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A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine

A gas turbine engine system having a combustion section and a turbine section is provided. The turbine section includes at least one turbine stage having a plurality of turbine blades coupled to a rotor and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about at least a portion of the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises at least one air inlet and the inner casing comprises at least one air outlet. At least one flange is provided within the cavity, and the at least one flange flanks the air inlet and at least one flow guide.

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1. A system, comprising: a gas turbine engine, comprising: a combustion section;a turbine section coupled to the combustion section, wherein the turbine section comprises a plurality of turbine stages having a plurality of turbine blades coupled to a rotor, an inner casing circumferentially disposed

1. A system, comprising: a gas turbine engine, comprising: a combustion section;a turbine section coupled to the combustion section, wherein the turbine section comprises a plurality of turbine stages having a plurality of turbine blades coupled to a rotor, an inner casing circumferentially disposed about the plurality of turbine blades, and an outer casing circumferentially disposed about at least a portion of the inner casing, wherein the inner casing and the outer casing define a cavity between the inner casing and the outer casing, wherein the cavity comprises a volume extending between a forward portion and an aft portion to facilitate distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing, wherein the forward portion is closer to the combustion section than the aft portion, wherein the cavity extends axially in a longitudinal direction of the turbine section to surround respective portions of at least two turbine stages of the plurality of turbine stages, wherein the outer surface of the inner casing comprises a curved portion that gradually curves inwardly toward a longitudinal axis of the gas turbine engine in an upstream direction relative to a flow of a working fluid in the gas turbine engine and the curved portion extends axially in the longitudinal direction of the turbine section to surround respective portions of the at least two turbine stages of the plurality of turbine stages, wherein the outer casing comprises at least one air inlet for the air to flow into the aft portion of the cavity, and the inner casing comprises at least one air outlet for the air to flow out of the forward portion of the cavity directly into a turbine nozzle; andat least one flange disposed within the cavity, wherein the at least one flange flanks the at least one air inlet and at least one flow guide, wherein the at least one flange and a first flow guide of the at least one flow guide extend axially in the longitudinal direction of the turbine section along at least a portion of the outer surface of the inner casing, and wherein the at least one flow guide is configured to change a velocity or a direction of an air flow within the cavity to facilitate heat transfer along the outer surface of the inner casing and the inner surface of the outer casing. 2. The system of claim 1, comprising at least one protrusion of the at least one flow guide disposed on the outer surface of the inner casing and extending circumferentially about the inner casing, wherein the at least one protrusion is configured to facilitate distribution of the air flow within the cavity. 3. The system of claim 2, wherein at least one slot is disposed within the at least one protrusion to facilitate distribution of the air flow within the cavity. 4. The system of claim 1, comprising a first protrusion of the at least one flow guide extending radially into the cavity from the inner surface of the outer casing and a second protrusion of the at least one flow guide extending radially into the cavity from the outer surface of the inner casing, wherein the first and second protrusions radially overlap and are axially offset along the longitudinal direction of the turbine section to form a gap configured to enable the air flow between the first and second protrusions from the aft portion toward the forward portion of the cavity. 5. The system of claim 1, comprising at least one perforated plate of the at least one flow guide extending between the inner casing and the outer casing. 6. The system of claim 5, wherein a first end of the at least one perforated plate is coupled to a first bracket disposed on the inner surface of the outer casing and a second end of the at least one perforated plate is coupled to a second bracket disposed on the outer surface of the inner casing. 7. The system of claim 1, wherein the cavity comprises one or more flow guides of the at least one flow guide extending in an axial direction, a radial direction, a circumferential direction, or a combination thereof, relative to the longitudinal direction of the turbine section. 8. The system of claim 1, wherein the cavity comprises a pair of flanges of the at least one flange flanking the at least one air inlet and a pair of flow guides of the at least one flow guide. 9. The system of claim 1, wherein an orthogonal distance between the outer surface of the inner casing and the inner surface of the outer casing varies by between 0% and 10% along a length of the cavity between the at least one air inlet and the at least one air outlet. 10. The system of claim 1, wherein the cavity extends axially to surround respective portions of at least three turbine stages of the plurality of turbine stages. 