Abstract:
A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
Abstract:
A liner panel is provided for a combustor of a gas turbine engine. The liner panel includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a depression, where the depression includes an entrance to at least one passage through the liner panel.
Abstract:
A self-cooled orifice structure, for example a dilution hole structure for a combustor of a gas turbine engine, includes a cold side panel spaced from a hot side panel, and a continuous inner wall extending between the hot and cold side panels and defining an orifice communicating through the hot and cold side panels. A plurality of end walls of the structure are in a cooling cavity that is defined in-part by the hot and cold side panels and the inner wall. Each end wall extends between and are engaged to the hot and cold side panels and are circumferentially spaced from the next adjacent end wall. A plurality of inlet apertures extend through the cold side panel, in fluid communication with the cavity, and proximate to a first side of the end walls. A plurality of outlet apertures extend through the hot side panel, in fluid communication with the cavity, and associated with an opposite second side of the end walls.
Abstract:
A liner panel for a combustor of a gas turbine engine includes a multiple of heat transfer augmentors. At least one of the multiple of heat transfer augmentors includes a cone shaped pin.
Abstract:
A liner panel is provided for use in a gas turbine engine. The liner panel includes an intermediate rail that extends from a cold side of a liner panel. The liner panel also includes a multiple of heat transfer augmentors, which generally decrease in height with respect to a distance from the intermediate rail.
Abstract:
A combustor wall is provided for a turbine engine. The combustor wall includes a combustor shell and a combustor heat shield that is attached to the shell. The heat shield includes a first panel and a second panel that sealingly engages the first panel in an overlap joint. A cooling cavity extends between the shell and the heat shield and fluidly couples a plurality of apertures in the shell with a plurality of apertures in the heat shield.