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A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of

A vane carrier temperature control system for use in a gas turbine engine includes a first cooling air source, a second cooling air source, and an air temperature control system. The first cooling air source supplies a first portion of vane carrier cooling air extracted from a compressor section of the engine to a first section of a vane carrier that supports a plurality of rows of vanes within a turbine section of the engine. The second cooling air source supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section. The air temperature control system controls a temperature of at least one of the first and second portions of vane carrier cooling air.

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1. A vane carrier temperature control system in a gas turbine engine that includes a compressor section including a plurality of compressor stages, a combustion section, a turbine section including a plurality of turbine stages, and a rotatable rotor, the vane carrier temperature control system comp

1. A vane carrier temperature control system in a gas turbine engine that includes a compressor section including a plurality of compressor stages, a combustion section, a turbine section including a plurality of turbine stages, and a rotatable rotor, the vane carrier temperature control system comprising: a rotor cooling air source that supplies rotor cooling air to the rotor;a first vane carrier cooling air source that supplies a first portion of vane carrier cooling air extracted from the compressor section to a first section of a vane carrier, the vane carrier supporting a plurality of rows of vanes within the turbine section;a second vane carrier cooling air source that supplies a second portion of vane carrier cooling air extracted from the compressor section to a second section of the vane carrier, the second section being spaced from the first section in an axial direction defined by a direction of hot working gas flow through the turbine section; andan air temperature control system for controlling a temperature of at least one of the first and second portions of vane carrier cooling air, the air temperature control system comprising: a heat exchanger assembly having a first heat exchanger and a secondary cooler wherein fuel that is to be supplied to combustors in the combustion section is used as a coolant to cool the second portion of vane carrier cooling air within the secondary cooler;wherein the first heat exchanger is upstream from the secondary cooler and the first portion of vane carrier cooling air is used as a coolant to cool the second portion of vane carrier cooling air within the first heat exchanger prior to the second portion of vane carrier cooling air entering the secondary cooler; andthe secondary cooler is used to cool the second portion of vane carrier cooling air to a desired temperature if the first portion of vane carrier cooling air does not have the capacity to cool the second portion of vane carrier cooling air in the first heat exchanger all the way down to the desired temperature without the first portion of vane carrier cooling air being heated above a preferred temperature. 2. The vane carrier temperature control system of claim 1, wherein the first portion of vane carrier cooling air is extracted from a first section of the compressor section and the second portion of vane carrier cooling air is extracted from a second section of the compressor section that is spaced from the first section of the compressor section in a direction of compressed air flow through the compressor section. 3. The vane carrier temperature control system of claim 2, wherein: the first portion of vane carrier cooling air is extracted from an upstream stage of the compressor section and the second portion of vane carrier cooling air is extracted from a downstream stage of the compressor section with reference to the direction of compressed air flow through the compressor section; andthe first portion of vane carrier cooling air is supplied to an axially downstream stage of the turbine section and the second portion of vane carrier cooling air is supplied to an axially upstream stage of the turbine section. 4. The vane carrier temperature control system of claim 1, further comprising a pair of bypass circuits including respective valves for selectively allowing the first and second portions of vane carrier cooling air to bypass the first heat exchanger. 5. The vane carrier temperature control system of claim 1, wherein the first heat exchanger is configured such that the temperatures of the first and second portions of vane carrier cooling air are each within about 25° C. of a temperature of the rotor cooling air at axial locations corresponding to where the respective portions of vane carrier cooling air are supplied to the vane carrier. 6. The vane carrier temperature control system of claim 1, further comprising a bypass circuit including a valve for selectively allowing the second portion of vane carrier cooling air to bypass the heat exchanger. 