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An apparatus for removing heat from a turbine includes a stator having a cavity and a first plenum and a second plenum inside the cavity. The second plenum is connected to the first plenum and surrounds the first plenum inside the cavity. A refrigerant flows through the first plenum and the second p

An apparatus for removing heat from a turbine includes a stator having a cavity and a first plenum and a second plenum inside the cavity. The second plenum is connected to the first plenum and surrounds the first plenum inside the cavity. A refrigerant flows through the first plenum and the second plenum to remove heat from the stator. A method for cooling a turbine includes forming a cavity in a component to be cooled, installing a first plenum inside the cavity, and installing a second plenum inside the cavity. The method further includes connecting the second plenum to the first plenum, surrounding the first plenum with the second plenum inside the cavity, and flowing a refrigerant through the first plenum and the second plenum to cool the component.

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1. An apparatus for removing heat from a gas turbine having one or more combustors and a turbine, comprising: a. a component in the gas turbine, wherein the component includes a cavity therein;b. a first plenum inside the cavity;c. a second plenum inside the cavity and connected to the first plenum,

1. An apparatus for removing heat from a gas turbine having one or more combustors and a turbine, comprising: a. a component in the gas turbine, wherein the component includes a cavity therein;b. a first plenum inside the cavity;c. a second plenum inside the cavity and connected to the first plenum, wherein the second plenum surrounds the first plenum inside the cavity;d. a refrigerant flowing through the first plenum and the second plenum to remove heat from the component, wherein the first and second plenums define a closed loop for the refrigerant;e. a plurality of apertures through the closed loop that provide fluid communication for cooling air supplied to flow though the plurality of apertures and around the closed loop; andf. wherein one of the first or second plenums provides refrigerant flow out of the cavity. 2. The apparatus of claim 1, wherein the first plenum and the second plenum are substantially concentric tubes. 3. The apparatus of claim 1, wherein the second plenum defines the plurality of apertures therethrough. 4. The apparatus of claim 1, further including an emissivity coating on the second plenum. 5. The apparatus of claim 1, wherein the component in the gas turbine is a stator in the turbine. 6. The apparatus of claim 1, wherein the component in the gas turbine is a casing surrounding the turbine. 7. The apparatus of claim 1, wherein the refrigerant has a specific heat capacity greater than 1.5 kJ/kg C. 8. The apparatus of claim 1, wherein the refrigerant is fuel. 9. An apparatus for removing heat from a turbine, comprising: a. a stator;b. a cavity inside the stator;c. a first plenum inside the cavity;d. a second plenum inside the cavity and connected to the first plenum, wherein the second plenum surrounds the first plenum inside the cavity;e. a refrigerant flowing through the first plenum and the second plenum to remove heat from the stator wherein the first and second plenums define a closed loop for the refrigerant;f. a plurality of apertures through the closed loop that provide fluid communication for cooling air supplied to the cavity to flow through the plurality of apertures and around the closed loop; andg. wherein one of the first or second plenums provides refrigerant flow out of the cavity. 10. The apparatus of claim 9, wherein the first plenum and the second plenum are substantially concentric tubes. 11. The apparatus of claim 9, wherein the second plenum defines the plurality of apertures therethrough. 12. The apparatus of claim 9, further including an emissivity coating on the second plenum. 13. The apparatus of claim 9, wherein the refrigerant has a specific heat capacity greater than 1.5 kJ/kg C. 14. The apparatus of claim 9, wherein the refrigerant is fuel. 15. An apparatus for removing heat from a gas turbine having one or more combustors and a turbine, comprising: a. a component in the gas turbine, wherein the component includes a cavity therein;b. a closed loop cooling system inside the cavity, wherein the closed loop cooling system includes a supply plenum connected to an exhaust plenum inside the cavity;c. a refrigerant flowing through the supply and exhaust plenums;d. a plurality of apertures through the closed loop cooling system, wherein the plurality of apertures provide fluid communication for cooling air supplied to the cavity to flow through the plurality of apertures and around the closed loop cooling system. 16. The apparatus of claim 15, wherein the supply plenum and the exhaust plenum are substantially concentric tubes. 17. The apparatus of claim 15, wherein the refrigerant has a specific heat capacity greater than 1.5 kJ/kg C. 18. The apparatus of claim 15, wherein the refrigerant is fuel.