11. The system of claim 1, wherein a first axial end of the cavity is located on a first side of one turbine stage of the at least two turbine stages of the plurality of turbine stages, and a second axial end of the cavity is located on a second side of the one turbine stage along the longitudinal axis, such that the cavity extends axially across an entire axial length of the one turbine stage. 12. A system, comprising: a cooling assembly for a turbine section of a gas turbine comprising a plurality of turbine stages, the cooling assembly comprising: an inner casing having a first inner surface and a first outer surface, the inner casing being circumferentially disposed about a portion of the turbine section of the gas turbine;an outer casing having a second inner surface and a second outer surface, the outer casing being circumferentially disposed about at least a portion of the inner casing; anda cavity defined by the first outer surface of the inner casing and the second inner surface of the outer casing, the cavity extending axially in a longitudinal direction of the turbine section to surround respective portions of at least two turbine stages of the plurality of turbine stages, the cavity having a volume configured to facilitate an air flow within the cavity to cool the first outer surface of the inner casing and the second inner surface of the outer casing, wherein the first outer surface of the inner casing comprises a curved portion that gradually curves inwardly toward a longitudinal axis of the gas turbine in an upstream direction relative to a flow of a working fluid in the gas turbine and the curved portion extends axially in the longitudinal direction to surround respective portions of the at least two turbine stages of the plurality of turbine stages;at least one inlet configured to receive air proximate to a first end of the cavity, the at least one inlet being distributed circumferentially about the cavity;a plurality of outlets configured to exhaust air directly into a turbine nozzle proximate to a second end of the cavity, the outlets being distributed circumferentially about the cavity; anda plurality of flanges extending axially in the longitudinal direction of the turbine section along at least a portion of the first outer surface of the inner casing, wherein each of pairs of adjacent flanges of the plurality of flanges flank at least two flow guides. 13. The system of claim 12, wherein the second inner surface of the outer casing gradually curves inwardly toward the longitudinal axis of the gas turbine in the upstream direction relative to the flow of the working fluid in the gas turbine. 14. The system of claim 13, wherein an orthogonal distance between the first outer surface of the inner casing and the second inner surface of the outer casing varies by between 0% and 10% along a length of the cavity between the at least one inlet and the plurality of outlets. 15. The system of claim 12, comprising at least one protrusion of the at least two flow guides disposed on the first outer surface of the inner casing and extending circumferentially around the inner casing, wherein the at least one protrusion is configured to facilitate distribution of the air flow within the cavity. 16. The system of claim 12, comprising a first protrusion of the at least two flow guides extending radially into the cavity from the second inner surface of the outer casing and a second protrusion of the at least two flow guides extending radially into the cavity from the first outer surface of the inner casing, wherein the first and second protrusions radially overlap and are axially offset relative to the longitudinal direction of the turbine section to form a gap configured to enable the air flow between the first and second protrusions from the first end toward the second end of the cavity. 17. The system of claim 12, comprising at least one perforated plate of the at least two flow guides extending between the inner casing and the outer casing, wherein the at least one perforated plate is configured to enable the air flow to flow through the at least one perforated plate from the first end toward the second end of the cavity. 18. A method comprising: routing air through an inlet disposed proximate a first end of a cavity formed between an inner casing and an outer casing of a turbine section of a gas turbine, wherein the cavity extends axially in a longitudinal direction of the turbine section to surround respective portions of at least two turbine stages of the turbine section, and the cavity has a volume configured to facilitate cooling of the inner casing and the outer casing;routing the air around a plurality of surface features disposed within the cavity, wherein the surface features include at least one flow guide extending axially along an outer surface of the inner casing in the longitudinal direction of the turbine section, the at least one flow guide being flanked by at least two flanges, wherein the outer surface of the inner casing comprises a curved portion that gradually curves inwardly toward a longitudinal axis of the gas turbine in an upstream direction relative to a flow of a working fluid in the gas turbine and the curved portion extends axially in the longitudinal direction to surround respective portions of the at least two turbine stages; androuting the air through at least one outlet disposed proximate to a second end of the cavity directly into a turbine nozzle. 19. The method of claim 18, wherein an inner surface of the outer casing gradually turns inwardly toward the longitudinal axis of the gas turbine in the upstream direction relative to the flow of the working fluid in the turbine section of the gas turbine. 20. The method of claim 19, wherein routing the air around the plurality of surface features comprises controlling the air flow to control radial and axial clearances in the turbine section of the gas turbine.