Cooling arrangement for a turbine component

A cooling arrangement for a turbine component wall with a combustion gas on a first side of the wall and a coolant gas on an opposed second side of the wall, wherein the coolant gas has a higher pressure than the combustion gas, the cooling arrangement comprising:

• a chamber in the wall, the chamber enclosed by side and end surfaces and a cover plate, the chamber comprising an impingement cooling plenum, a film cooling plenum, and a plurality of heat transfer elements forming a convection zone there between;
• a plurality of impingement holes through the cover plate that admit and direct jets of the coolant gas to impinge against the wall within the impingement cooling plenum;
• and
• a plurality of film cooling holes through the wall between the film cooling plenum and the first side of the wall that direct a film of the coolant gas along the first side of the wall;
• wherein a flow of the coolant gas follows a continuous path from the impingement holes to the impingement cooling plenum, thence among the heat transfer elements to the film cooling plenum, thence to the film cooling holes, and thence along the first side of the turbine component wall;
• wherein the impingement cooling plenum defines a single outflow direction for the coolant gas flow to the convection zone;
• and
• wherein the convection cooling zone comprises metering of the coolant gas that produces a coolant pressure drop between the impingement cooling plenum and the film cooling plenum and the film cooling holes provide further metering, producing four pressure zones wherein the pressure of the coolant gas is higher than a pressure in the impingement plenum, which in turn is higher than a pressure in the film cooling plenum, which in turn is higher than the pressure of the combustion gas.