A workpiece manufactured from an additive manufacturing system (AMS) having a particle separator and a method of operating includes modeling the workpiece into layers and modeling the layers into a plurality of regions. The AMS then deposits one of a plurality of particle types into a respective one of the plurality of regions. In this way, the surface finishes of the component may be controlled and material densities from one region to the next and from one layer to the next are also controlled.

Turbine assemblies, loss recovery systems, and related fabrication methods are provided for managing temperatures associated with an electrical generator. One exemplary turbine assembly suitable for use in a loss recovery system includes a wheel configured to rotate in response to a portion of a fluid flow bypassing a flow control valve, a generator including a stator assembly disposed about a rotor coupled to the wheel to rotate in response to rotation of the wheel, a conductive structure in contact with the stator assembly, and an insulating structure radially encompassing the conductive structure and the generator. The conductive structure accesses at least a portion of the fluid flow bypassing the flow control valve and impacting the wheel, thereby providing thermal coupling between the stator assembly and the bypass fluid flow to transfer heat from the stator assembly to the bypass fluid flow via the conductive structure.

A turbocharger (1) in which the bearing-housing-side diffuser wall is thermally decoupled in order to reduce the heat introduction at the bearing housing cover (5). The turbocharger (1) includes a turbine (2), a compressor (3) which has a diffuser, and a bearing housing (4) which is arranged between the turbine (2) and the compressor (3) and which has the bearing housing cover (5). The bearing housing cover (5) is composed of a material with a low thermal conductivity of at most 5 W/mK, for example a temperature-resistant plastic.

A turbomachine includes a compressor configured to compress air received at an intake portion to form a compressed airflow that exits into an outlet portion. A combustor is operably connected with the compressor, and receives the compressed airflow. A turbine is operably connected with the combustor, and receives the combustion gas flow. The turbine has a plurality of wheels and a plurality of buckets. The turbine receives compressor bleed off air to cool the wheels and buckets. A cooling system is operatively connected to the turbine. The cooling system includes a plurality of heat pipes located axially upstream of at least one of the wheels. The heat pipes are operatively connected to a bearing cooler system. The heat pipes and the bearing cooler system are configured to transfer heat from the compressor bleed off air to one or more heat exchangers.

A thermally conductive lightweight elastomeric seal including a stator substrate having an external surface; a casing coupled to the external surface, the casing including radial walls extending orthogonal radially from the external surface; an abradable material disposed within the casing, the abradable material comprises an elastomer material with imbedded metal-coated hollow microspheres, wherein the abradable material comprises a density of 0.5 to 0.6 grams/cubic centimeter; the abradable material and the casing being coupled together.

A heat exchanger (2) comprising a duct (4) through which a first fluid (e.g. a coolant such as ram air) may flow, and one or more vanes (18) disposed within the duct (4) and configured to disrupt the flow of the first fluid through the duct (4). Each vane (18) comprises one or more flow channels (24) through which a second fluid (e.g. a fluid to be cooled, such as engine coolant) may flow so as to transfer heat between the first fluid flowing through the duct (4) and the second fluid flowing through the one or more flow channels (24). The flow channels (24) within the vanes (18) are separated from the duct (4) by a channel wall such that fluid cannot flow between the duct (4) and the flow channels (24).

A wrap configured to cover a surface of a casing surrounding a rotating member includes one or more graphene sheets and a matrix configured to stabilize the one or more graphene sheets. The matrix further configured to receive an adhesive or mechanical fastener and to bond to a surface of the casing using the adhesive or mechanical fastener. The wrap is further configured to facilitate heat transfer over the casing, to structurally reinforce the casing, and to enhance containment resilience.

A method for joining engine components includes positioning a first plurality of thermal protection structures across a thermal protection space between a first thermal protection surface and a second thermal protection surface. The first and second engine components are locally joined by forming a first plurality of transient liquid phase (TLP) or partial transient liquid phase (PTLP) bonds along corresponding ones of the first plurality of thermal protection structures between the first thermal protection surface and the second thermal protection surface. The second thermal protection surface is formed from a second surface material different from a first surface material of the first thermal protection surface.

An article and method of forming an article are provided. The article includes a body portion having an inner surface and an outer surface, the inner surface defining an inner region, and at least one cooling feature positioned within the inner region. The body portion includes a first material and the at least one cooling feature includes a second material, the second material having a higher thermal conductivity than the first material. The method includes manufacturing a body portion by an additive manufacturing technique and manufacturing at least one cooling feature by the additive manufacturing technique. The body portion includes a first material and the at least one cooling feature includes a second material, the second material having a higher thermal conductivity than the first material.

Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.