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.

Clearance control systems with thermal actuators are disclosed. An example thermally-actuated clearance control system for a gas turbine engine includes a compliant material; a high-conductive material coupled to a first surface of the compliant material, the high-conductive material thermally coupling the compliant material to a heated substance, the compliant material to expand radially-inward toward a fan blade when the high-conductive material provides heat; and an abradable material coupled to a second surface of the compliant material facing the fan blade.

The invention relates to a turbine casing of an exhaust-gas turbocharger, having an inlet connection piece adjoined by a spiral, and having an outlet connection piece, characterized by an insulating device for reducing the input of heat into the inlet connection piece, the spiral and/or the outlet connection piece.

An aircraft thrust reverser inner wall and method of manufacturing the same. The aircraft thrust reverser inner wall may include a face sheet, a perforated back sheet, and a core sandwiched between the face sheet and the perforated back sheet. The face sheet may have an inner face sheet surface and an outer face sheet surface, and the core may have an inner core surface, an outer core surface, and a plurality of cell walls extending therebetween. An electro-depositable material may be applied, via electrodeposition, in a substantially continuous layer over the outer core surface, the cell walls, and the outer face sheet surface, thus bonding the face sheet and core together. The perforated back sheet may be attached to the core at the outer core surface, and a conductive coating may be applied to the inner face sheet surface.

A method for installing an inner fixed structure (IFS) seal may comprise disposing a ceramic matrix composite (CMC) member over an inner skin of an IFS, disposing a seal retainer over the CMC member, and coupling the IFS seal to the seal retainer. The CMC member may be configured to thermally insulate the seal retainer from the IFS.

A component is disclosed, the component comprising a first material and a second material, wherein a second member made from the second material is embraced by a first member made from the first material. Further, a method is disclosed for manufacturing said component, the method comprising applying an additive manufacturing process, building up a first member from a first material by the additive manufacturing process, and adding a second member made from a second material during the additive manufacturing process and adding further first material to the first member thus embracing the second member.

A flame resistant shield includes two opposing walls between which are positioned at least: a first insulating layer, the first layer being capable of distributing heat in the plane formed by the first layer and being insulating across its thickness, a second insulating layer, one of the opposing walls which covers the first layer being produced from a refractory antioxidant material or having at least the surface intended to be exposed to flames covered with a material preventing this surface from being oxidized, the other wall being a support.

Provided are discs and bores of a gas turbine engine having one or more graphene layers and methods of preparing the same. The one or more graphene layers are disposed adjacent to the disc rim and/or bore to improve heat transfer and reduce oxidation of the discs. Methods of preparing the graphene layers and systems for using the same are provided.

In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud.

An exhaust gas turbocharger may include a compressor housing and a turbine housing. The turbine housing may be connected to the compressor housing via a plurality of spacer pins composed of a heat-insulating material. The plurality of spacer pins may respectively include a head and at least one axial pin.