A wall assembly that may be for a combustor of a gas turbine engine includes a liner having a hot face that defines a combustion chamber, an opposite cold face, and a plurality of effusion holes. A shell of the assembly is spaced outward from the cold face and includes a plurality of impingement holes each having a centerline orientated substantially normal to the cold face. A plurality of cooling member arrays of the liner each include a first plurality of members that may be pins projecting outward from the cold face to conduct heat out of the liner. Each array is spaced between adjacent effusion holes and is symmetrically orientated about the respective centerline.

A downhole torch system and method of use includes a cylindrical housing, a protective material provided on at least one of the cylindrical housing and the fuel load, and a fuel load located within the cylindrical housing. The protective material is provided between the fuel load and the cylindrical housing to protect the cylindrical housing from adverse effects caused by the reaction of the burning fuel and/or the subsequent production of combustion products for cutting and/or perforating processes during operation of the torch system. The protective material significantly improves the cutting and/or perforating performance of the torch system.

According to one embodiment, a heat shield panel for a combustor of a gas turbine engine is provided. The heat shield comprising: a panel body having a first surface configured to be oriented toward a combustion zone of a combustor, and a second surface opposite the first surface, the second surface being configured to be oriented toward a combustor liner of the combustor; a plurality of first pin fins projecting from the second surface of the panel body, wherein each of the plurality of first pin fins has a rounded top opposite the second surface; and one or more second pin fins projecting from the second surface of the panel body, wherein each of the one or more second pin fins has a flat top opposite the second surface.

According to one embodiment, a heat shield panel for a combustor of a gas turbine engine is provided. The heat shield comprising: a panel body having a first surface configured to be oriented toward a combustion zone of a combustor, and a second surface opposite the first surface, the second surface being configured to be oriented toward a combustor liner of the combustor; a plurality of first pin fins projecting from the second surface of the panel body, wherein each of the plurality of first pin fins has a rounded top opposite the second surface; and one or more second pin fins projecting from the second surface of the panel body, wherein each of the one or more second pin fins has a flat top opposite the second surface.

Methods for preparing slotted ceramic coatings and the resulting components comprising the same are provided. The methods and products include the incorporation of a coating system comprising a ceramic coating with cooling holes disposed throughout the ceramic coating and slots defined in the thermal barrier coating and disposed in relation to the cooling holes. The resulting ceramic coating has improved resistance to CMAS infiltration and improved compliance resulting in an increased life of the coated component.

A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved.

A machine component including a base body produced from a base material is provided. The base body is equipped in a partial region of the surface thereof with a plating made of an application material having a greater hardness and/or viscosity as compared to the base material. The plating is foamed by a number of plating elements that are applied to the base body in the longitudinal direction thereof in a tilted manner relative to the main flow direction of a hot gas flowing through the base body.

A combustor for a liquid propellent motor has an elongated hollow tubular casing having an inner wall delimiting a combustion chamber for the liquid propellent and an outlet nozzle for the combustion products, and an outer wall, both being coaxial to an axis of the casing; the inner and outer walls being spaced apart from each other in radial direction and delimiting at least one guiding conduit of a cooling fluid therebetween; a plurality of bar-shaped elements extending into the guiding conduit, which form a grid for perturbing the cooling fluid, stiffening the casing and increasing the heat exchange surface; the grid being part of a body made in one piece and of a single material along with the inner and outer walls.

The present disclosure discloses a combustion chamber and a combustion apparatus. The combustion chamber includes: a first surrounding plate located on an outer side and a second surrounding plate located on an inner side. A combustion cavity is defined by the second surrounding plate. The first surrounding plate and the second surrounding plate are spaced apart from each other to define at least one air duct in communication with the combustion cavity. Each of the at least one air duct has an air inlet hole formed in the first surrounding plate, and an air outlet hole formed in the second surrounding plate.