NOZZLE GUIDE WITH INTERNAL COOLING FOR A GAS TURBINE ENGINE COMBUSTOR

摘要

A nozzle guide (105; 205; 300; 305; 405) is provided for a combustor (110) of a gas turbine engine (100). The nozzle guide includes an annular structure (130; 230; 330; 430) including a plurality of cooling holes (135; 235; 335; 435), a guide plate (140; 240; 340; 440) including a plurality of openings (145; 245; 345; 445) on an outer periphery of the guide plate, and a plurality of cooling passages (247; 334; 426) within the annular structure to provide air flow from the plurality of cooling holes to the plurality of openings.