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A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides

A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.

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1. A gas turbine engine including a longitudinal axis defining an axial direction of the engine, the engine comprising: a compressor section where air pulled into the engine is compressed;a combustion section comprising a plurality of combustor apparatuses where, during a first mode of engine operat

1. A gas turbine engine including a longitudinal axis defining an axial direction of the engine, the engine comprising: a compressor section where air pulled into the engine is compressed;a combustion section comprising a plurality of combustor apparatuses where, during a first mode of engine operation fuel is mixed with at least a portion of the compressed air from the compressor section and burned to create hot combustion gases;a turbine section where, during the first mode of engine operation the hot combustion gases from the combustion section are expanded to extract energy from the combustion gases;a casing having a portion disposed about the combustion section, the casing portion comprising a casing wall having a top wall section defining a top dead center, left and right side wall sections, and a bottom wall section defining a bottom dead center, the casing portion further defining an interior volume in which the combustor apparatuses and air compressed by the compressor section are located; anda shell air recirculation system comprising: at least one outlet port located at the bottom wall section of the casing wall;first and second inlet ports located at the top wall section of the casing wall, the inlet ports being circumferentially spaced apart from one another and located at generally the same axial location;a piping system that provides fluid communication between the at least one outlet port and the inlet ports;a blower for extracting air from the interior volume of the casing portion through the at least one outlet port and for conveying the extracted air to the inlet ports; anda valve system that is configured to be: closed during the first mode of engine operation to substantially prevent air from passing through the piping system; andopen during a second mode of engine operation for allowing air to pass through the piping system such that at least a portion of the air in the interior volume of the casing portion is extracted from the at least one outlet port by the blower and conveyed by the blower to the inlet ports for injection into the top wall section of the casing wall, wherein the inlet ports are configured such that the air injected thereby:includes a velocity component in the circumferential direction; andis injected at least partially in respective directions toward one another and toward the top dead center of the casing wall, the top dead center of the casing wall being located circumferentially between the inlet ports. 2. The gas turbine engine of claim 1, wherein the first mode of engine operation is full load operation. 3. The gas turbine engine of claim 2, wherein the second mode of engine operation is less than full load operation. 4. The gas turbine engine of claim 1, wherein the inlet ports are configured such that the air injected thereby flows from the top wall section of the casing wall down the left and right side wall sections of the casing wall toward the bottom wall section of the casing wall. 5. The gas turbine engine of claim 4, wherein the inlet ports are configured such that the air injected thereby includes a velocity component in the axial direction. 6. The gas turbine engine of claim 1, wherein the at least one outlet port and the inlet ports are also configured to function as steam augmentation pipes to introduce high pressure steam into the interior volume of the casing portion during the first mode of operation. 7. The gas turbine engine of claim 1, wherein the combustion section comprises a can annular combustion section and the plurality of combustor apparatuses comprises an annular array of combustor apparatuses. 8. A gas turbine engine including a longitudinal axis defining an axial direction of the engine, the engine comprising: a compressor section where air pulled into the engine is compressed;a combustion section comprising a plurality of combustor apparatuses where, during a first mode of engine operation fuel is mixed with at least a portion of the compressed air from the compressor section and burned to create hot combustion gases;a turbine section where, during the first mode of engine operation the hot combustion gases from the combustion section are expanded to extract energy from the combustion gases;a casing having a portion disposed about the combustion section, the casing portion comprising a casing wall having a top wall section defining a top dead center, left and right side wall sections, and a bottom wall section defining a bottom dead center, the casing portion further defining an interior volume in which the combustor apparatuses and air compressed by the compressor section are located; anda shell air recirculation system comprising: at least one outlet port located at the bottom wall section of the casing wall;first and second inlet ports located at the top wall section of the casing wall, the first inlet port including an outlet facing in a circumferential direction toward the first sidewall section of the casing wall and the second inlet port including an outlet facing in a circumferential direction toward the second sidewall section of the casing wall such that air injected by the first and second inlet ports flows