Cooled wall of a turbine component and a method for cooling this wall

A gas turbine comprising:

• a combustor liner including a wall configured to be cooled during an operation of the gas turbine, the wall including:
• a first layer of channels for a coolant arranged along a first side of the wall facing to a hot gas flow path, said channels of said first layer of channels having a serpentine shape with a repeating pattern of curves along an axial extension of the channel and, each channel of said first layer having an inlet and an outlet;
• a second layer of channels for the coolant arranged along a second side of the wall facing a coolant flow and opposite to the first side of the wall facing to the hot gas flow path, each channel of said second layer having an inlet and an outlet, said outlet of each of said channels of said first layer configured to be in fluid communication with a corresponding inlet of an associated channel of said second layer via a bend for changing a direction of coolant leaving said channel of said first layer when entering the channel of said second layer, said inlet of each of said channels of said first layer and said outlet of said channels of said second layer being open on said second face;
• wherein a path of each channel of said first layer, when seen perpendicularly to the first side, crosses a path of the respective associated channel of said second layer in each repetition of said repeating pattern of curves.