Patent ID: 8647053

Claim:
A turbine component comprising a wall having 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 component characterized by: a chamber in the wall, the chamber enclosed by side and end surfaces and a cover plate, the chamber comprising an impingement cooling zone, a film cooling zone, and a convection cooling zone there between; the impingement cooling zone comprising a plurality of impingement holes that admit and direct jets of the coolant gas into an impingement cooling plenum to impinge against the wall within the impingement cooling zone; the convection cooling zone comprising a plurality of heat-transfer elements that increase a surface area of the wall exposed to the coolant gas in the convection cooling zone; and the film cooling zone comprising a film cooling plenum receiving the coolant gas from the convection cooling zone and a plurality of film cooling holes between the film cooling zone 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 into the impingement cooling plenum, thence through the convection cooling zone 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 going into the convection cooling 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.