respectively down both the left and right side wall sections to the bottom wall section of the casing wall;a piping system that provides fluid communication between the at least one outlet port and the inlet ports;a blower that is configured to extract air from the interior volume of the casing portion through the at least one outlet port and to convey the extracted air to the inlet ports during the first mode of engine operation; anda valve system that is configured to be: closed during the first mode of engine operation to substantially prevent air from passing through the piping system; andopen during a second mode of engine operation for allowing air to pass through the piping system such that at least a portion of the air in the interior volume of the casing portion is extracted from the at least one outlet port by the blower and conveyed by the blower to the inlet ports. 9. The gas turbine engine of claim 8, wherein the first mode of engine operation is full load operation and the second mode of engine operation is less than full load operation. 10. The gas turbine engine of claim 9, wherein the combustion section comprises a can annular combustion section and the plurality of combustor apparatuses comprises an annular array of combustor apparatuses. 11. The gas turbine engine of claim 8, wherein the first and second inlet ports are circumferentially spaced apart and located at generally the same axial location, wherein the inlet ports are both configured to inject air in a direction toward one another and toward the top dead center of the casing wall. 12. The gas turbine engine of claim 11, wherein the inlet ports are configured such that the air injected thereby includes a velocity component in the axial direction toward the compressor section and away from the turbine section. 13. The gas turbine engine of claim 8, wherein the at least one outlet port and the inlet ports are also configured to function as steam augmentation pipes to introduce high pressure steam into the interior volume of the casing portion during the first mode of operation. 14. A gas turbine engine including a longitudinal axis defining an axial direction of the engine, the engine comprising: a compressor section where air pulled into the engine is compressed;a can annular combustion section comprising an annular array of combustor apparatuses where, during a first mode of engine operation fuel is mixed with at least a portion of the compressed air from the compressor section and burned to create hot combustion gases;a turbine section where, during the first mode of engine operation the hot combustion gases from the combustion section are expanded to extract energy from the combustion gases;a casing having a portion disposed about the combustion section, the casing portion comprising a casing wall having a top wall section defining a top dead center, left and right side wall sections, and a bottom wall section defining a bottom dead center, the casing portion further defining an interior volume in which the combustor apparatuses and air compressed by the compressor section are located; anda shell air recirculation system comprising: at least one outlet port located at the bottom wall section of the casing wall;first and second inlet ports located at the top wall section of the casing wall, the inlet ports being circumferentially spaced apart from one another and located at generally the same axial location, at least one of the outlet and inlet ports also being configured to function as a steam augmentation pipe to introduce high pressure steam into the interior volume of the casing portion during a first mode of operation;a piping system that provides fluid communication between the at least one outlet port and the inlet ports;a blower that is configured to extract air from the interior volume of the casing portion through the at least one outlet port and for conveying the extracted air to the inlet ports during the first mode of engine operation; anda valve system that is configured to be: closed during the first mode of engine operation to substantially prevent air from passing through the piping system; andopen during a second mode of engine operation for allowing air to pass through the piping system such that at least a portion of the air in the interior volume of the casing portion is extracted from the at least one outlet port by the blower and conveyed by the blower to the inlet ports for injection into the top section of the casing wall, wherein the inlet ports are configured to inject air in opposing circumferential directions such that the air injected thereby flows down both the left and right side wall sections to the bottom wall section of the casing wall. 15. The gas turbine engine of claim 14, wherein each of the outlet and inlet ports are also configured to function as a steam augmentation pipe to introduce high pressure steam into the interior volume of the casing portion during the first mode of operation. 16. The gas turbine engine of claim 14, wherein the first inlet port is located near the left side wall section of the casing wall and the second inlet port is located near the right side wall section of the casing wall. 17. The gas turbine engine of claim 16, wherein the inlet ports are configured such that the air injected thereby is injected at least partially in respective directions toward one another and toward the top dead center of the casing wall, the top dead center of the casing wall being located circumferentially between the inlet ports. 18. The gas turbine engine of claim 17, wherein the inlet ports are configured such that the air injected thereby includes a velocity component in the axial direction.