Abstract: A stator heat shield segment for a gas turbine includes an inner surface facing a hot gas main flow of the gas turbine; an outer surface opposite to the inner surface and at least partially exposed to cooling air; a first impingement cavity provided with a plurality of first impingement holes fluidly connected with the cooling air supplied outside the outer surface; a feeding cavity isolated from the cooling air supplied outside the outer surface and fluidly connected with first impingement cavity; and a second impingement cavity provided with a plurality of second impingement holes fluidly connected to the feeding cavity.

Abstract: A wall for a hot gas channel in a gas turbine is described, the wall having a back side and a front side and an impingement sheet having impingement cooling holes, the wall being for exposure to a hot fluid at the front side, and the wall having an array of pins attached to the back side and extending between the back side and the impingement sheet, the wall additionally having a plurality of ribs attached to the back side, each rib extending between two pins to delineate an array of cells on the back side, and/or at least one compartment wall attached to the back side to delineate compartments on the back side. Embodiments include an impingement sheet with impingement cooling holes and cooling exit holes. A gas turbine including the wall is also described.

Abstract: A stator heat shield segment for a gas turbine includes an inner surface facing a hot gas main flow of the gas turbine; an outer surface opposite to the inner surface and at least partially exposed to cooling air; a first impingement cavity provided with a plurality of first impingement holes fluidly connected with the cooling air supplied outside the outer surface; a feeding cavity isolated from the cooling air supplied outside the outer surface and fluidly connected with first impingement cavity; and a second impingement cavity provided with a plurality of second impingement holes fluidly connected to the feeding cavity.

Abstract: A wall for a hot gas channel in a gas turbine is described, the wall having a back side and a front side and an impingement sheet having impingement cooling holes, the wall being for exposure to a hot fluid at the front side, and the wall having an array of pins attached to the back side and extending between the back side and the impingement sheet, the wall additionally having a plurality of ribs attached to the back side, each rib extending between two pins to delineate an array of cells on the back side, and/or at least one compartment wall attached to the back side to delineate compartments on the back side. Embodiments include an impingement sheet with impingement cooling holes and cooling exit holes. A gas turbine including the wall is also described.