A method, apparatus, and systems for circumferentially aligning turbine blades with respect to combustor tubes and cooling airflow through the turbine hot gas flowpath

摘要

A method of operating a turbine engine (100), wherein the turbine engine (100) includes a compressor (106), a combustor (112), a turbine (110), a plurality of sequentially axially disposed stages that are a series of circumferentially spaced apart ones Stator blades (128) and circumferentially spaced rotor blades (126) and a plurality of circumferentially spaced injection ports (156) disposed upstream of a first row of stator blades (128) in the turbine (110); wherein the injection openings (156) have an opening through which cooling air is injected into the hot gas path of the turbine (110), and wherein the method comprises the steps of: configuring the stator vanes (128) in the first row of stator vanes (128) such that the circumferential position of a leading edge (222) of one of the stator blades (128) is within ± 15% of the pitch of the first row of stator blades (128) from the circumferential location of the injection port center (224) of at least a majority of the injection ports (156).