Abstract: A method for forming a coating system on a component includes depositing a reactive layer with predetermined CMAS reaction kinetics on at least a portion of a thermal barrier coating. The method also includes activating the reactive layer with a scanning laser. A component, such as a gas turbine engine component, includes a substrate, a thermal barrier coating and a reactive layer. The thermal barrier coating is deposited on at least a portion of the substrate. The reactive layer is deposited on at least a portion of the thermal barrier coating. The reactive layer has predetermined CMAS reaction kinetics activated by laser scanning.

Abstract: A turbine engine component has a first portion and a hotspot portion with both portions being substantially covered with a thermal barrier coating (TBC). The hotspot portion may be additively manufactured to the first portion. Furthermore, the hotspot portion may have a single crystal microstructure to resist high temperatures and the first portion may not have such a microstructure and may further be cast. A method of forming the component includes the steps of casting the first portion and additively manufacturing the hotspot portion to the first portion, then covering the first and hotspot portion with the TBC.

Abstract: A method for forming a coating system on a component includes depositing a reactive layer with predetermined CMAS reaction kinetics on at least a portion of a thermal barrier coating. The method also includes activating the reactive layer with a scanning laser. A component, such as a gas turbine engine component, includes a substrate, a thermal barrier coating and a reactive layer. The thermal barrier coating is deposited on at least a portion of the substrate. The reactive layer is deposited on at least a portion of the thermal barrier coating. The reactive layer has predetermined CMAS reaction kinetics activated by laser scanning.

Abstract: A method for forming a coating system on a component includes depositing a reactive layer with predetermined CMAS reaction kinetics on at least a portion of a thermal barrier coating. The method also includes activating the reactive layer with a scanning laser. A component, such as a gas turbine engine component, includes a substrate, a thermal barrier coating and a reactive layer. The thermal barrier coating is deposited on at least a portion of the substrate. The reactive layer is deposited on at least a portion of the thermal barrier coating. The reactive layer has predetermined CMAS reaction kinetics activated by laser scanning.

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 turbine engine component has a first portion and a hotspot portion with both portions being substantially covered with a thermal barrier coating (TBC). The hotspot portion may be additively manufactured to the first portion. Furthermore, the hotspot portion may have a single crystal microstructure to resist high temperatures and the first portion may not have such a microstructure and may further be cast. A method of forming the component includes the steps of casting the first portion and additively manufacturing the hotspot portion to the first portion, then covering the first and hotspot portion with the TBC.

Abstract: A method for forming a coating system on a component includes depositing a reactive layer with predetermined CMAS reaction kinetics on at least a portion of a thermal baffler coating. The method also includes activating the reactive layer with a scanning laser. A component, such as a gas turbine engine component, includes a substrate, a thermal baffler coating and a reactive layer. The thermal baffler coating is deposited on at least a portion of the substrate. The reactive layer is deposited on at least a portion of the thermal baffler coating. The reactive layer has predetermined CMAS reaction kinetics activated by laser scanning.

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 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: A process for forming a coating system on a turbine engine component comprises the steps of providing a substrate, depositing a thermal barrier coating on the substrate, depositing a reactive with known CMAS reaction kinetics on the thermal barrier coating, and activating the reactive layer prior to the component being placed in service. As a result of the foregoing process, there is provided a turbine engine component which has a substrate, a thermal barrier coating deposited on the substrate, a reactive layer deposited on the thermal barrier coating, which reactive layer has known CMAS reaction kinetics and is activated prior to the turbine engine component entering into service.

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.