Abstract: An assembly is provided for a turbine engine. This assembly includes an engine core extending along an axis. The engine core includes a compressor section, a combustor, a diffuser structure, a diffuser plenum and a separator. The combustor is arranged within the diffuser plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the diffuser plenum. The combustor wall includes a dilution aperture extending through the combustor wall to the combustion chamber. The diffuser structure includes a first diffuser passage and a second diffuser passage radially offset from the first diffuser passage. The first diffuser passage fluidly couples the compressor section to the diffuser plenum. The second diffuser passage fluidly couples the compressor section to the separator. The separator fluidly couples the second diffuser passage to the dilution aperture.

Abstract: A gas turbine engine component includes a substrate having first surface and a second surface disposed opposite the first surface, a plurality of holes extending through the substrate from the first surface to the second surface, the holes defined by a plurality of respective walls each extending from the first surface to the second surface, a metallic bond coat disposed on the first surface, and an aluminide coating disposed on the first surface, the second surface, and the walls. The metallic bond coat is disposed between the first surface and the aluminide coating and the walls are free of the metallic bond coat.

Abstract: A nose cone for debris deflection comprising a deflector formed in the nose cone, and an actuator in operative communication with the deflector, the actuator configured to engage the deflector configured to create a deflection air stream; the deflection air stream being configured to manipulate a fan inlet air flow such that any debris entrained in the fan inlet air flow has a trajectory line directed away from a core flow of a gas turbine engine and toward a bypass flow of the gas turbine engine.

Abstract: A counter weight for use with a rotor module, including: a root portion; a main body portion that extends away from the root portion; a pair of side portions each extending from opposite sides of the main body portion; and at least one plate secured to one of the opposite sides of the main body portion in order to adjust a weight of the counter weight.

Abstract: An article includes a barrier layer disposed on a bond coat. The barrier layer includes diffusive particles and gettering particles disposed in a matrix. The article also includes a machinable coating disposed on the barrier layer. A method of applying a coating to an article is also disclosed.

Abstract: A combustor assembly for a gas turbine engine includes a combustor liner disposed about an axis and defining a combustion chamber and an outer case disposed about the combustor liner and defining an air flow duct therebetween. The combustor liner includes an outer wall having a plurality of mounting bosses and a plurality of first holes open to the combustion chamber. The outer case includes a plurality of inlet scoops extending radially inward of the outer case and radially aligned with the plurality of first holes to guide an air flow into first holes. A plurality of pins is fixed to the outer case and slidingly received in openings in the plurality of mounting bosses.

Abstract: A special tool in intermediate form, comprising: at least one aft core module having at least one aft alignment aperture and at least one baffle; a forward core having at least one forward alignment aperture, the at least one aft core module and the forward core disposed adjacent to and aligned with one another; at least one alignment tool disposed within each at least one aft alignment aperture, and aligned with and also disposed within each at least one forward alignment aperture; and a preform material disposed about the adjacent, aligned aft core and forward core.

Abstract: An under-root fan blade spacer system including a fan hub including a fan hub receiver, the fan hub receiver having a hub receiver floor, the fan hub receiver having an opening configured to receive a fan blade root, the fan blade root includes a base end; a gap formed between the base end of the fan blade root and a hub receiver floor; and a spacer disposable within the gap, the spacer comprising a shape memory alloy material.

Abstract: A method for oxide formation on the surface of a ring includes: mounting a ring in a fixture; driving rotation of the ring about a first axis; contacting an outer diameter surface of the ring with a roller; and laser heating the outer diameter surface of the ring to form an oxide layer. The rotation causes compaction of the oxide by the roller.

Abstract: A brush seal of a turbine engine may provide a cooling flow to a ceramic matrix composite (CMC) component that has a hot side exposed to a hot gas path and an opposing cold side. The brush seal includes an inner diameter (ID) backing plate providing a radial face seal across a cavity in the CMC component. The brush seal also includes an outer diameter (OD) backing plate, a plurality of brush seal bristles disposed between the ID and OD backing plates, and a hole extending through the brush seal to provide the cooling flow to the cavity of the CMC component. A cross-flow channel is disposed on an inner surface of the ID backing plate such that the cross-flow channel extends from an edge of the ID backing plate to the hole to pass leakage air to mix with the cooling flow and reduce an impingement cooling effect thereof.

