Abstract: A liner panel for a combustor of a gas turbine engine includes a nominal wall thickness and a thickened wall thickness in the region of a hot spot.

Abstract: A component assembly includes a support structure, a ceramic substrate mounted to the support, and a foam-like coating adhered to one of the support structure and the ceramic substrate. The foam-like coating engages the other of the support structure and the ceramic substrate.

Abstract: A gas turbine engine component includes a wall that provides exterior and interior surfaces. The interior surface faces an internal cooling passage of the gas turbine engine component. An aperture extends through the wall and interconnects the interior and exterior surfaces to one another and is configured to provide a cooling fluid from the cooling passage to the exterior surface. The aperture has first and second outlet holes overlapping one another at an intersection to provide opposing sharp corners at the intersection.

Abstract: A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.

Abstract: Disclosed are exemplary structures with adaptive cooling and methods of adaptively cooling structures. A liner is affixed to a support and the liner deflects away from the support when exposed to a localized hot spot in a hot fluid stream. The liner deflection creates a chamber between the liner and support, allowing cooling air to impinge against the liner, thus mitigating the effects of the hot spot. By providing impingement cooling only where needed, the amount of air needed for cooling is reduced.

Abstract: A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert at least partially between opposed surfaces of the support shell and the heat shield panel, the insert exposed to a combustion chamber, and the insert being flush with a hot side of the heat shield.

Abstract: A rotor of a turbine engine includes a mounting slot for receiving a blade. The example blade is formed from a ceramic material and is received within the mounting slot. An intumescent material is disposed within the mounting slot between the blade and an inner surface of the mounting slot and expanded by the application of heat for securing the blade within the mounting slot.

Abstract: A component assembly includes a support structure, a ceramic substrate mounted to the support, and a foam-like coating adhered to one of the support structure and the ceramic substrate. The foam-like coating engages the other of the support structure and the ceramic substrate.

Abstract: A liner panel for a combustor of a gas turbine engine includes a nominal wall thickness and a thickened wall thickness in the region of a hot spot.

Abstract: A gas turbine engine component includes a wall that provides exterior and interior surfaces. The interior surface faces an internal cooling passage of the gas turbine engine component. An aperture extends through the wall and interconnects the interior and exterior surfaces to one another and is configured to provide a cooling fluid from the cooling passage to the exterior surface. The aperture has first and second outlet holes overlapping one another at an intersection to provide opposing sharp corners at the intersection.

Abstract: A component within a gas turbine engine includes a surface with one or more upstream-directed cooling film holes therethrough.

Abstract: A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions.

Abstract: A combustor component of a gas turbine engine includes a substrate with a cold side, a central core section and a hot side, the cold side and the hot side have a porosity different than the central core section.

Abstract: Floatwall panel assemblies and related systems are provided. A floatwall panel assembly includes a panel formed of porous ceramic material, the porous ceramic material exhibiting a porosity gradient along at least one of a length, a width and a depth of the panel, the panel lacking a substrate, formed of a material other than porous ceramic material, for supporting the porous ceramic material.

Abstract: A combustor assembly includes a support structure and at least one combustor liner panel selectively attached to the support structure. The combustor liner panel includes an uncooled ceramic portion, a cooled ceramic portion and a support that receives the cooled ceramic portion.

Abstract: A gas turbine article includes a substrate and a thermally insulating topcoat disposed on a surface of the substrate. The surface of the substrate includes a surface pattern defining first surface regions and second surface regions. The first surface regions include incubation sites that are favorable for deposition of the thermally insulating topcoat and the second surface regions are less favorable for deposition of the topcoat. The topcoat includes segmented portions that are separated by faults extending through the topcoat from the second regions.

Abstract: A combustor liner segment seal member is provided that includes a center section, a forward flange, and an aft flange. The center section includes a base surface, a gas path surface, a forward side surface, and an aft side surface. The forward flange extends outwardly from the forward side surface, and includes a width, a height, a shell side surface, and a liner side surface. The aft flange extends outwardly from the aft side surface, and includes a width, a height, a shell side surface, and a liner side surface.

Abstract: A combustor for a gas turbine engine is provided that includes a support shell, a forward liner segment, an aft liner segment, and a seal member. The support shell has an interior surface, and exterior surface, and a plurality of impingement apertures disposed within the shell. The forward liner segment and aft liner segment are attached to the inner surface of the shell. The forward liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The aft liner segment has an edge surface extending between a face surface and a back surface, and a seal shoulder. The forward liner segment and the aft liner segment are separated from one another by a gap. The seal member is disposed within the gap. At least some of the plurality of impingement apertures disposed within the shell are aligned with the seal member and oriented to direct cooling air to impinge on the seal member.

Abstract: A combustor of a gas turbine engine includes a heat shield panel mounted to a support shell and an insert adjacent to the support shell and the heat shield panel.

Abstract: An adaptive cooling structure comprises a mounting support, a liner, and a spacer. The mounting support has a coolant aperture for directing cooling air through the support. The liner has a first surface facing away from the mounting support and a second surface facing towards the support. The liner is coupled to the mounting support, and the spacer is positioned between the support and the liner. The positioning of the spacer creates a chamber between the mounting support and the liner, thus allowing the cooling air to impinge on the second surface of the liner. The liner wall is configured to deflect away from the mounting support to expand the chamber, thus allowing the cooling air to further impinge on the second surface of the liner.