A heat exchanger includes a plurality of fins arranged as a network and delimiting corridors, and an envelope having an internal wall and an external wall, the internal and external walls delimiting between them a channel for a flow of a first fluid in a main direction, the network of fins being arranged in the channel and connected to the internal and external walls, at least one passage for a flow of a second fluid being embedded in at least one of the internal and external walls, the channel being, in the main direction, divergent and then convergent.

A manufacturing method is provided. During this method, a preform component is provided for a turbine engine. The preform component includes a substrate. A meter section of a cooling aperture is formed in the substrate. An internal coating is applied onto a surface of the meter section. An external coating is applied over the substrate. A diffuser section of the cooling aperture is formed in the external coating and the substrate to provide the cooling aperture.

A coated component of a gas turbine engine includes a substrate defining a surface, a thermal barrier coating deposited on the surface of the substrate, a region of the component where the thermal barrier coating has spalled from the substrate, a layer of environmental contaminant compositions formed on one or more of the thermal barrier coating or the region of the component where the thermal barrier coating has spalled from the substrate in response to an initial exposure of the component to high operating temperatures of the gas turbine engine, and a thermal barrier coating (TBC) restoration coating deposited at least on the region of the component where there thermal barrier coating has spalled from the substrate.

A method of fabricating an airfoil includes drawing a continuous woven fabric ply over a contoured surface that has a geometry that is analogous to a geometry of an airfoil. The continuous woven fabric ply takes the geometry of the contoured surface to thereby form a contoured continuous woven fabric ply. The contoured continuous woven fabric ply is then wrapped around an airfoil tool to produce an airfoil preform. The airfoil tool has a geometry that is analogous to the airfoil. The contoured continuous woven fabric ply takes the geometry of the airfoil tool. The airfoil preform is then densified with a ceramic matrix to produce a ceramic matrix composite airfoil.

A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.

An electroformed heat exchanger suitable for use between rotating blades and seals in a stationary casing of a turbine engine. The heat exchanger comprising a non-electroformed carrier plate having a radial outer surface and a radial outer surface, an electroformed duct provided along the radial outer surface, an electroformed rail provided on the radial inner surface, and an electroformed stiffener formed by a portion of the electroformed duct and the electroformed rail.

A lubrication system for an attritable engine includes a bearing chamber, a fluid filtering inlet configured to receive a fluid, and a fluid filtering outlet located downstream of the fluid filtering inlet and configured to deliver the fluid to the bearing chamber. The lubrication system also includes a lattice, integral and conformal with the attritable engine, configured to filter the fluid, and located between the fluid filtering inlet and the fluid filtering outlet. The lubrication system also includes a metering port, configured to meter the fluid and located downstream of the lattice and upstream of the fluid filtering outlet.

A sealing structure for a gas turbine engine including a plurality of cells connected to each other is provided. Each cell includes a plurality of walls and the plurality of walls defines a polygonal shape therebetween in a cell plane. The polygonal shape includes a plurality of edges and a plurality of vertices defining a cell area in the cell plane. Each wall is shared by two adjacent cells such that each wall defines corresponding edges of the two adjacent cells. Each cell is connected to a set of adjacent cells at corresponding vertices, such that each cell and the set of adjacent cells form a plurality of connections at the corresponding vertices. The plurality of connections forms a total overlap area between each cell and the set of adjacent cells. The total overlap area is less than or equal to 10% of the cell area.

In accordance with at least one aspect of this disclosure, embodiments of fluid pumps, pump cases, valve bodies, and volutes are disclosed herein. Embodiments of methods for manufacturing fluid pumps, pump cases, valve bodies, and volutes are also disclosed herein. Embodiments can include additive manufacturing, for example. Certain embodiments can include additively manufacturing a pump case in a tilted orientation, utilizing only coincidental support structure having a unique shape, and with teardrop shaped volute and/or valve body.

In accordance with at least one aspect of this disclosure, embodiments of fluid pumps, pump cases, valve bodies, and volutes are disclosed herein. Embodiments of methods for manufacturing fluid pumps, pump cases, valve bodies, and volutes are also disclosed herein. Embodiments can include additive manufacturing, for example. Certain embodiments can include additively manufacturing a pump case in a tilted orientation, utilizing only coincidental support structure having a unique shape, and with teardrop shaped volute and/or valve body.