Abstract: Environmental barrier coatings (EBCs) are disclosed having a topcoat layer having a primary hafnon phase and a dispersed hafnia phase. The hafnia can be homogeneously dispersed or the layer can exhibit a concentration gradient in which the hafnia concentration increases continuously or stepwise. The hafnon primary phase provides a desirable CTE match with the underlying CMC substrate, while the dispersed hafnia provides desirable corrosion resistance.

Abstract: A gas turbine engine stator stage has: a case; a plurality of vane clusters; and a plurality of vane singlets. The plurality of vane clusters each have: an inner diameter first platform; an outer diameter first shroud mounted to the case; and a plurality of first airfoils extending between the first platform and first shroud. The plurality of vane singlets each have: an inner diameter second platform; an outer diameter second shroud; and a single second airfoil extending between the second platform and second shroud.

Abstract: A gas turbine engine component, comprising a first surface having at least one first aperture, and exposed to a first plenum comprising a mixed fluid flow and a first pressure; at least one second surface having at least one second aperture, and exposed to a gas path fluid flow and at least one second pressure; at least one channel, at least one internal plenum or both at least one channel and at least one internal plenum disposed between and in fluid communication with each the at least one first aperture and the at least second aperture.

Abstract: A brush seal for use with a ceramic matrix composite (CMC) component of a gas turbine engine may feed a cooling flow to the CMC component, which has a hot side configured for exposure to a hot gas path of the gas turbine engine and an opposing cold side having a cavity for feeding a cooling flow to at least one film cooling hole of the CMC component. The brush seal includes: an outer diameter (OD) backing plate; an inner diameter (ID) backing plate; a plurality of brush seal bristles sandwiched between the OD backing plate and the ID backing plate; at least one hole forming a passage extending through the OD backing plate, the brush seal bristles, and the ID backing plate; and a cover plate attached to an inner surface of the ID backing plate and configured to extend into the cavity of the CMC component.

Abstract: The disclosure describes methods and devices for directing cooling air to cool CMC components. A baffle member or splash plate is used to direct the flow of cooling air towards an outer radial surface of a CMC component into a one or more cooling cavities provided within the interior of the CMC component. The splash plate provides an efficient distribution of cooling air into the one or more cooling cavities and aids in the cooling of the component to reduce the formation of thermal stresses induced by the thermal differential between the outer radial surface (cold side) and inner radial surface (hot side) of the component.

Abstract: A piston seal ring for sealing between an inner and an outer radial component includes a core having a shell, wherein the core includes a material selected from the group consisting of titanium alloy, titanium-based metal matrix, carbon-carbon composite, electro-graphitic carbon, ceramic matrix composite and combinations thereof, and wherein the shell includes a material selected from the group consisting of nickel alloy, cobalt alloy and combinations thereof.

Abstract: A thermo-cell includes a first electrode and a second electrode defining a space therebetween with an electrolyte disposed within the space. At least one p-type membrane is positioned in the space and facing the first electrode and at least one n-type membrane is positioned in the space and facing the second electrode. The p-type membrane and the n-type membrane are physically separated and create an electric field gradient through the space for the selective transport of ions within the electrolyte. A system including a plurality of such thermo-cells arranged to be electrically coupled is also provided.

Abstract: The disclosure describes methods and devices for directing/controlling cooling air flow for cooling CMC components. A cover plate is positioned within a cooling cavity in the CMC component wherein the cover plate is angled to vary the depth of the cooling cavity between the cover plate and a bottom wall of the cavity. The angled cooling plate can be used to vary the flux of cooling air within the cooling cavity and thereby achieve a desired cooling performance within the cooling cavity.

Abstract: A ceramic matrix composite (CMC) component segment forming a portion of a substantially ring-shaped gas turbine engine stage includes a mateface extending axially between an upstream end and a downstream end of the CMC component and configured to form an inter-segment gap with an adjacent CMC component, and a plurality of film cooling holes having diffused openings at the mateface to provide film cooling of the mateface. A method of providing an inter-segment purge flow to such a CMC component includes disposing a first mateface of the CMC component segment next to a second mateface of an adjacent CMC component segment to form an inter-segment gap, and providing first film cooling of the first mateface via the plurality of film cooling holes having diffused openings at the first mateface.

Abstract: Attachment pins are used to attach a ceramic matrix composite (CMC) component to a support structure, the attachment pins passing through openings in flange structures extending from a surface of the CMC component. The attachment pins are provided with a cooling air passageway extending in an axial direction, the cooling passageway having an inlet opening in a first end of the attachment pin for introduction of cooling air, and each attachment pin having one or more cooling air outlets extending radially from the cooling air passageway to provide for discharge of cooling air in a desired direction.