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A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The s

A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.

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1. A system, comprising: a gas turbine combustor, comprising: a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner;an air passage between the combustion liner and the flow sleeve;a structure between the combustion liner and the flow sleeve, wherein

1. A system, comprising: a gas turbine combustor, comprising: a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner;an air passage between the combustion liner and the flow sleeve;a structure between the combustion liner and the flow sleeve, wherein the structure obstructs an airflow through the air passage; anda wake reducer disposed adjacent the structure, wherein the wake reducer directs a flow into a wake region downstream of the structure, the wake reducer comprises an upstream opening configured to intake a portion of the airflow, a downstream opening configured to exhaust the portion of the airflow into the wake region, and an intermediate passage between the upstream opening and the downstream opening, and the intermediate passage is defined between the structure and the wake reducer. 2. The system of claim 1, wherein the wake reducer comprises a plurality of upstream openings configured to intake the portion of the airflow. 3. The system of claim 1, wherein the wake reducer comprises a plurality of downstream openings configured to exhaust the portion of the airflow into the wake region. 4. The system of claim 1, wherein the wake reducer comprises a flow control wall disposed about the structure to define the intermediate passage, and the flow control wall comprises the upstream opening and the downstream opening. 5. The system of claim 4, wherein the flow control wall comprises first and second wall portions disposed on opposite first and second sides of the structure, the first wall portion extends between the upstream opening and the downstream opening on the first side of the structure, and the second wall portion extends between the upstream opening and the downstream opening on the second side of the structure. 6. The system of claim 5, wherein the first and second wall portions converge toward one another along the airflow toward the downstream opening. 7. The system of claim 1, wherein the wake reducer comprises a flow control wall at an offset distance from the structure, and the flow control wall curves around the structure from an upstream side to a downstream side of the structure. 8. The system of claim 7, wherein the structure comprises an elongated structure having a circular cross-section, and the flow control wall comprises a circular wall disposed about the circular cross-section. 9. The system of claim 7, wherein the structure comprises an elongated structure having an oval cross-section or aerodynamic shaped cross-section, and the flow control wall comprises an oval wall or aerodynamic shaped wall disposed about the oval cross-section or the aerodynamic shaped cross-section. 10. The system of claim 1, wherein the wake reducer comprises a plurality of upstream or downstream openings configured to direct the flow into the wake region. 11. The system of claim 1, comprising a fuel injector disposed downstream of the combustion liner and the flow sleeve, wherein the fuel injector obstructs the airflow through the air passage downstream from the structure, and the wake reducer is configured to reduce a wake in the airflow from the structure. 12. The system of claim 1, wherein the structure comprises a cross-fire tube configured to extend between the gas turbine combustor and another gas turbine combustor, a flame detector, a spark plug, a boss, a spacer, a pressure probe, a late lean injector, a sensor, or a combination thereof. 13. A system, comprising: a gas turbine engine, comprising: a turbine wake reducer configured to reduce a wake in a wake region downstream from a structure obstructing a gas flow of the gas turbine engine, wherein the turbine wake reducer comprises: a flow control wall configured to surround the structure;an upstream opening configured to intake a portion of the gas flow into an intermediate passage between the flow control wall and the structure; anda downstream opening configured to exhaust the portion of the gas flow into the wake region; anda fuel injector disposed downstream of the turbine wake reducer and the structure, wherein the fuel injector is configured to obstruct the gas flow downstream from the turbine wake reducer and the structure. 14. The system of claim 13, wherein the flow control wall is an airfoil shaped wall. 15. The system of claim 13, comprising the structure, wherein the structure comprises an internal flow passage. 16. The system of claim 13, wherein the gas turbine engine comprises: a combustion liner disposed about a combustion region;a flow sleeve disposed about the combustion liner; anda gas passage between the combustion liner and the flow sleeve, wherein the structure obstructs the gas flow through the gas passage. 17. The system of claim 13, comprising an intermediate passage between the upstream opening and the downstream opening, wherein the intermediate passage is defined between the structure and the turbine wake reducer. 18. A method, comprising: reducing, via a wake reducer, a wake in a wake region downstream from a structure that obstructs an airflow between a combustion liner and a flow sleeve of a gas turbine combustor, wherein reducing the wake comprises redirecting a portion of the airflow from an upstream opening that intakes a portion of the airflow, through an intermediate passage defined between the structure and the wake reducer, and out through a downstream opening that exhausts the portion of the airflow into the wake region. 19. The method of claim 18, comprising flowing the portion of the airflow along a curved path between a flow control wall and the structure, wherein the flow control wall surrounds the structure.