Swirler Assembly with Compressor Discharge Injection to Vane Surface

摘要

A swirler assembly (2) in a gas turbine combustor includes a hub (201), a shroud, and a plurality of vanes (23) connected between the hub (201) and the shroud (202). The vanes (23) include a high pressure side (231) on which air and fuel impinge the vanes (23) and a low pressure side (232). An air circuit is provided in each of the plurality of vanes (23) receiving discharge air from a compressor. Each of the air circuits includes an air entry passage (233) into the vanes (23) and an air exit passage on the low pressure side (232) of the vanes (23).