7. A vane carrier temperature control system in a gas turbine engine that includes a compressor section including a plurality of compressor stages, a combustion section, a turbine section including a plurality of turbine stages, and a rotatable rotor, the vane carrier temperature control system comprising: a rotor cooling air source that supplies rotor cooling air to the rotor;a first vane carrier cooling air source that supplies a first portion of vane carrier cooling air extracted from an upstream section of the compressor section with respect to a direction of compressed air flow through the compressor section to a downstream section of a vane carrier with reference to an axial direction defined by a direction of hot working gas flow through the turbine section, the vane carrier supporting a plurality of rows of vanes within the turbine section;a second vane carrier cooling air source that supplies a second portion of vane carrier cooling air extracted from a downstream section of the compressor section with reference to the direction of compressed air flow through the compressor section to an axially upstream section of the vane carrier;a third vane carrier cooling air source that supplies a third portion of vane carrier cooling air extracted from an intermediate section of the compressor section with respect to the direction of compressed air flow through the compressor section to an axially intermediate section of the vane carrier; andan air temperature control system including a heat exchanger assembly having a first heat exchanger and a secondary cooler for controlling a temperature of the second portion of vane carrier cooling air, the secondary cooler using fuel that is to be supplied to combustors in the combustion section as a coolant such that the temperature of the second portion of vane carrier cooling air is within a predetermined temperature differential relative to a temperature of the rotor cooling air at a predetermined location;wherein the first heat exchanger is upstream from the secondary cooler and the first portion of vane carrier cooling air is used as a coolant in the first heat exchanger to cool the second portion of vane carrier cooling air within the first heat exchanger before the second portion of vane carrier cooling air enters the secondary cooler. 8. The vane carrier temperature control system of claim 7, further comprising a pair of bypass circuits including respective valves for selectively allowing the first and second portions of vane carrier cooling air to bypass the first heat exchanger. 9. The vane carrier temperature control system of claim 7, wherein the first heat exchanger is configured such that the temperatures of the first and second portions of vane carrier cooling air are each within about 25° C. of the temperature of the rotor cooling air at axial locations corresponding to where the respective first and second portions of vane carrier cooling air are supplied to the vane carrier. 10. A method for operating a gas turbine engine that includes a compressor section including a plurality of compressor stages, a combustion section, a turbine section including a plurality of turbine stages, and a rotatable rotor, the method comprising: supplying rotor cooling air to the rotor;supplying a first portion of vane carrier cooling air extracted from an upstream section of the compressor section with reference to a direction of compressed air flow through the compressor section to a downstream section of a vane carrier with respect to an axial direction defined by a direction of hot working gas flow through the turbine section, the vane carrier supporting a plurality of rows of vanes within the turbine section;supplying a second portion of vane carrier cooling air extracted from a downstream section of the compressor section with respect to the direction of compressed air flow through the compressor section to an axially upstream section of the vane carrier; andcontrolling a temperature of the second portion of vane carrier cooling air in a heat exchanger assembly having a first heat exchanger and a secondary cooler, the secondary cooler using fuel that is to be supplied to combustors in the combustion section as a coolant such that the second portion of vane carrier cooling air is within a predetermined temperature differential relative to a temperature of the rotor cooling air at a predetermined location;wherein the first heat exchanger is upstream from the secondary cooler and the first portion of vane carrier cooling air is used as a coolant in the first heat exchanger to cool the second portion of vane carrier cooling air within the first heat exchanger before the second portion of vane carrier cooling air enters the secondary cooler. 11. The method of claim 10, further comprising supplying a third portion of vane carrier cooling air extracted from an intermediate section of the compressor section with respect to the direction of compressed air flow through the compressor section to an axially intermediate section of the vane carrier. 12. The method of claim 10, further comprising providing a pair of bypass circuits to selectively allow the first and second portions of vane carrier cooling air to bypass the heat exchanger under select operating conditions. 13. The method of claim 10, further controlling the temperature of the first and second portions of vane carrier cooling air in the first heat exchanger such that each is within about 25° C. of the temperature of the rotor cooling air at axial locations corresponding to where the respective portions of vane carrier cooling air are supplied to the vane carrier. 14. The vane carrier temperature control system of claim 7, wherein the secondary cooler is used to cool the second portion of vane carrier cooling air to a desired temperature if the first portion of vane carrier cooling air does not have the capacity to cool the second portion of vane carrier cooling air in the first heat exchanger all the way down to the desired temperature without the first portion of vane carrier cooling air being heated above a preferred temperature. 15. The method of claim 10, wherein the first heat exchanger is upstream from the secondary cooler and the secondary cooler is used to cool the second portion of vane carrier cooling air to a desired temperature if the first portion of vane carrier cooling air does not have the capacity to cool the second portion of vane carrier cooling air in the first heat exchanger all the way down to the desired temperature without the first portion of vane carrier cooling air being heated above a preferred temperature.