface of the first stage of the hub to smooth the outer surface, depositing material on the first stage of the hub in a radial direction through a first stage of the vanes and the shroud, and machining all surfaces of the first stage of the vanes and an inner surface of the first stage of the shroud to smooth the surfaces. Subsequent stages of the shrouded rotor are formed similarly to the first stage.

A gas turbine engine component includes a structure having a wall that provides an exterior surface. A first cooling passage is arranged adjacent to and interiorly of the wall. A second cooling passage is arranged in the wall and provides a first fluid flow direction. A resupply channel is arranged in the wall and is fluidly interconnected to the second cooling passage. A resupply hole fluidly interconnects the first cooling passage and the resupply channel. The resupply channel is transverse relative to the second cooling passage to provide a second fluid flow direction that extends from the resupply hole to the second cooling passage.

A turbine blade for a turbine engine, including an aerofoil and a platform. The platform includes an internal channel having a suction opening which opens on a first surface of an upstream portion of the platform, this first surface defining a primary duct. The internal channel includes an ejection opening which opens on a second surface of a downstream portion of the platform, this second surface defining a purge cavity. The internal channel makes it possible to suck in a part of a fluid circulating in the primary duct so as to reduce the intensity of secondary flows which result from friction of the fluid on the first surface.

An intermediate duct (10) for disposition between an outlet of a low-pressure compressor and an inlet of a high-pressure compressor of a turbomachine, in particular of an aircraft engine is provided, the intermediate duct including an outer wall (2) and an inner wall (3) between which are disposed an optional exit stator ring (4) and at least one strut (12) extending radially with respect to a central axis of the intermediate duct (10). The intermediate duct (10) is at least partially manufactured by additive manufacturing. A method for manufacturing such an intermediate duct (10), and a turbomachine having such an intermediate duct (10) are also provided.