Patent ID: 7104751

Claim:
A hot gas pat assembly for a turbomachine, the hot gas path assembly comprising: an operation hot gas flow direction; a cross-section selected from the group consisting of annular and annulus-section shaped; a cooling side and a hot gas side, with hot gas flowing over a surface of the hot gas side in the operation hot gas flow direction during operation; at least one gas-permeable element configured and adapted for transpiration cooling and at least one gas-impermeable element, the gas-permeable element and the gas-impermeable element being arranged in different positions on a wall of a hot gas path in the operation hot gas flow direction; the gas-impermeable element being configured and adapted for impingement cooling, with an impingement cooling element being arranged on the cooling side at a distance from te gas-impermeable element, a coolant path being formed on the cooling side of the assembly, and with the coolant path leading from the impingement cooling element to a coolant side of the gas-permeable element; at least one dividing wall configured and adapted for subdividing the coolant path into a multitude of fluidly isolated segments in a circumferential direction; and an airfoil arranged on the gas-impermeable element; wherein the at least one dividing wall for subdividing the coolant path is arranged essentially parallel to profile chords of the airfoil.