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A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes

A gas turbine engine is disclosed having a vane disposed in a flow path of a gas turbine engine component, for example a gas turbine engine compressor. The vane is in thermal contact with a heat tube that extends through a wall of the engine component and into a space in which a thermal fluid passes. The thermal fluid can be at a different temperature than the vane such that heat is transferred between the two. In one embodiment the vane forms part of an intercooler for a compressor of the gas turbine engine. The vane can have a fin disposed at the end of the heat tube to facilitate a heat transfer.

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1. An apparatus comprising: a gas turbine engine having a turbomachinery flow path between a first wall and a second wall and a heat exchange flow path external to the first wall;an airfoil member extending between the first wall and the second wall of the turbomachinery flow path and exposed to a t

1. An apparatus comprising: a gas turbine engine having a turbomachinery flow path between a first wall and a second wall and a heat exchange flow path external to the first wall;an airfoil member extending between the first wall and the second wall of the turbomachinery flow path and exposed to a turbomachinery fluid in the flow path; anda heat transferring member in thermal contact with the airfoil member and extending through the first wall and exposed to a heat exchanger fluid flowing in the heat exchange flow path, wherein the heat transferring member is incapable of having heat transfer fluid internal thereto. 2. The apparatus of claim 1, wherein a working fluid is diverted from a location in the gas turbine engine upstream of the airfoil member to form the heat exchange fluid that is flowed through the heat exchange flow path, the heat exchange fluid in the form of a cooling fluid. 3. The apparatus of claim 2, wherein the airfoil member is a compressor vane and the turbomachinery flow path is a flow path through a multistage compressor, the compressor vane forming an intercooler of the gas turbine engine. 4. The apparatus of claim 1, which further include a plurality of airfoil members, wherein the airfoil member is made from a heat conductive material, and wherein the heat exchange fluid in the heat exchange flow path is prevented from entering the airfoil member. 5. The apparatus of claim 1, wherein the airfoil member and the heat transferring member is a unitary member. 6. The apparatus of claim 1, wherein the heat transferring member operates on the basis of heat conduction to transfer heat between the airfoil member and the heat exchange flow path. 7. The apparatus of claim 1, wherein a heat from the heat transferring member is transmitted away from the airfoil member by one of convection or radiation. 8. The apparatus of claim 1, wherein the heat transfer member includes a fin formed on one end of a heat tube, the fin defined by a flattened portion of the heat tube. 9. An apparatus comprising: a gas turbine engine having a rotating component capable of changing a temperature of an airflow traversing a flow path through the rotating component;an air flow partitioning device extending between a first wall and a second wall of the flow path;a heat exchange flow path located on an outside of the first wall and capable of flowing a heat exchange airstream which remains external to the air flow partitioning device; anda thermal member having an area extending through the first wall which receives a heat exchange airstream in the heat exchange flow path and the thermal member connected to the air flow partitioning device, the thermal member capable of transferring heat between the air flow partitioning device and the heat exchange airstream in the heat exchange flow path; wherein the thermal member is always free from internal heat transfer fluid. 10. The apparatus of claim 9, which further includes a manifold having an inlet and an outlet, the manifold forming the heat exchange flow path in which the thermal member is exposed to the heat exchange airstream, wherein the manifold extends circumferentially around the rotating component to enclose a plurality of thermal members. 11. The apparatus of claim 9, wherein the heat exchange flow path extends axially along the gas turbine engine, wherein a plurality of air flow partitioning devices are located axially aft of the rotating component in the gas turbine engine, and wherein a plurality of thermal members are connected to the plurality of airflow partitioning devices located axially aft, the plurality of air flow partitioning devices located in the heat exchange flow path. 12. The apparatus of claim 11, wherein the rotating component is a compressor of the gas turbine engine and the thermal member and the air flow partitioning device form part of an intercooler of the compressor, and wherein a heat is transmitted from the thermal member using one of convection or radiation. 13. The apparatus of claim 9, wherein the thermal member includes a wall defining a hollow center. 14. The apparatus of claim 9, wherein the thermal member includes a heat flow path through a fin disposed in the heat exchange flow path, and wherein the air flow partitioning device is a vane of a compressor. 15. The apparatus of claim 14, wherein the fin is a monolithic extension of the thermal member defined by a crimped region thereof. 16. An apparatus comprising: a gas turbine engine compressor having first and second flow path walls and a row of vanes disposed between the walls;a heat exchange area exterior to the first flow path wall; andmeans for transferring heat between a plurality of vanes of the row of vanes and a flow of working fluid through the heat exchange area, the means for transferring including a heat transfer portion of the plurality of vanes extending through the first flow path wall to contact the working fluid and wherein the means for transferring is permanently devoid of heat transfer fluid internal thereto. 17. The apparatus of claim 16, wherein the means includes a fin disposed in the heat exchange area exterior to the first flow path wall. 18. A method comprising: flowing a working fluid through a rotating component of a gas turbine engine;changing a temperature of the working fluid by rotation of the rotating component;passing a heat exchange fluid through a heat exchange flow path external to a flow path that the working fluid traverses through the rotating component, the working fluid having a different temperature than the heat exchange fluid; andtransferring heat through a heat tube connected with an airfoil member disposed in flow communication with the rotating component, the heat tube extending through a wall between the heat exchange flow path and the flow path, the heat tube transferring heat between the airfoil member and the heat exchange fluid passing through the heat exchange flow path external to the rotating component by virtue of a mass flow rate along a surface of the heat tube; and wherein heat is transferred through the heat tube without using internal heat transfer fluid to transfer heat during operation of the gas turbine engine. 19. The method of claim 18, wherein the passing includes withdrawing a portion of the working fluid from the flow path of the gas turbine engine, and wherein the transferring heat includes heat exchange fluid that is relatively cooler than the working fluid. 20. The method of claim 19, wherein the withdrawing includes diverting a portion of the working fluid to a bypass flow of the gas turbine engine. 21. The method of claim 18, wherein the transferring includes intercooling a compressor of the gas turbine engine. 22. The method of claim 18, wherein the transferring includes transferring heat with a plurality of airfoil members arranged circumferentially around the rotating component of the gas turbine engine. 23. The method of claim 22, wherein the plurality of airfoil members is disposed at a plurality of axial locations.