System and method for flow control in gas turbine engine

摘要

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.

主权项

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.