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A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between

A combustion system is provided having a liner, a flow sleeve, a flow-obstructing element, and a venturi. The liner is disposed around a combustion region. The flow sleeve is disposed around the liner. The liner and the flow sleeve cooperate to create an air passage having an airflow located between the liner and the flow sleeve. The flow-obstructing element is disposed within the air passage, and generally obstructs the airflow in the air passage to create wakes in the airflow. The venturi is disposed downstream from the flow-obstructing element, and generally restricts and diffuses the airflow in the air passage to reduce wakes in the airflow.

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1. A combustion system, comprising: a combustor liner disposed around a combustion region;a combustor flow sleeve disposed around the combustor liner, the combustor liner and the combustor flow sleeve cooperating to create an air passage configured to receive an airflow, the air passage being locate

1. A combustion system, comprising: a combustor liner disposed around a combustion region;a combustor flow sleeve disposed around the combustor liner, the combustor liner and the combustor flow sleeve cooperating to create an air passage configured to receive an airflow, the air passage being located between the combustor liner and the combustor flow sleeve;a flow-obstructing element disposed within the air passage, the flow-obstructing element generally obstructing the airflow in the air passage and creating wakes in the airflow, wherein the flow-obstructing element is one of a cross-fire tube, a flame detector, a spark plug, a liner stop, a boss, a pressure probe, or a sensor; anda venturi section disposed downstream from the flow-obstructing element, the venturi section comprising:a first wall defined by one of the combustor liner or the combustor flow sleeve anda second wall defined by the other of the combustor liner or the combustor flow sleeve,wherein one of the first wall or the second wall converges toward the other of the first wall or the second wall defining a converging area and diverges downstream of the converging area from the other of the first wall or the second wall defining a diverging area, the diverging area being greater than the converging area,wherein a throat connects the converging area and the diverging area, the throat placed at a distance from the flow-obstructing element, the distance being no less than one and no greater than ten times a width or a diameter of the flow-obstructing element,wherein at least one air aperture is defined within the combustor flow sleeve in the diverging area downstream of the throat, andwherein the venturi section generally restricts and diffuses the airflow in the air passage to generally reduce wakes in the airflow. 2. The combustion system of claim 1, wherein the first wall is defined by the combustor flow sleeve. 3. The combustion system of claim 1, wherein the throat provides a reduction in a cross-sectional area of the air passage ranging from about 20 to about 70 percent. 4. The combustion system of claim 1, wherein the at least one air aperture is fluidly connected to the air passage, and wherein the at least one air aperture receives a high pressure air that is injected into the air passage, the high pressure air having a pressure that is greater than an air passage pressure of the air passage. 5. The combustion system of claim 4, wherein the at least one air aperture is a thru-hole located within the combustor flow sleeve, and wherein the at least one air aperture is positioned at an angle in relation to a vertical axis. 6. The combustion system of claim 5, wherein the angle ranges between about 5 degrees to about 80 degrees. 7. The combustion system of claim 4, comprising a plurality of air apertures, wherein a portion of the plurality of air apertures are positioned adjacent to and generally surrounding the flow-obstructing element, and another portion of the plurality of air apertures are positioned downstream of the flow-obstructing element, and a remaining portion of the plurality of air apertures are positioned upstream of the flow-obstructing element. 8. The combustion system of claim 1, wherein the airflow is directed to a set of quaternary vanes located in the combustion system. 9. A gas turbine having combustion system, comprising: a combustor liner disposed around a combustion region;a combustor flow sleeve disposed around the combustor liner, the combustor liner and the combustor flow sleeve cooperating to create an air passage configured to receive an airflow, the air passage being located between the combustor liner and the combustor flow sleeve; a flow-obstructing element disposed within the air passage, the flow-obstructing element generally obstructing the airflow in the air passage and creating wakes in the airflow, wherein the flow-obstructing element is one of a cross-fire tube, a flame detector, a spark plug, a liner stop, a boss, a pressure probe, or a sensor; anda venturi section disposed downstream from the flow-obstructing element, the venturi section comprising:a first wall defined by one of the combustor liner or the combustor flow sleeve, a second wall defined by the other of the combustor liner or the combustor flow sleeve,wherein one of the first wall or the second wall converges toward the other of the first wall or the second wall defining a converging area and diverges downstream of the converging area from the other of the first wall or the second wall defining a diverging area, the diverging area being greater than the converging area, andat least one air aperture that is fluidly connected to the air passage, the at least one air aperture defined within the diverging area of the combustor flow sleeve, the at least one air aperture receiving a high pressure air that is injected into the air passage, the high pressure air having a pressure that is greater than an air passage pressure of the air passage. 10. The gas turbine of claim 9, wherein the first wall is defined by the combustor flow sleeve. 11. The gas turbine of claim 9, wherein the venturi section includes a throat, wherein the throat connects the converging area with the diverging area, and wherein the throat provides a reduction in a cross-sectional area of the air passage ranging from about 20 to about 70 percent. 12. The gas turbine of claim 11, wherein the flow-obstructing element includes a dimension that represents one of a width and a diameter of the flow-obstructing element. 13. The gas turbine of claim 12, wherein the throat is located at a specified distance from the flow-obstructing element, wherein the specified distance ranges from about the dimension of the flow-obstructing element to about ten times the dimension of the flow-obstructing element. 14. The gas turbine of claim 9, wherein the at least one air aperture is a thru-hole located within the combustor flow sleeve, and wherein the at least one air aperture is positioned at an angle in relation to a vertical axis. 15. The gas turbine of claim 14, wherein the angle ranges between about 5 degrees to about 80 degrees.